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R-7 - SS-6 SAPWOODThe R-7/SS-6 Sapwood, the first Soviet intercontinental ballistic missile developed andprogrammed for operational deployment in the USSR, is a one and one-half stage,cryogenic liquid-propellant missile. According to Western estimates it was capable ofdelivering a 9000 lb reentry vehicle to a maximum operational range of 6500 nm with aCEP of approximately 2 nm.

The R-7 missile became the first Soviet intercontinental ballistic missile. It was based onplans laid out in the governmental order from February 13, 1953 to develop a two-stageballistic missile with a range of 7000-8000 km. The original design plans provided for atotal weight of the nose cone plus warhead of 3 tons. However, soon after the first tests inOctober 1953 were carried out, the design was substantially changed. The total weight ofthe nose cone was increased to carry a thermonuclear warhead of 3 tons. To preserve theprevious maximum range it was necessary to redesign the missile completely since thelaunch weight was increased from 170 up to 280 ton. The development of this two-stageballistic missile was approved on May 20, 1954.

The R-7 missile employs a unique parallel division of stages, consisting of one centralsustainer and four strap-on boosters, all of which were started simultaneously at liftoff.The strap-on boosters formed the first stage, and the central sustainer constituted thesecond stage. This tandem structure allowed the start and control of all engines at normalatmospheric pressure [the Atlas first-generation American ICBM employed a similarprinciple, while using common propellant tanks for both booster and sustainer engines].Each of the stages featured a four-chamber open-cycle rocket engine using liquid oxygenand kerosene. Flight control was achieved by vernier engines located on the straponboosters and the core sustainer. Aerodynamic fins located on the aft bay of the strap-onsalso provided for flight control.

The missile had a combined command structure consisting of both an independentautonomous system and a radio command system. The independent autonomous systemprovided attitude control for the missile with respect to the vehicle's center of mass andmotion on the planned trajectory. It also controlled the synchronous draining of thepropellant tanks in all units of the first stage. The system of radio control carried out in-flight trajectory corrections and provided for an increase of delivery accuracy.

The flight tests of the 8K71 missile began on 15 May 1957. The spectacular launch of thefirst Sputnik satellite in October 1957 revealed a rocket with a thrust far in excess ofanything the United States could then produce. The Soviet feat caused the United Statesto review its missile programs in order to narrow the rocket-booster gap. To sustainmorale, several small American satellites using the Jupiter and Vanguard boosters werelaunched in 1958, but it would take considerable time to construct engines equaling thosealready developed by the Russians.

The results of the first six tested R-7 (two of which were used in a modified version toplace the first two Sputnik satellites into orbit) led to a modification of the nose cone andits mode of separation. During the first launches the nose cone collided after its'separation with a missile body and was destroyed during atmospheric reentry. Between29 March and 10 July 1958 the new design with a modified nose cone was successfullytested and between 24 1958 and 27 November 1959 16 flight tests were conducted toassure the reliability of the design. Following the completion of tests in December 1959the first launch complexes were put on an alert, and on 20 January 1960 deployment ofthe R-7 missile started..

During the test phase of the R-7 missile, on 02 July 1958, a ministerial decree was issuedfor the development of an improved ICBM based on the R-7 design. The new R-7A(8K74) included a modernized lighter warhead, more powerful engines and an increasedpropellant volume. Thus maximum range was increased from 8000 up to 12000 km. Anewly developed gyroscopic inertial navigation system, replacing the previous radio-command control system, improved the missile's accuracy. Flight tests of this variantwere conducted from December 1959 through July 1960. In January 1960 for the firsttime a successful test of a long-range missile carried out with successful delivery of thenose cone into the Pacific Ocean. Eight missile launches were carried out of which sevenwere successful. In early 1960 theR-7A missile was put on active alert.

The 8K71 and 8K74 missiles were put on alert at test facilities at the Baikonurcosmodrome and at "Angara" in the Arkhangelsk area (subsequently known as Plesetsk).They were deployed at five sites that consisted of six launch facilities in total. The SS-6ICBM system has had limited deployment in fixed soft sites in northwestern USSR. Thesystem reaction time in the normal readiness condition was approximately ten hours.Because of the cryogenic oxidizer, the allowable hold time in the maximum alertcondition (reaction time equals five to ten minutes) was approximately one hour. By mid-1968 the SS-6 ICBM had been phased out of the operational inventory. Use of the SS-6 isnow restricted to space applications.

SpecificationsDIA SS-6 SS-6

NATO Sapwood Sapwood

Bilateral

Service R-7 R-7A, R-7M

OKB/Industry 8K71 8K74/8K710

Design

Bureaus

OKB-1 (Acad.S. P. Korolev),

NII-88

OKB-1 (Acad. S. P.Korolev),

NII-88

Approved 5/20/1954 7/2/1958

Years of R&D 1954 -1959 1954 -1959

Engineering andTesting

1957 - 59 1959 - 60

First Flight Test 5/15/57 12/23/59

IOC 1960 1960

Deployment Date 1/20/1960 9/12/1960

Type of Warhead Single Single

Warheads 1 1

Yield (Mt) 3-5 3-5

Payload (t) 5.3 -5.5 3.0 -3.7 or 2.2

Total length (m) 34.22 - 33 -31.07

31.070

Total length w/owarhead (m)

28 28

Missile Diameter (m) 2.95 coresustainer Total= 10.3

2.95 core sustainer Total= 10.3

Launch Weight (t) Total = 280 -283

274.5 Total = 276

Fuel Weight (t) Total = 253 Total = 250

Range (km) 8,000-8,500-8,800

9,000-9,500 or 12,000-14,000

CEP (m) (RussianSources)

2,500 -5,000 5,000

CEP (m) (WesternSources)

3,700 3,000 -3,700

Number of Stages 2Canister length (m) N/ACanister length w/o

Front meters (m)

N/A

Canister diameter (m) N/ABooster guidance system Autonomous inertial plus radio control

1st stage 2nd stagefour Strap-on's Sustainer Core

Length (m) 19.2 28.0Body diameter (m) 2.68 tapered cone 2.15 -2.95 hammerhead shapeFueled weight (t) 4 x 42.5=170.0

4 x 39.2=156.8

1st. 30.08+2nd. 79.92=110 total -5.5warhead=104.5 or 5.5 + core93.355 +11.145=110-5.5=104.5 or95.400 + Payload Mass

Dry weight (t) ~22 -24.5 total +Payload Mass or3.784 x 4=15.1360

~22 total + Payload Mass or 6.525+ Payload Mass

Engine Designation Four RD-107 's(8D74)

RD-108 (8D75)

Design bureau Acad. V. P. GlushkoOKB-456

Acad. V. P. Glushko OKB-456

Years of R&D 1954-1957 1954-57Propellants Liquid LiquidFuel Kerosene, (T-1) Kerosene, (T-1)Oxidizer Liquid Oxygen Liquid OxygenBurning time (sec.) 120-118 + 10 start 310 - 320 + 10 start timeVerniers Thrust SeaLevel/Vacuum (Tonnes)

8 x ~ 3.9 = 31.2Vac. Total

4 x ~3.9 = 15.6 Vac. Total

Main engines Thrust SeaLevel/Vacuum (Tonnes)

4 x 83.77=334.8 / 4x 99-102=408

1 x 75.90 / 90-93- 94.1-96 Vac.

Total thrust launch

(Tonnes)

403.4/9 - 410.7 1st. shutdown thrust 497

Specific Impulse (sec.) 257-259 / 305-308 248 / 305-309-315-316Basing Mode Ground BasedLaunching Mode Hot launchDeployed boosters 0Test BoostersWarheads Deployed 0Deployment Sites 5 launch pads -3 Plesetsk, 2 BaikonurTraining LaunchersSpace Booster Variant Yes

SL-1/A, Sputnik

SL-3, A-1, Lunik, Vostok

SL-4/A-2, Soyuz

SL-6/A-2-e, Molniya

SL-4/ A-2 / Soyuz-2

Historical Review - WesternEstimates

First system flight test January 30,1958

Operational training flights began October 1959

Initial operational capability Early 1960

Deployed missiles retrofitted with 9000 lb reentry vehicleLate 1960-Early 1961

Maximum operational deployment (four missiles) reached 1962

Last missile test firing 1966

Phase-out completed 1968

R-9 - SS-8 SASINThe R-9/SS-8 Sasin intercontinental ballistic missile is a two-stage, tandem, cryogenicliquid-propellant missile. According to Western assessements it was capable of deliveringa 3500 lb reentry vehicle to a maximum operational range of 6000 nm with a CEP ofabout 1.0 nm.

The R-9 was the last Soviet ICBM using cryogenic propellant. This two-stage ICBM hadsequential stages that were connected by a truss. The first stage was equipped with aclosed cycle engine with four combustion chambers that used a liquid cryogenicpropellant developed by NPO Energomash Imeni V.P. Glushko (OKB-456). For thesecond stage an open-cycle four combustion chamber engine developed by KBKhimavtomakiki (OKB-154) was employed. The flight control during the first stageflight used a new system of gimbaled combustion chambers of the sustainer stage. Theflight control of the second stage was provided through control nozzles using exhaust gasfrom the turbopump unit. As the separation of the first stage occurred at an altitude wherethe influence of aerodynamic forces was still essential, the application of stabilizers wasnecessary. To maintain aerodynamic stability during the first seconds of flight of thesecond stage four aerodynamic fins were placed on its aft bay. They opened after theseparation from the first stage. Several seconds afterwards the aft bay of the second stagewas also separated. The R-9 was the first Soviet ICBM to incorporate pressurization ofthe main propellant in the fuel tanks, which obviated the need for special bottles with apressuring gas.

The original missile had a combined command structure with a radio engineeringchannels. The inertial system provided flight control during almost all the activetrajectory except for the last ten seconds which were controlled by a radio-correction-system. Subsequently however, the use of a radio engineering channel was discarded, andthe command system of the missile allowed to execute autonomous monitoring of missileflight parameters. .

The missile could be equipped with two different nose cones according to differentpayloads: a light nose cone capable of containing a warhead with a yield of 1.7 MT and aheavier one with a warhead of 2.09 MT.

The original missile was intended to be surface launched, but in 1960 the development ofa silo-launched version was begun. In total three different launch complexes weredeveloped: Two ground-launch complexes (Desna-N/Valley) and a silo-launch complex("Desna-V").were developed. Two launchers, a command center, missile and propellantdepots and radio command guidance system formed part of the "Desna-N" launchcomplex. The "Valley" complex had a similar structure, but was equipped with anautomatic system that could carry out a launch within 20 minutes. Within this time themissile could be transported from the depot to the launch-complex, installed, fueledprepared and targeted. The minimal interval for the next missile firing lasted from nineminutes for the next launcher up to 2.5 hours for a repeat launch from one pad.

The silo-launch complex "Desna-V" consists of three silos, located in a straight line closeto each other an underground command center, underground depots of propellantcomponents and compressed gases and a radio control complex. The silos were 36 mdeep with a minimum diameter of 7.8 m and a canister diameter of 5.5 m. For the firsttime a hot launch of a missile from the silo was accomplished through the use of oxygenthat was previously cooled to –186C. The missile could be held in readiness up to 1year, and in the fueled condition up to 24 hours.

The proposals of the chief designers for the development of a new ICBM with anoxygen-kerosene propellant and an initial weight of about 100 tons (i.e. almost threetimes less than that of the R-7) were submitted to the government in April 1958. Theorder of the ministerial council to build the R-9 missile was issued on 13 May 1959 andthe designated head developer was S. P. Korolev's OKB-1. The flight tests of a missilewere conducted at the Baikonur cosmodrome. They were first carried out on 09 April1961 at a modified launch complex, then proceeded on an experimental ground-launchlaunch complex "Desna-N" until 14 February 1963. The test of the ground-launchedversion were finished on the "Valley" battle complexes and tests of the silo-launchedversion were finished on 02 February 1964. Due to serious engine problems 15 of thefirst 32 launches terminated in emergencies. In total 54 missile tests were carried out.

The SS-8 system was deployed at both soft and hard sites.On July 21, 1965 thedeployment of SS-8 missiles began. They were capable of ground and silo-launch fromthe "Valley" and "Desna-V" launch complexes. The "Desna-N" complex was notdeployed, since launch preparation took at least 2 hours. According to Westernassessments, the reaction time for soft systems in the normal readiness condition was oneto three hours, and for hard systems from 30 to 45 minutes. Because of the cryogenicoxidizer, the allowable hold time in the highest degree of pre-launch alert (reaction timeequals five to ten minutes) was assessed at about one hour.

According to Western intelligence, soft-site initial operational capability was achieved inNovember, 1963, and hard-site IOC followed in April 1964. In fact, Russian sourcessuggest that the first missile regiments equipped with missiles R-9A, were put on alert inDecember 1964 (4 regiments with surface-based missiles and one regiment with missilesof silo basing). The maximum operational launcher inventory of 23 was reached in 1963and 1964. Soft-site phase out began in 1971, and in 1976 the R-9A missiles were phasedout entirely.

SpecificationsDIA SS-8 SS-8 SS-8

NATO Sasin Sasin Sasin

Bilateral

Service R-9, R-9A, R-9B

OKB/Industry 8K75, 8K75A, 8K76

Design Bureau OKB -1 (Acad.S. P. Korolev)

OKB -1 (Acad.S. P. Korolev)

OKB -1 (Acad.S. P. Korolev)

Approved 5/13/1959

Years of R&D


1959 - 1961 -1965

First Flight Test 4/9/61 02-22-63

IOC Dec. 14/15,1964,

DeploymentDate

7/21/1965

Type ofWarhead

Single Single Single

Warheads 1 1 1

Yield (Mt) 1.65, 2.1-2.5 1.65 - 3.0 -5.0

Payload (t) 1.7- 2.2, 1.1,-1.65 -2.1

Total length (m) 24.18, 24.227


MissileDiameter (m)

2.68 2.68 2.68

Launch Weight(t)

81.0 - 82.0 81.0 - 82.0 81.0 - 82.0

Fuel Weight (t) 1st. 81.0 - 25.4 =55.6, 2nd.18.2 -15.3= 2.9 ?Total (71.1)

1st. 81.0 - 25.4 =55.6, 2nd.18.2 -15.3= 2.9 ?Total (71.1)

1st. 81.0 - 25.4 =55.6, 2nd.18.2 -15.3= 2.9 ?Total (71.1)

Range (km) 12,000 -13,000 16,000 -12,500

CEP (m)(RussianSources)

3,000 - 3,500

CEP (m)WesternSources)

1,800 - 2,000

Number of Stages 2Canister length (m) N/A

Canister length w/o

Front meters (m)

N/A

Canister diameter (m) N/ABooster guidance system Radio/Inertial autonomous

1st stage 2nd stageLength (m) 14.79 9.40Body diameter (m) 2.68 2.68Fueled weight (t) (71.1) totalDry weight (t) 7.2 3.1 9.3 - 9.9 totalEngine Designation RD-111, 8D716 RD-0106 (RO-9) 8D715Design Bureau Glushko OKB-456 Kosberg OKB-154Years of R&D 1959-1962 1959-1961Propellants Liquid LiquidFuel T-1, Kerosene T-1, KeroseneOxidizer Liquid Oxygen Liquid OxygenBurning time (sec.) 104-105 105 & 108 VerniersThrust SeaLevel/Vacuum (Tonnes)

141.24 -143.3 /

162.8 -163 -166

30.5 -30.62 -31.0 - 31.5 Vacuum

Specific Impulse SeaLevel/vacuum (sec.)

270.4 - 274 -275 /

310 -317

330 Vacuum

Basing Mode Ground and siloHardnessLaunching Technique Hot launchDeployed boosters 0Test BoostersWarheads Deployed 0Training LaunchersSpace Booster Variant N/A

Deployment Sites

START Locale US-DesignationKozel=sk Kozelsk

http://www.fas.org/nuke/guide/russia/icbm/ru_nuke_icbm_ss08_01.jpg

GR-1 / SS-X-10 SCRAGThe 1961 Global Rocket 1 (GR-1) requirement chartered a competition for thedevelopment of a Fractional Orbital Bombardment System. Yangel offered the R-36.Korolev proposed the 8K713, which was cancelled in 1964 prior to flight testing due toengine delays. Chelomei proposed the UR-200, which was cancelled following theOctober 1964 ouster of downfall of Khrushchev, who had been Chelomey's politicalpatron.

The GR-1 (8K713) Fractional Orbital Bombardment System [FOBS] intended toovercome the ABM-system that the USA was about to deploy in order to protect selectiveICBM deployment sites from a Soviet nuclear strike. The GR-1 orbital missile wassupposed to be capable of placing a warhead in a low earth orbit of 150 km, brakingduring its trajectory and targeting the warhead on the earth surface. Its target accuracywas 5 km along range and 3 km on azimuth deviation at unlimited range.

The three-stage liquid cryogenic propellant missile had a launch weight of 117 tons andcarried a single warhead with a yield of 2.2 MT. Since the R-9A was reaching the end oftheir service, it was planned that the GR-1 missile would use the same launching sites asthe R-9A missile.

The design of a missile that could serve both as a ballistic and an orbital missile began atKorolev's OKB-1 in 1961. The development of the GR-1 missile was officiallyauthorized by the Ministerial Council on 24 September 1962. Further development of theGR-1 missile was halted in 1964 in preference of the orbital R-36 missile (8K69).

Although the GR-1 missile had not been flight tested, it was paraded in Red Square anddid receive the US-designation SS-X-10 SCRAG. It was displayed in a 1965 parade,where it was described as a sister to the manned spacecraft launch vehicles. This missilewas correctly identified as being a FOBS configuration, although open sources at the timeevidently assumed that the FOBS parading in Red Square and the FOBS undergoingflight tests were the same system. In fact, the initial FOBS flight tests were conducted bythe competing UR-200 missile, and subsequent orgital tests by a variant of the R-36. It isunclear when US intelligence understood that the parade missile and the test missile weretwo different systems.

SpecificationsDIA

NATO Scrag

Bilateral

Service GR-1

OKB/Industry 8K713

Design Bureau OKB-1 (Acad. S. P. Korolev)

Approved 9/24/1962

Years of R&D

Engineering and Testing

First Flight Test 10/20/64 One to eight flightssuggested. All missed through1967 by U.S. Intelligence.

IOC Canceled 11/19/68

Deployment Date Not deployed

Type of Warhead Single/Orbital

Warheads 1

Yield 2.2

Payload 2.5

Total length 35.305

Total length w/o warhead 33.9

Missile Diameter (m) 2.85

Launch Weight (t) 116

Fuel Weight (t) 1st 116 -38.94, = 77.06

2nd 30.76 -10.24,= 20.52

3rd 7.44 -3.84 = 3.6

Total 101.18

Dry weight total (t) 14.82 - 2.5 payload mass = 12.32

Range (km) 12,000/40,000

CEP (m) (Russian Sources) 5,000/3,000

CEP (m) (Western Sources)Number of Stages 3Canister length (m) N/ACanister length w/o

front meters (m)

N/A

Canister diameter (m) N/ABooster guidance system Inertial autonomous

1st stage 2nd stage 3rd stage

Length (m) 18.0 7.7 6.4Body diameter (m) 2.85 2.7 2.35Fueled weight (t) 77.06 20.52 3.6

Dry weight (t) 8.18 2.8 1.34Engine Designation NK-9 (8D717) NK-9V /

(NK-19)

Derivation of the

S1.5400, 8D726Design Bureau Acad. N. D.

Kuznetsov,OKB-276

Acad. N. D.Kuznetsov,OKB-276

Acad. A.M.

Isayev,

OKB-2Years of R &D 1959-1965 1959-1965 1962-1965

Propellants Liquid Liquid LiquidLiquid Fuel RG-1, Kerosene RG-1, Kerosene RG-1,

KeroseneOxidizer Oxygen Oxygen Oxygen

Burning time (sec.)Thrust Sea

Level/Vacuum (tonnes)4 x 36.5=147/ 4x 38=152

44.6-45-46.1 6.87-8.5

Specific ImpulseLevel/Vacuum (sec.)

285 - 327 330 - 341 344

Basing Mode SiloHardness

Launching Technique Hot LaunchDeployed boosters 0

Test Boosters 1-8?Warheads Deployed 0

Deployment Sites 0Training Launchers 0

Space Booster Variant Yes GR-1

http://www.fas.org/nuke/guide/russia/icbm/gr-1_1.jpg

http://www.fas.org/nuke/guide/russia/icbm/gr-1_2.jpg

R-16 / SS-7 SADDLERThe R-16/SS-7 intercontinental ballistic missile is a two-stage, tandem, storable liquid-propellant missile capable of delivering a single 3500 lb reentry vehicle to a maximumoperational range of 7000 nm,or a 4200 lb reentry vehicle to a range of 6000 nm. The SS-7 is about 100 feet long and 10 feet in diameter. The missile guidance system was inertialwith a CEP estimated by the West at 1.0-1.25 nm.

The propulsion system of the first stage consists of three motors with two combustionchambers (similar to those used on the R-14 missile) and a four-chamber control engine.The pivoted combustion chambers of the control engine were placed on an externalsurface under fairings, which also served as aerodynamic stabilizers. The second stagehad a two combustion chamber engine with that had a greater nozzle as the first stage anda four-chamber control engine. Dedicated retrorockets were used to separate the sustainerstages and the warhead. A novel and more reliable autonomous guidance control systemthat was protected from radio-jamming was designed for this missile.

Three versions of the R-16 missile were developed differing with regard to the numberand the yield of warheads and the ensuing maximum range. Four variants of the reentryvehicle were detected by Western intelligence during the R&D program. Only the Mod 2(ballistic coefficient equals 700 lb per sq ft; yield assesed by the West to be 2.0 to 3.5MT) and the Mod 3 (ballistic coefficient equals 850 lb per sq ft; yield assessed by theWest to be 3.0 to 5.0 MT) were deployed extensively.

The order to build an intercontinental ballistic missile designated as R-16 (8K64) wasapproved by the ministerial Council of the USSR on 17 December 1956. The developerwas Yangel's OKB-586.

Test flights were to be started on 24 October 1960 at the Baikonur cosmodrome.However during preparation of a fueled rocket to resume a delayed launch there was anaccidental engine ignition of the second stage. As a consequence of the ensuing explosionand fire about 100 people were killed, including Strategic Rocket Forces MarshalMitrofan Nedelin. The incident was shrouded in mystery, and was first described in [notentirely correct] detail by James Oberg's books "Red Star in Orbit" and "UncoveringSoviet Disasters." Initially it was thought in the West that the disaster was associated witha failed attempt to launch a probe to Mars, and only subsequently was it understood to bea test of a new ICBM.

Flight tests resumed on 02 February 1961, and the SS-7's first successful flight testoccurred on 02 April 1961. By late 1961 the first R-16 missile regiment was put on alert,though the system was not believed by Western intelligence to be operational untilJanuary 1962. The missile was fired from the surface launch complex "Desna-N", whichconsisted of two open launchers, a command center and a fuel depot.

In May 1960 the development of a missile designated as R-16U and its correspondingsilo launch complex "Desna-V" began. The R-16U was to become the first silo launchedICBM but it also had a surface-launch capability. The launch complex consisted of threesilos located in a straight line 60 meters away from each other, along with fourunderground command centers and fuel depots. The silo launchers had a depth of 45.6 m,a diameter of 8.3 m and a door diameter of 4.64 m.

The flight tests of the ground launched R-16U were conducted from 10 October 1961through February 1962. The flight tests of the silo launched version began in January,1962. The first surface-launched missile firing was conducted on 13 July1962, and thisversion was initially deployed on 15 June 1963. The silo launched version becameoperational on 15 July 1963 (simultaneously with the R-12U and R-14U missiles). Thefirst three ground based R-16 regiments were put on alert on 01 November 1961, whilethe first regiment with silo based P-16U missiles was put on alert on 05 February 1963.

The system was deployed in both soft and hard sites. Between 1961 and 1965 a total of186 mostly sufrace-based R-16 and R-16U were deployed. The SS-7 reaction time in thenormal readiness condition is one to three hours for soft sites and five to fifteen minutesfor hard sites. The allowable hold time in the highest alert condition (reaction time equalsthree to five minutes) is many hours for soft sites and days for hard sites. Maximumoperational launcher inventory occurred in 1965 with some phase-out of both soft andhard sites occurring in 1971. Both missiles were phased out in 1976.

SpecificationsMod-1 Mod-2 Mod-3

DIA SS-7 SS-7 SS-7

NATO Saddler Saddler Saddler

Bilateral R-16 R-16 R-16

Service R-16(U) 1 R-16(U)1 R-16(U)

OKB/Industry 8K64(U) 8K64(U) 8K64(U)

Design Bureau OKB-586

(Acad. M. K.Yangel)

OKB-586

(Acad. M. K.Yangel)

OKB-586

(Acad. M. K.Yangel)

Approved 12/17/1956 05/30/1960, 04/27/1961

Years of R&D 1956-1961

Engineeringand Testing

1961-1962 1961-1963

First Flight Test 10/24/1960 10/10/1961 07/13/1962

failure

02/02/1961success

11/22/1963

IOC 1961 1963

DeploymentDate

11/__ /1961 02/05/1963,6/15/1963 2

Type ofWarhead

Single Single Single

Warheads 1 1 1

Yield (Mt) 3, 5-6 3, 5-6 3, 5-6

Payload (t) 1.475-1.5 2.175-2.2 2.175-2.2

Total length(m)

32.4 –30.44/31

30.44/31 34.3

Total length

w/o warhead(m)

MissileDiameter (m)

3 3 3

Launch Weight(t)

140.6, 141.2 146.6 148

Fuel Weight (t) 130 130 130

Range (km) 13,000,

10,500 -11,000

11,000 -13,000 10,500


2,700 2,700 2,700

CEP (m)(WesternSources)

2,750-2,800 2,750-2,800 2,750-2,800

Basing Mode Soft sitegroundbased

Silo based Silo based

(12)Number of Stages 2Canister length w/o front meters (m) N/A

Canister diameter (m) Canister length (m)

Booster guidance system Inertial autonomous1st stage 2nd stage

Length (m) 14.5, 16.8 10.8 ~12.7Body diameter (m) 3.0 2.4Fueled weight (t) Total 130.0Dry weight (t) Total 10.6Engine Designation Acad. V. P. Glushko,

RD-218 (8D712)Acad. V. P. Glushko,

RD-219 (8D713)Configuration Cluster of three engines

+ Yuzhnoy Vernierengine

RD – 68 / RD-851

One engine + Yuzhnoy

Vernier engine

RD – 69 / RD-852Design Bureau Acad. V. P. Glushko

OKB-456Acad. V. P. Glushko OKB-456

Years of R&D 1958-1961 1958-1961Propellants Liquid Storable Liquid StorableFuel UDMH (heptyl) UDMH (heptyl)Oxidizer AK-27 I, ,= 73%HNO3

+ 27% N204 (NTO),Nitrogen Tetroxideconcentrated in NitricAcid N02

AK-27 I,= 73%HNO3 + 27%N204 (NTO), Nitrogen Tetroxideconcentrated in Nitric Acid N02

Burning time (sec.) 90 125Verniers Thrust SeaLevel/Vacuum (Tonnes)

28.850 / 38.7518 4.920 - 5.0173

Main engines ThrustSea Level/Vacuum(Tonnes)

225.886 / 264.8379 90.1 Vacuum

Total Thrust SeaLevel/Vacuum (Tonnes)

254.736 -255.4/303.5897 Altitude

95.02 – 95.1173 Vacuum

Specific Impulse SeaLevel/Vacuum (sec.)

246-247/266 altitude290 Vacuum

293 Vacuum

HardnessLaunching Technique Soft site and siloDeployed boosters 0Test BoostersWarheads Deployed 0Training LaunchersSpace Booster Variant N/A

Deployment Sites

START Locale US-DesignationBershet= PermDrovyanaya Drovyanaya

ItatkaKostroma KostromaKozel=sk KozelskKrasnoyarsk GladkayaNizhniy Tagil Verknnyaya SaldaNovosibirskSvobodny SvobodnyTeykovo Teykovo

TyumenVypolzovo YedrovoYasnaya OlovyannayaYoshkar Ola Yoshkar OlaYur=ya Yurya

1. The R-16U is almost identical to the R-16b ballistic missile except for its basingmode. It was deployed on above ground soft sites as well as in silos.

2. This was the above ground soft site deployment date for the R-16U. The silobased version of the R-16U was deployed one month later.


Flight testing

First successful attempt April 2, 1961

First Mod 2 reentry vehicle October 11, 1962

First Mod 3 reentry vehicle November 22, 1962

First Mod 4 reentry vehicle August 30, 1963

Initial operational capability

Soft sites, Mod 1 reentry vehicle January 1962

Hard sites December 1962

Mod 2 reentry vehicle 1962

Mod 3 reentry vehicle 1963

Maximum operational launcher inventory 1965

Phase-out began 1971

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R-26 / "SS-8 SASIN"The R-26 (8K66) missile was one of the first strategic missiles of the second generationwith integrated fuel tanks. The development of this R-26 missile was approved on 23May 1960 and KB Yuzhnoye (OKB-586) was the leading developer. The flight-designtests were supposed to begin in December 1961, but development of the R-26 was haltedby governmental order on 09 July 1962. The reason for the suspension of thedevelopment were partly technical and lay partly in design bureau rivalries concerningthe development of a light liquid propellant missile. NPO Mashinotroyeniya (OKB-52)successfully proposed the development of the UR-100 missile known as SS-11 SEGO.

After it had been cancelled, examples of the R-26 were paraded in Red Square, andidentified in the West as the SS-8 SASIN. In fact, the entirely unrelated R-9A missile wasthe deployed SS-8 SASIN. It is not apparent at what point Western intelligenceunderstood that the missile shown on parades in Red Square in Moscow and the missilesactually deployed elsewhere in Russia were in fact different and entirely unrelatedmissiles.

SpecificationsDIA Mistaken for SS-8/R-9,R-9A

NATO Sasin mistaken for SS-8/R-9, R-9A

Bilateral N/A

Service Not deployed

OKB/Industry R-26, 8K66

Design Bureau OKB-586 (Acad. M. K. Yangel)

Approved 5/23/1960

Years of R&D

Engineering and Testing 1960-1961

First Flight Test Project canceled 07/09/1962

IOC Not operational


Type of Warhead Single

Warheads 1

Yield (Mt) 5

Payload (t) 3-3.500

Total length (m) 24.38

Total length w/o warhead (m) 22


Launch Weight (t) 85-87

Fuel Weight (t)

Range (km) 10,500-11,000-12,000

CEP (m) (Russian Sources) 1,500-2,000

CEP (m) Western Sources) ?

Number of Stages 2Canister length (m) N/ACanister length w/o

front meters (m)

N/A

Canister diameter (m) N/ABooster guidance system Inertial

1st stage 2nd stageLength (m) 11.4 10.05Body diameter (m) 2.75 2.4Fueled weight (t)Dry weight (t)Engine Designation RD-216 (11D614) Z-RD-?configuration two engine cluster 1 engineDesign Bureau Acad. V. P. Glushko

OKB-456Yuzhnoy?

Years of R & D 1958-1960Propellants Liquid Storable Liquid StorableFuel UDMH UDMHOxidizer AT=AK-27P,= Nitrogen

tetroxide, N204 in N02AT=AK-27P,= Nitrogentetroxide, N204 in N02

Burning time (sec.) 120 160Thrust SeaLevel/Vacuum (Tonnes)

151.499/177.9115 43.65 vacuum


248/291.3

Basing Mode Soft site and SiloHardnessLaunching Technique Hot launchDeployed boosters 0Test BoostersWarheads Deployed 0

Deployment SitesTraining LaunchersSpace Booster Variant N/A


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R-36 / SS-9 SCARPThe R-36 (8K67) ballistic missile, known in the west as the SS-9 SCARP, was a a two-stage, tandem, storable liquid-propellant intercontinental ballistic missile. The missile-uses an all-inertial guidance system and according to Western estimates had a CEP of 0.4to 0.5 nm.

The R-36 missile was derived from the experience gained during the development of theR-16 missile, and the first stage of the two missiles are very similar. The propulsionsystem of the first stage R-36 consisted of three open-cycle rocket engines with twocombustion chambers and a four-chambered control engine. The second stage compriseda single engine with two combustion chambers. The oxidizer and fuel tanks of the secondstage was the first Soviet ICBM to incorporated a common bulkhead, all propellant tankswere synchronously drained. Asymmetrical dimethylhydrazine and nitrogen tetroxidewere used as propellants, and during flight gaseous combustion products were used topressurize the fuel tanks. In order to increase accuracy the guidance system wasoriginally planned to encompass a combination of an autonomous inertial system andradio-control. However, the deployed missile only disposed of an autonomous, inertialguidance/control system that provided the required accuracy.

The SS-9's combination of high accuracy and yield constituted a convincing threat for theAmerican ICBMs for the first time. The SS-9 was viewed in the United States asspecifically designed to attack American Minuteman ICBM Launch Control Centers(LCCs), which initially were the "Achilles heel" of the Minuteman system, as 100 LCCscontrolled all 1,000 Minuteman missiles. However, by 1969, as a result of redundantinternetting of Minuteman silos and a backup airborne launch control system, the LCCsno longer were the "achilles heel" of Minuteman, so building one SS-9 for eachMinuteman silo required MIRVed systems.

Four payload variants were tested and deployed.

The Mod 1 featured a single reentry vehicle with a warhead with a yield estimatedby Western intelligence at 12 to 18 MT [this light version carried a warhead witha yield of 5 MT according to Russian sources]. This variant was assesed byWestern intelligence as being capable of capable of delivering a payload of12,500 lb to a range of 5500 nm.

The Mod 2 featured a single reentry vehicle with a warhead with a yield estimatedby Western intelligence at 18 to 25 MT, although this heavy version carried awarhead with a yield of 10MT according to Russian sources. This variant wasassesed by Western intelligence as being capable of capable of delivering a13,500 lb reentry vehicle a maximum operational range of 5300 nm. The largeyield, single warhead Mod 2 variant was the most extensively deployed.

The Mod 3 was a fractional-orbit, depressed-ICBM variant which combines theSS-9 first and second stages with an upper stage.

The Mod 4 variant was a three-warhead MRV which probably began as anattempt to achieve a true MIRV capability. The large throw-weight of the 8K67missiles (up to 5.8 tons) made them suitable for carrying multiple warheads. Thedesign for the R-36P missile carrying three warheads (8K67P) were conducted bythe KB Yuzhnoye (OKB-586) in November 1967. The flight-design tests werestarted in August 1968. American intelligence remained divided over whetherthese warheads were independently targetable [MIRV], or merely flying paralleltrajectories [MRV], and the issue assumed considerable importance in the contextof the debate over the deployment of the American anti-missile program.

The development of the R-36 missile in its heavy, light and orbital version began after itsapproval by the Soviet government on 16 April 1962. The leading developer was KBYuzhnoye (OKB-586). The flight-design tests of the ballistic missiles (8K67) began on28 September 1963, though the first Mod 1 flight test was not detected by Westernintelligence until 03 December 1963. The flight-design tests of the R-36 missile wereconducted at the Baikonur cosmodrome. The tests of the 8K67 ballistic missiles lastedfrom 28 September 1963 though May 1966.

The missile was placed in a silo of 41.5 meters deep with a shaft diameter of 8.3 metersand a door-diameter of 4.64 meters. Unlike the silo of the R-16U missile, the launchplatform was not rotary, and the missile was directed to its trajectory (azimuthalguidance) through an onboard command structure after it left the silo. The SS-9 wasdeployed in individual, dispersed silos hardened to withstand 500-psi overpressure from a1-MT weapon. The reaction time in the normal readiness condition is three to fiveminutes, with an unlimited hold time in that condition.

According to Western estimates, the initial operational capability for the SS-9 system,with both the Mod 1 and Mod 2 single reentry vehicle variants was reached in early 1966.According to Russian sources, the first regiment equipped with R-36 missiles was placedon alert on 05 November 1966, deployment of the 8K67 ballistic missiles began on 21July 1967, and on 26 October 1970 deployment of the multiple-warhead variant began.Between 1965 and 1973 a total of 268 launchers for the R-36 missiles were constructed.Their replacement by the MIRVed R-36P began in 1975. The R-36 ballistic missile wasphased out in 1978. The missile was ready for launch during its whole period of servicethat was originally fixed at five years but subsequently extended to 7.5 years.

SpecificationsMod-1 Mod-2 Mod-3 Mod-4

DIA SS-9 SS-9 SS-9 SS-9

NATO Scarp Scarp Scarp/FOBS

Scarp/ MRV

Bilateral

Service R-36 R-36 R-36O R-36P

OKB/Industry 8K67 8K67 8K69 8K67P

Design Bureau OKB-586(Acad. M.K. Yangel)

OKB-586(Acad. M. K.Yangel)

OKB-586(Acad. M.K. Yangel)

OKB-586(Acad. M. K.Yangel)

Approved 4/16/1962 4/16/1962 1/12/1965


1967- 1968


1963-1966 1963-1966 1965-1969

1968-1970

First Flight Test 9/23/1963 10/10/1964 12/16/65 8/23/1968

IOC 11/05/1966 1966 08/25/66 1970

Deployment Date 7/21/1967&

7/21/1967 11/19/68 10/26/1970

Type of Warhead Single Single Orbital Multiple

Warheads 1 1 1 3

Yield (Mt)(Russian Sources)

5 10 5 2.0-3.5

Yield (Mt)(Western Sources)

12-18 18-25 1-3

Payload (t) 5.825 3.95 1.7 6

Total length (m) 32.2 31.7 32.6-34.5 32.2


Missile Diameter(m)

3.0 3.0 3.0 3.0

Launch Weight (t) 183.9 179 -183.89 180 183.9

Fuel Weight (t) 166.9-170.2

166.2 166.2 166.2

Range(km) 10,200 15,200-15,500

40,000 10,200-12,000

CEP (m)(Russian Sources)

1,300-1,900

1,300-1,900 1,100 1,340-1,970

CEP (m)(Western Sources)

900-920 920 1,800-5,500

1,850

Number of Stages 2

Canister length (m)

Canister length w/o

front meters (m)

Canister diameter (m)

Booster guidance system Inertial, autonomous

1st stage 2nd stage

Length (m) 18.9 9.4

Body diameter (m) 3 3

Fueled weight (t) 121.7 -122.3 (118.7) 48.5 - 49.3

Dry weight (t) 6.4 3.7 Total =17.737

Engine Designation RD-251 (8D723) RD-252

Design Bureau Acad. V. P.Glushko(OKB-456)

Acad. V. P. Glushko(OKB-456)

Configuration Cluster of three mainengines, 6 chambers

One engine 2chambers

Configuration Yuzhnoy Yuzhnoy

RD-68M / RD-855 RD-854

One engine 4 chambers One engine 4chambers

Propellants Liquid Storable Liquid Storable

Fuel UDMH UDMH

Oxidizer AT =Nitrogen tetroxide AT=Nitrogentetroxide = NTO

Main Engines Burning time (sec.) 120, 160

Verniers Burning time (sec.) 127 163

Verniers Thrust Sea Level/Vacuum(Tonnes)

Yuzhnoy RD-68M / Yuzhnoy RD-69M /

RD-855 RD-856

29.1 5.53

Main engines Thrust SeaLevel/Vacuum (Tonnes)

241 / 270.4 96 Vacuum

Total Thrust Sea Level/Vacuum(Tonnes)

270.1 / 303 101.53 B 102.9982

Vernier Engine Specific ImpulseSea Level/Vacuum (sec.)

Vernier Engine Vernier Engine

254 / 292 280.5 Vacuum

Main Engines Specific Impulse SeaLevel/Vacuum (sec.)

Main Engines Main Engine

269 -270 /301 317.6 Vacuum

Basing Mode Silo

Hardness

Launching Technique Hot launch

Deployed boosters 0

Test Boosters

Warheads Deployed 0

Training Launchers

Space Booster Variant Yes - SL-10 / F-1-r, Mod-3, FOBS

SL-11 / F-1-m, Tsyklon - 2

SL-14 / F-2, Tsyklon - 3

Deployment Sites

START Locale US-Designation

Aleysk Aleysk

Derzhavinsk Imeni Gastello

Dombarovskiy Dombarovskiy

Kartaly Kartaly

Uzhur Uzhur

Zhangiz Tobe Zhangiz Tobe


First flight test, Mod 1 RV December 3, 1963

First flight test, Mod 2 RV prototype October 10, 1964

First flight test, Mod 3 RV 1965

Initial operational capability

Mod 1 and 2 Early 1966

Mod 4 subsystem design began Early 1967

First flight test, Mod 4 RV August 23, 1968

Initial operational capability Mod 4 RV 1971

Maximum operational launcher inventory achieved 1971



R-36O / SL-X-? FOBSIn the early 1960s, the Soviets needed a way to overcome the West's geographicadvantages (forward bases in Turkey, Europe, and Asia from which shorter rangemissiles and bombers could attack the USSR). The Soviet attempt to place missiles inCuba would have been a partial remedy. When the Cuban venture did not go as planned,they moved to other technological possibilities. The Soviets demonstrated the technologynecessary to orbit a space vehicle and then land it in a specific place with the Vostoklaunches. It was thus logical to assume they could place nuclear weapons in orbit andreturn them to Earth at any time and place. Khrushchev made this suggestion in 1961, buton 15 March 1962, as part of the rhetoric proceeding the Cuban crisis, he made yetanother, more ominous suggestion.We can launch missiles not only over the North Pole, but in the opposite direction, too. . .. Global rockets can fly from the oceans or other directions where warning facilitiescannot be installed. Given global missiles, the warning system in general has lost itsimportance. Global missiles cannot be spotted in time to prepare any measures againstthem.This statement was the first hint of a new concept called the fractional orbit bombardmentsystem (FOBS).The 1961 Global Rocket 1 (GR-1) requirement chartered a competition for thedevelopment of a Fractional Orbital Bombardment System. Yangel offered the R-36O.Korolev proposed the 8K713, which was cancelled in 1964 prior to flight testing due toengine delays. Chelomei proposed the UR-200, which was cancelled following theOctober 1964 ouster of downfall of Khrushchev, who had been Chelomey's politicalpatron.

The R-36O SS-9 Mod 3 SCARP with a modified upper stage was equipped with anorbital nose cone, which contained an instrumentation section, a single-chambered liquidpropellant retrorocket motor and a nuclear warhead. The orbital missile carried a one- tothree-megaton warhead according to Western estimates [and five megatons according tosome published Russian estimates -- about the only instance in which published Russianyield estimates are higher than published Western estimates]. Flying into low-Earth orbitgave the ICBM unlimited range and allowing it to approach the US from any direction,avoiding US northern-looking detection radars and, therefore, giving little or no warning.The reentry vehicle came down in less than one revolution, hence the "fractional" orbit.

After the failure of their first two tests in 1966, the Soviets tested their FOBS with ninelaunches between 25 January and 28 October 1967. All missions followed the samedistinct flight profile--launching in the late afternoon into an elliptical, near-polar low-Earth orbit and deorbiting over the Soviet landmass before one complete orbit. Thisprofile allowed the Soviets to monitor the deorbit, reentry, and impact. US plannersviewed FOBS as a pathfinder system intended to precede a conventional ICBM attack.The FOBS would circumvent the existing US ballistic missile early warning radars andhit SAC airfields before the bombers could take off. FOBS could destroy ABM radars,disrupt US retaliatory capability, destroy command posts, the White House, and the

command and control network. But, due to its limited accuracy and payload, FOBS wasineffective against hardened targets.Under the 1967 Outer Space Treaty, the Soviets could orbit everything but the nuclearwarhead. Some US Senators were concerned with the Soviet FOBS development whichfollowed on ratification of the Outer Space Treaty. The Soviets could, without treatyviolation, deploy the weapons system minus the warheads.By 1968 the Soviets' FOBS program settled into a two-flight-per-year pattern whichindicated an operational status, although they only deployed FOBS in 18 silos. Littleattention was paid to these events in the United States, because they occurred during thenational election and at a time when Vietnam had all the headlines. At that time itremained unclear to US intelligence whether the Soviets were developing FOBS, orballistic missiles with depressed trajectories and deboost capabilities.

The orbital missile 8K69 was initially deployed on 19 November 1968, and the firstregiment with the R-36 orbital missiles was put on alert on 25 August 1969. The orbitalmissile was phased out in January 1983 in compliance with the SALT-2 treaty, whichprohibited the deployment of these missiles.

SpecificationsMod-3

DIA SS-9

NATO Scarp/ FOBS

Bilateral 16935

Service R-36O

OKB/Industry 8K69


Approved 1/12/1965



First Flight Test 12/16/65

IOC 08/25/66

Deployment Date 11/19/68

Type of Warhead Orbital

Warheads 1

Yield (Mt) 5

(Russian Sources)

Yield (Mt) 1-3

(Western Sources)

Payload (t) 1.7

Total length (m) 32.6-34.5

Total length w/o warhead (m) 21543

Missile Diameter (m) 3


Fuel Weight (t) 166.2

Range(km) 40,000

CEP (m) 1,100

(Russian Sources)

CEP (m) 1,800-5,500

(Western Sources)

1st stage 2nd stage 3rd.Stage FOBS/OR-36

Length (m) 18.9 9.4 8.3

Body diameter(m)

3.0 3.0 4.64

Fueled weight(t)

121.7 -122.3(118.7)

48.5 - 49.3

Dry weight (t) 6.4 3.7 Total =17.737

EngineDesignation

RD-251(8D723)

RD-252

Design Bureau Acad. V.P.Glushko(OKB-456)

Acad. V. P. Glushko

(OKB-456)

Yuzhnoy

Configuration Cluster ofthree mainengines, 6chambers

One engine

2 chambers

One engine

1 chamber

Configuration Yuzhnoy

RD-68M / RD-

Yuzhnoy

855

One engine 4chambers

RD-854

One engine 4

chambers

Propellants LiquidStorable

Liquid Storable Liquid Storable

Fuel UDMH UDMH UDMH

Oxidizer AT =Nitrogentetroxide

AT=Nitrogen tetroxide= NTO

AT= NTO

Main EnginesBurning time(sec.)

120, 160 70 sec.

VerniersBurning time(sec.)

127 163

Verniers ThrustSeaLevel/Vacuum(Tonnes)

Yuzhnoy RD-68M /

RD-855

29.1

Yuzhnoy RD-69M /

RD-856

5.53

Main enginesThrust SeaLevel/Vacuum(Tonnes)

241 / 270.4 96 Vacuum 7.7 Vac.

Total ThrustSeaLevel/Vacuum(Tonnes)

270.1 / 303 101.53 102.9982

Vernier EngineSpecificImpulse SeaLevel/Vacuum(sec.)

VernierEngine

254 / 292

Vernier Engine

280.5 Vacuum

Main EnginesSpecificImpulse Sea

Main Engines

269 -270

Main Engine

317.6 Vacuum

Level/Vacuum(sec.)

/301

R-36M / SS-18 SATANThe R-36m / SS-18 intercontinental ballistic missile is a large, two-stage, tandem,storable liquid-propellant inertial guided missile developed to replace the SS-9 ICBM.Housed in hard silos, the highly accurate fourth generation SS-18 ICBM is larger than thePeacekeeper, the most modern deployed US ICBM. The SS-18 opened a "window ofvulnerability" of Minuteman silos (at 300 psi) by 1975, so that some analysts aregued thatfew Minuteman could be expected to survive a Soviet attack by 1980. The "window ofvulnerability" of U.S. land based strategic missiles opened on schedule, and became oneof the major issues in U.S. strategic debates in the late 1970s and early 1980s.

The R-36M (15A14) was a two-stage missile capable of carrying several differentwarheads. The basic design is similar to the R-36 missile modified to include advancedtechnologies and more powerful engines. This missile, using dinitrogen tetroxide (N2O4)and heptyl (a UDMH [unsymmetrical dimethyl hydrazine] compound) has a first stagepowered by a 460-ton-thrust motor with four combustion chambers, and the second by asingle-chamber 77-ton-thrust motor. The first stage uses four closed-cycle singlechambered rocket motors. The second stage was equipped with a closed-cycle singlechambered sustainer motor and an open-cycle four chambered control motor. The secondstage sustainer is built into the fuel tank's toroidal cavity. The flight control of the firststage was conducted through gimbaled sustainers. The sustainers used asymmetricaldimethylhydrazine and nitrogen tetraoxide. The missile was equipped with anautonomous inertial command structure and an onboard digital computer.

The R-36M used a gas-dynamic method for the first and second stages whereby specialports are opened through which the propellant tanks are pressurized. This obviated theneed for the use of pressurant gases from tanks and the so-called chemical tankspressurization (by injecting small amounts of fuel in the oxidizer tank and oxidizer intothe fuel tank). The improved design and more effective engines allowed an increase inthe total liftoff weight from 183 tons to 209.6 ton and the throw weight from 5.8 tons to8.8 tons, while maintaining the overall dimensions of its predecessor missile.

The SS-18 was deployed in modified SS-9 silos, and employed a cold-launch techniquewith the missile being ejected from the silo prior to main engine ignition. The rocket wasplaced in a transport-launch canister made of fiberglass composites. The container wasplaced into an adapted R-36 silo. The specially hardened silo was 39 meters deep and hada diameter of 5.9 m. Prior to main engine ignition the missile was ejected from thecontainer with the help of a solid-propellant gas generator located in the lower unit of thetransport-launch canister. According to Western estimates, the SS-18 was deployed in asilo with a hardness of at least 4,000 psi (281 kg/sq. cm; 287 bar), and possibly as high as6,000 psi (422 kg/sq. cm; 430 bar).

The development of the two stage heavy liquid-propellant ICBM R-36M intended toreplace the R-36 SS-9 Scarp was accepted on 02 September 1969. The preliminary designwas completed in December 1969 by the design bureau was KB Yuzhnoye. The system

was designed by the M. K. Yangel OKB Yuzhnoye at Dnepropetrovsk (Ukraine) during1966-1972, with testing beginning in November 1972. It was deployed in January 1975,and integrated with the weapons arsenal in December 1975.

There are six variants that have been deployed, while others were tested but notdeployed:

SS-18 Mod 1 - R-36M The SS-18 Mod 1 carried a single large reentry vehicle,with a warhead yield of 18 to 25 MT, a distance of about 6,000 nm. In January1971 pop-up tests, began during which the mortar launch was perfected. Theactual flight tests for the single-RV Mod-1 began on 21 February 1973, thoughsome sources suggest that testing began in October 1972. The testing phase of theR-36M with various different types of warheads was finished in October 1975 andon 30 December 1975 deployment began [though some Western sources suggestthat an initial operational capability was reached in early 1975]. A total of 56were deployed by 1977, though all were replaced by Mod 3 or Mod 4 missiles by1984. These high-yield weapons were assessed in the West as possibly developedto attack American Minuteman ICBM launch control centers.

SS-18 Mod 2 - R-36M The SS-18 Mod 2 included a post-boost vehicle and up toeight reentry vehicles, each with a warhead yield estimated at between 0.5 to 1.5MT, with a range capability of about 5,500 nm. The MIRVs were placed in pairs,and a post boost vehicle with a command structure and a propulsion system werecontained in the nose cone of the R-36M. The flight tests of the MIRVed Mod-2began in September 1973 [though some Western sources suggest that the initialflight test of the Mod 2 MIRV version occurred in August 1973], with IOC in1975. Approximately 132 were deployed by 1978, but the post-boost vehicledesign was seriously flawed, and the Mod 2 missiles were all replaced by the Mod4 variant by 1983.

SS-18 Mod 2x - R-36M Between July 1978 and August 1980 a MIRVed missilewith an improved nose cone was tested but not deployed. The fact of the existenceof this system is reported by Russian sources, but not attested by unclassifiedWestern literature.

SS-18 Mod 3 - R-36UTTh The SS-18 Mod 3 carried a single large reentryvehicle that was an improved version of the SS-18 Mod-1. On 16 August 1976, afew months after the R-36M entered service, the development of an improvedmodification of the R-36M (15A14) and MR UR-100 (15A15) was approved.This missile subsequently received the designation R-36M UTTh (15A18) andwas developed by KB Yuzhnoye (OKB-586) through December 1976. Itsincreasing accuracy made it possible to reduce the yield of the warheads. The R-36M UTTh was capable of carrying two different nose cones. The version with adivided nose cone [Mod-4] allowed an increase the numbers of warheads from 8up to 10 and the single-RV version [Mod-3] had a maximum range of up to16,000 km. The flight-design tests of the R-36M UTTh began on 31 October1977. On 29 November 1979 deployment of the SS-18 Mod-3 with a singlereentry vehicle carrying a warhead with a yield of 24-25 MT began. The P-

36MUTTh was introduced into the inventory on 17 December 1979. A total of 24were deployed in 1977, and all were replaced by the Mod 4 variant by 1984.

SS-18 Mod 4 - R-36UTTh The SS-18 Mod 4 carries at least 10 MIRVs and wasprobably designed to attack and destroy ICBMs and other hardened targets in theUS. According to some Western estimates, evidence suggested that the Mod 4may be capable of carrying as many as 14 RVs [this may reflect observation ofthe deployment of countermeasures intended to overcome a ballistic missiledefense, or to confuse American attack characterization systems]. In November1979 the flight tests of the MIRVed missile were completed. The first threeregiments were put on alert on 18 September 1979. During 1980 a total of 120SS-18 Mod 4 missiles were deployed, replacing the last remaining R-36 missiles.In 1982-1983 the remaining R-36M missiles were also replaced with the new R-36M UTTh and the total number of deployed missiles reached a maximumoperational launcher reached 308, ceiling established in the SALT-1 treaty. TheSS-18 Mod 4 force had the estimated capability to destroy 65 to 80 percent of USICBM silos using two nuclear warheads against each. Even after this type ofattack, it was estimated that more than 1,000 SS-18 warheads would be availablefor further strikes against targets in the US. After 1988 the SS-18 Mod 4s werepartially replaced by the new R-36M2 "Voivode".

SS-18 Mod 5 - R-36M2 "Voivode" The newer, more accurate version (the SS-18Mod 5) placed in converted silos allowed the SS-18 to remain the bulwark of theSRF's hard-target-kill capability. The Mod 5 carries 10 MIRVs, each having ahigher yield than the Mod 4 warheads. The Mod-5 warheads have nearly twice theyield of the Mod-4 (approximately 750 kt to 1 megaton) according to Westernestimates, though Russian sources suggest a yield of 550-750 Kt each. Theincrease in the Mod 5's warhead yield, along with improved accuracy, would,under the START treaty, help allow the Russians to maintain their hard-target-killwartime requirements even with the 50 percent cut in heavy ICBMs the STARTagreement required. The technical proposals to build a modernized heavy ICBMwere made in June 1979. The missile subsequently received the designation R-36M2 "Voivode" and the industrial index number 15A18M. The design of the R-36 M2 "Voivode" was completed in June 1982. The R-36M2 disposed of a seriesof new engineering features. The engine of the second stage is completely built inthe fuel tank (earlier this was only used on SLBMs) and the design of thetransport-launching canister was altered. Unlike the R-36M, the 10 warheads onthe post-boost vehicle are located on a special frame in two circles. The flighttests of the R-36M2 equipped with 10 MIRVs began in March 1986 and werecompleted in March 1988. The first regiment with these missiles was put on alerton 30 July 1988 and was deployed on 11 August 1988.

SS-18 Mod 6 - R-36M2 "Voivode" The flight tests of a the R-36M2 missile(Mod-6) carrying a single warhead with a yield of 20 MT were completed inSeptember 1989 and deployment began in August 1991.

The only deployed versions of the SS-18 are the R-36M UTTh and R-36M2. In 1997there were 186 deployed launchers for of these missiles in Russia. The dismantling of104 launchers located in Kazakhstan was completed in September 1996.

The Reagan and Bush administrations respected the SS-18 to such a degree that theymade it the main focus of their arms control initiatives. The START II Treaty specificallybanned land-based MIRV systems, in part, because of the threat the SS-18 posed to thebalance of power. It was seen as a first-strike weapon and a very destabilizing presence inthe bilateral relationship.

US negotiators allowed the Russian Federation to retain 90 of the SS-18 silos. Aftercomplying with the START II silo conversion protocol, the Russian Rocket Forces willbe permitted to replace 90 of the SS-18s with a smaller, single-warhead missile. Theprotocol requires Russia to place a 2.9-meter restrictive ring near the top of the retainedSS-18 silos and to fill the bottom five meters of the silos with concrete. These measuresmake the silos too small to hold an SS-18.

The Nunn-Lugar program is assisting in the reduction of the SS-18 missile threat to theUnited States. The Russian Federation must eliminate 100 SS-18s by December 2001 andan additional 154 SS-18s by January 2003. In recent years, Nunn-Lugar has played a rolein SS-18 dismantlement. It provided the equipment necessary to help destroy the missiles.A total of 204 of these missiles were deployed on Russian territory and 104 inKazakhstan. The elimination base at Surovatikha, near Nijny-Novgorod, destroyed 32missiles in 1993 with the remaining 44 destroyed in 1994.

The SS-18 was manufactured in Ukraine, while Russian enterprises provide maintenancefor SS-18s which are currently in inventory. Manufacturing of SS-18s in Russia would beexpensive, and could require 5 to 7 years of design work to begin at least tests at a cost of8-10 billion rubles.

SpecificationsMod Mod-1 Mod-2 Mod-3 Mod-4 Mod-5 Mod-6

DIA SS-18 SS-18 SS-18 SS-18 SS-18 SS-18

NATO Satan Satan Satan Satan Satan Satan

Bilateral RS-20A RS-20A RS-20A RS-20B RS-20V RS-20V

Service R-36M R-36M R-36M

UTTkh

R-36MU

UTTkh

R-36M2 R-36M2

OKB/Industry 15A14 15A14 15A14 15A18 15A18M 15A18M

Design

Bureau

OKB-586

Acad. V.F. Utkin

OKB-586Acad. V.F. Utkin

OKB-586

Acad. V.F. Utkin

OKB-586

Acad. V.F. Utkin

OKB-586Acad.V. F.Utkin

OKB-586Acad.V. F.Utkin

Approved 9/2/1969 9/2/1969 9/2/1969 8/16/1977 8/9/83 6/1979

?12/17/

1980 ?

Years ofR&D

1969-1973

1969-1973

12/ 76 -78

1983-1988

1979-1982


1973-1974

1973-1975

1978-1980

1977-1979

1986-88 1986-1990

First FlightTest

1 / / 721St.failure

2/21/1973success 1& anotherderivation11-29-79

9/ /73,

08/ /73 &anotherderivation

07/ /78

7/ /1978 7/31/1977

or 10-31-1977

3/21/86

twofailuresin theflighttestprogram

1986

IOC 12 /25 /1974

1975 1980 9/1979 ?11-27-1979?

12/1988 1990

DeploymentDate

12/30/

1975

12/30/

1975 or11/20/78

11/29/

1979

12/17/

1979, or1980?

12/1988 9/1991

Type of

Warhead

Single MIRV Single MIRV MIRV Single

Warheads 1 8 1 10 10 1

Yield (Mt)Russiansources

18-20 0.5-1.3 24-25 0.55 0.55-0.75

20

Yield (Mt)Westernsources

18-25 0.6-1.5 18-25 0.75-1.0

Payload (t) 7.2 7.2 - 8.8 7.2 - 8.8 8.8 8.8 8.8

Total length(m)

33.6 33.6 33.6 34.3 37.25 36.3

Total lengthw/o warhead(m)

28.5 28.5 28.5 28.5 -29.25

29.25 29.25

Missile 3.0 3.0 3.0 3.0 3.0 3.0

Diameter (m)

LaunchWeight (t)

209.6 -210

209.6 -210

209.6 -210

211.1 211.1 211.1

Fuel Weight(t)

188 188 188 188 188 188

Range (km) 11200 9250-10200

16.000 16000

11500

11000

15,000

16000

CEP (m)

RussianSources

1000 1000 1000 920 500 500

CEP (m)WesternSources

400-550 400-500 350 220-320 250 ?250

Number of Stages 2

Canister length (m) 27.9

Canister diameter (m) 3.5


1st stage 2nd stage

Length (m) 22.3 7.0

Body diameter (m) 3.0 3.0

Fueled weight (t) Total 161.5

Dry weight (t) Total 48.1 ? 48.5

Engine Designation RD-263 x 4 = RD-264(11D119) for the

R-36M

RD-0228 = RD-0229 one mainengine and RD-0230 fourverniers for the R-36M

Engine Designation RD-273 / RD-274 forthe R-36MU

RD-0230 verniers for the R-36M

Engine Designation N/A RD-0255 = RD-0256 one mainengine & RD-0257 four verniersfor the R-36M2.

Design Bureau Acad. V. P. Glushko(OKB-456)

Acad. S. A. Kosberg

(OKB-154)

Configuration Four RD-263?sEngines = RD-264

1 Main Engine + 4 Verniers

Years Of R & D 1969-1973 = RD-263x 4=RD-264

1967-1975 = RD-0228 / RD-0229

Years Of R & D 1975-1980 = RD-273 1967-1975 = RD-0230

Years Of R & D 1983-1989 = RD-0255

1983-1987 = RD-0256

1983-1987 = RD-0257

Propellants Liquid Storable Liquid Storable

Fuel UDMH UDMH

Oxidizer Nitrogen Tetraoxide Nitrogen Tetraoxide

Burn Time (sec.)

Main Engines ThrustSea Level/Vacuum(Tonnes)

424 / 450-461 77

Verniers Engine ThrustSea Level/Vacuum(Tonnes)

N/A ?

Main Engines SpecificImpulse Sea Level/Vacuum (sec.)

293 / 312-318

MIRV Bus Third StageEngine Designation forthe R-36M2

RD-869

Design Bureau (Bus) Yuzhnoy SKB

Years Of R & D (Bus) 1983-1985

Propellants (Bus) Liquid Storable

Fuel (Bus) UDMH

Oxidizer (Bus) Nitrogen Tetraoxide

Thrust Vacuum(Tonnes)

2.087- 0.875

Engines SpecificImpulse (sec.)

313 ? 302.3

Burn Time (sec.) 700

Basing Mode Silo

Hardness

Launching Technique Cold and Solid motor

Deployed boosters

Test Boosters

Warheads Deployed

Training Launchers

Space Booster Variant Yes- SL-21?/Dnipr SS-18 derivation

Deployment Sites


Aleysk in Altai (30) Aleysk

Derzhavinsk near Akmolinsk (52) Imeni Gastello

Dombarovsky-3 near Orenbourg (64) Dombarovskiy

Kartaly-6 near Chelyabinsk (46) Kartaly

Uzhur-4 near Krasnoyarsk (64) Uzhur

Zhangiz-Tobe near Seminpalatinsk(52)

Zhangiz Tobe

http://www.fas.org/nuke/guide/russia/facility/icbm/aleysk.htm

http://www.fas.org/nuke/guide/russia/facility/icbm/derzhavinsk.htm

http://www.fas.org/nuke/guide/russia/facility/icbm/dombarovskiy.htm

http://www.fas.org/nuke/guide/russia/facility/icbm/kartaly.htm

http://www.fas.org/nuke/guide/russia/facility/icbm/uzhur.htm

http://www.fas.org/nuke/guide/russia/facility/icbm/zhangiz_tobe.htm

SS-18/RS-20 in Launch Canister SS-18/RS-20, Stage 1 SS-18/RS-20 Missile

SS-18/RS-20Emplacement

Equipment

http://www.fas.org/nuke/guide/russia/icbm/r-36m_1.jpg

http://www.fas.org/nuke/guide/russia/icbm/ss-18-DDST8407751.jpg



http://www.fas.org/nuke/control/start1/text/image/rfphotos/rs20ss18c.jpg

http://www.fas.org/nuke/control/start1/text/image/rfphotos/rs20ss18stg1.jpg

http://www.fas.org/nuke/control/start1/text/image/rfphotos/rs20ss18ms.jpg

http://www.fas.org/nuke/control/start1/text/image/rfphotos/rs20ss18empl.jpg

R-46On 09 August 1961, Premier Nikita Khrushchev openly threatened the West with a newand terrifying weapon, the orbital H-bomb. "You do not have 50- or 100-megaton bombs,we have bombs more powerful than 100 megatons. We placed Gagarin and Titov inspace, and we can replace them with other loads that can be directed to any place onEarth." Although the US had hypothesized orbital bombs, this was the first publicindication that the Soviets were actively pursuing this course of action. Within a fewmonths, however, American analysis of the threat diminished its proportions.

SpecificationsSHB2

Mod-1 = 2Stages

SHB3

Mod-2 = 3Stages

DIA SS-LX-? "CityBuster"ICBM

SS-LX-?FOBS

NATO N/A N/A

Bilateral N/A N/A

Service

OKB/Industry (8K68) (8K68)

Design Bureau OKB-586,(Acad. M.K. Yangel)

OKB-586,(Acad. M. K.Yangel )

Approved 4/16/1962 4/16/1962


1962-1964

Engineering and Testing ModelDynamicTestingOnly

ModelDynamicTesting Only

First Flight Test N/ACanceled6/19/1964

N/ACanceled6/19/1964

IOC N/A N/A

Deployment Date N/A N/A

Type of Warhead 1 1

Warheads Single Single

Yield (Mt) 50 – 100– 150

30 – 50

Payload (t) 9,535 –12,264

Orbital10,960 –11,220

Total length (m) ~56 ~65

Total length

w/o warhead (m)

~49.87 ~59.87

Missile Diameter (m) 3.9 3.9

Launch Weight (t) 383,096 -390,400 +12,764

383,735.8350- 392,270 +12,764 or9,535

Fuel Weight (t)

Range (km) 12,000 –16,000

12,000 –16,000

CEP (m) (Russian Sources) N/A N/A

CEP (m) (Western Sources) N/A N/A

Basing Mode Hardenedlaunchcomplex

Hardenedlaunchcomplex

Number of Stages 2 3

Canister length w/o frontmeters (m)

N/A

Canister diameter (m) N/A


Length (m) 24 or (32.94 - 39.46) 10 – 10.41 ~10Body diameter (m) 4.0 - 3.9 4.0 - 3.9 ~4.0 - 3.9Fueled weight (t) 200,334 +77,052 =

277,38662,477+24,039 =86,516

1,639 + 0.603= 1639.603

Dry weight (t) 13,869 4,325 0.232

Engine Designation RD-253(11D48)(11D43)

RD-254 KTDU-5A

Configuration Cluster of FourEngines

One Engine One Engine

Design Bureau OKB-456, Acad. V. P.Glushko

OKB-456,Acad. V. P.Glushko

OKB-2, Acad.A. M. Isayev

Years of R&D 1961-1965 1962-1964 1961 – 1965Propellants Liquid Liquid LiquidFuel UDMH UDMH TG-02 = A

Amine basedfuel

Oxidizer Nitrogen Tetroxide NitrogenTetroxide

AK-27I = 73%HNO3 +27%N204 =NitrogenTetroxideconcentrated inNitric Acid

Burning time (sec.) 130 159.7 100.3+11.6+22.5=

134.4 totalVerniers Thrust SeaLevel/Vacuum(Tonnes)

N/A ? ?


148.8884 - 150.25 /166.7347

174.7 4.638

Total Thrust SeaLevel/Vacuum(Tonnes)

4 x 150.25 = 601.0 174.7 4.638


284.9/310.0 329.89 277.78

Hardness N/ALaunching Technique Hot launchDeployed boosters N/ATest Boosters N/AWarheads Deployed N/ATraining Launchers N/ASpace Booster Variant SL-LX-? SHB-2 & SHB-3 not developed

Deployment Sites

START Locale US-DesignationN/A N/A

UR-100 / SS-11 SEGOThe development of the massively deployed UR-100/SS-11 liquid propellant light ICBMwas the centerpiece of a major Soviet effort to reach numerical strategic parity with theUSA. The SS-ll was the Soviet counterpart of the US Minuteman system in quantity, sizeand purpose. Initially deployed with a single warhead [with a yield of 1.1 MT accordingto Russian sources, or 0.6 to 1.2 MT according to Western reports] and a low accuracy [aCEP of 1.4 km according to Russian sources], the missile could be used only against softtargets.

The UR-100 intercontinental ballistic missile is a two-stage, tandem, storable liquid-propellant missile. It is about 64 feet long and 8 feet in diameter. In both stages theoxidizer and fuel tanks had a common bottom which reduced overall dimensions andlaunch weight of the missile. The bottom of the oxidizer tank of the first stage was placedinside the tank like an inverted truncated cone. The nozzle of the sustainer of the secondstage was included in the formed upper volume. The first stage used a new set of fourclosed-cycle single-chambered rocket motors, while the second stage incorporated asingle-chambered sustainer and a four-chambered control motor. Asymmetricaldimethylhidrazine and nitrogen tetraoxide were used as propellants. The missile uses aninertial guidance system consisting of an autonomous guidance/control system with agyro-stabilized platform of floating gyros. The command structure also provided anautomatic checkout of all systems during flight and automatic preparation of launch.

The development of the UR-100 was approved by the government on 30 March 1963.The developer was NPO Mashinostroyenia (OKB-52). The missile was deployed in atleast four variants, and was probably tested in several additional configurations. There issome confusion among these variants between recent published Russian sources, whichfocus on the physical configuration of the rocket, and contemporaneous Western sources,which were limited to intelligence derived from observing flight tests. In the middle ofthe 1970's the UR-100 was replaced by two modernized versions that received thedesignations UR-100K (15A20) and UR-100U (15A20U).

SS-11 Mod-1 UR-100 The flight-design tests were conducted at the Baikonurcosmodrome between 19 April 1965 and 27 October 1966. The first silo-launchwas conducted on 17 July 1965. The Mod 1 reentry vehicle had a ballisticcoefficient of 310 lb per sq ft and a CEP assessed by Western intelligence at 1.0nm. Western intelligence assessed that an initial operational capability wasreached in early 1966. According to Russian sources the first three regiments withUR-100 missiles were put on alert on 24 November 1966, and operationalemployment began on 21 July 1967. According to Russian sources, initially themissile was equipped with two different types of warheads: a light one forintercontinental targets in North America, and a heavier one for medium rangetargets in Eurasia.

SS-11 Mod-1 UR-100UTTh Upgrades to the UR-100 missile provided a differentnose cone that allowed improved flight characteristics and a modified command

structure that reduced the time for pre-launch operations. The modified versionreceived the designation UR-100UTTh (8K84UTTh). It differed from formermissiles by improved warhead technology, improved launching equipment, andan autonomous power supply system, ensuring extended storage in fueledconditions. The flight-design tests of the UR-100UTTh missile were conductedbetween 23 July 1969 and 15 March 1971.

SS-11 Mod-2 UR-100K The development of the UR-100K (15A20) missile[known in the West as the SS-11 Mod-2] began in the middle of the 1960s. Themain design changes concerned lengthening of the first stage to increase theamount of propellant and modifications to the propulsion systems of both stages.These measures allowed an increase of launching weight of 8 tons and a 60percent increase of throw weight. The maximum range of the UR-100K wasincreased up to 12,000 km, and through the use of improved sensors the accuracywas increased by a factor of 1.5 to a CEP of 1 Km. The Mod 2 reentry vehicle hada ballistic coefficient of 900 lb per sq ft and a CEP assessed by Westernintelligence at 0.6 nm. The missile also dispensed decoys at the end of the boostphase of the trajectory before the separation of the reentry vehicle. The reentryvehicle itself had radio-reflecting properties. The sophisticated control systemallowed an increase of combat readiness of a missile through the use of boostedspin-ups of gyros. The silo had its own system of power supply allowing remotechanges of its mission and launch. The flight-design tests of the UR-100K missilewere conducted from 02 February 1971 through 24 November 1971. According toRussian sources the missile was initially deployed on 28 December 1971. Westernintelligence assessed that an initial operational capability was reached in 1973.

SS-11 Mod-3 UR-100U The UR-100U (15A20U) missile differed from the UR-100K missile by the number of warheads. Instead of a single warhead it carriedthree warheads, though with a reduced maximum range. The tests of the UP-100Uwere conducted from July 1971 through January 1973, and its deployment startedon 26 September 1974 according to Russian sources. According to Westernsources, the first Mod 3 flight test was on 12 September 1969, and Westernintelligence assessed that an initial operational capability was reached in 1973.During development of this missile efforts centered on increasing its survivability.The silos were hardened and the shock-absorption of the transport-launch canisterwas improved. The silo consists of a monolithic ferro-concrete trunk with a steelhardware compartment, rigidly attached to it. The trunk was covered with anaccident protection device in the form of a sliding roof.

SS-11 Mod-4 The Mod-4 missile differed from the Mod-3 missile by the numberof warheads -- instead of three warheads it carried six. This variant was tested butnot deployed.

The missile was deployed in a silo launcher, with a design that was substantiallysimplified in comparison with earlier complexes. The silo could be closed for protectionwith the help of a pneumatic driven sliding roof. This was the first Soviet ICBM to bedeployed with a pressurized transport launch canister in which the missile was deliveredto the launch complex and from which it was fired. During the storage of the missile the

engines were isolated from the propellant components by membrane-valves that providedtheir safety during extended times of being in a fueled condition.

The SS-11 deployment was assessed by Western intelligence to be similar in concept tothe US Minuteman, where a large force was deployed in hardened silos requiring aminimum of support facilities. Silo and launch control center hardness was estimated at700 and 400 psi overpressure, respectively, from a 1-MT weapon. The sites weredeployed in groups of ten unmanned silos with a single launch control center for eachgroup. Reaction time in the normal readiness condition was assessed by the West as 0.5to 3.0 min. with an unlimited hold time in this alert condition.

The UR-100 missile was the most extensively deployed ICBM within the StrategicRocket Forces. Between 1966 and 1972 a total of 990 of these missiles were deployed.Between 1973 and 1977 some 420 launchers of the UR-100K/UR-100U missiles weredeployed while the UR-100 missiles were phased out. As of 1991 some 326 remained inservice, while by the end of 1994 all but 10 of the UR-100 and UR-100U missiles hadbeen removed from combat duty in compliance with the START-1 treaty. By the end of1996 all SS-11 missiles had been dismantled.

SpecificationsMod-1 Mod-2 Mod-3 Mod-4

DIA SS-11 SS-11 SS-11 SS-11

NATO Sego Sego Sego Sego

Bilateral RS-10 RS-10 RS-10M RS-10M

Service UR-100/UR-100M

UR-100K UR-100U

OKB/Industry 8K848K84UTTkh

8K84K 8K84UTTkh8K84M15A20U

Design Bureau OKB-52Chelomey

OKB-52Chelomey

OKB-52Chelomey

OKB-52Chelomey

Approved 3/30/1963



1962-66 1969-1971

1971-1973 1971-1973

First Flight Test 4/19/65 7/23/1969 2/2/71 &9/2/69

6/16/71

IOC 11/24/966 3/1/1970 1973 - 74 [notdeployed]

Deployment Date 7/21/1967 12/28/72 9/26/1974 [notdeployed]

Type of Warhead Single Single MRV MRV

Warheads 1 1 3 6

Yield per Warhead(Mt)(Russian Sources)

0.5 or1.0 -1.1

1.2 0.35 0.35-1.3

Yield per Warhead(Mt)(Western Sources)

0.6 to 1.2 0.6 to 1.2 0.2 to 0.8

Payload (t) 0.76 - .08 0.9-1.2 1.208 1.2

Total length (m) 16.925 18.9 -19.0

18.9 19.1 - 19.8

Total length w/oWarhead (m)

16.45-16.69

16.5 17 17

Missile Diameter(m)

2 2. 2 2

Launch Weight (t) 39.4 - 42.3 50.1 50.09 - 50.1 50.1 -51.24

Fuel Weight (t) 40.4? 45.3 45.3 45.3

Range (km) 11,000-12,000 or5,000

11,000-13,000

10,600-12,000

10,600-12,000


1,400 1,400 900-1,350 900-1,350


1,400-1,500

1,100-1,400

1,000-1,100

Number of Stages 2


Canister length w/oFront meters (m)



1st stage (8S816) 2nd stage (8S817)

Mod-1

Mod-2 Mod-3/4 Mod-1 Mod-2 Mod-3/4

Length (m) 12.5 13.3 13.4 2.9 3.2 3.8

Body diameter (m) 2 2

Fueled weight (t) 34 38-40 40

Dry weight (t)

Engine

Designation

RD-0216 / RD-0217(15D2)

RD-0235 / RD-0236(8D13, 8D419, 15D14)

Design Bureau OKB-154, Acad. S. A.Kosberg

OKB-117, Acad. V. Klimov

Configuration Cluster of four engines One engine

Years of R & D 1963-1966

Propellants Liquid Liquid

Fuel UDMH UDMH

Oxidizer Nitrogen Tetroxide Nitrogen Tetroxide

Burning time (sec) 103? 164?

Verniers ThrustSea Level/Vacuum(Tonnes)

N/A 1.565 ?1.6

Main EnginesThrust SeaLevel/Vacuum(Tonnes)

79.95/86.275 - 89.33 13.665 - 15.195 - 24.5 Vacuum


319.8/357.6 20.0651 - 22.3 - 30.9 Vacuum

Main engineSpecific ImpulseSea Level/Vacuum(sec.)

262/313 Vacuum 320 Vacuum

Verniers SpecificImpulse Sera

N/A 293 Vacuum

Level/Vacuum(sec.)

Basing Mode Silo

Hardness Silo at 700-750 psiLCC at 360-400 psi

Launching Technique Hot

Deployed boosters

Test Boosters

Deployment Sites

Training Launchers

Space Booster Variant No

Deployment Sites


Bershet? Perm

Drovyanaya Drovyanaya

Itatka

Kostroma Kostroma

Kozelsk Kozelsk

Krasnoyarsk Gladkaya

Pervomaysk Pervomaysk

Shadrinsk

Svobodny Svobodny

Teykovo Teykovo

Tyumen

Yasnaya Olovyannaya


First flight test

Mod 1 April 19, 1965

Mod 2 July 23, 1969

Mod 3 September 12, 1969

Operational system production probably began

Mod 1 1965

Mod 2 ?

Mod 3 1971

First penaids flight testing September 20, 1967

Short-range flight testing . began July 1968

First launch from operational site November 11, 1970

Maximum operational launcher deployment 1971

SS-11/RS-10 in Launch CanisterSS-11/RS-10 Outside Launch

CannisterSS-11/RS-10 Stage 1

http://www.fas.org/irp/dia/product/83_ss11.jpg



http://www.fas.org/nuke/control/start1/text/image/rfphotos/rs10ss11msl.jpg


SS-11/RS-10Emplacement

Equipment

SS-11/RS-10EmplacementEquipment 2


http://www.fas.org/nuke/control/start1/text/image/rfphotos/rs10ss11empl2.jpg

UR-100MR / SS-17 SPANKERThe UR-100MR / SS-17 intercontinental ballistic missile is a two-stage, tandem, storableliquid-propellant missile intended to replace the light UR-100 SS-11 missile. It was acompeting design with the SS-19 Stiletto, though in fact both were deployed. It was thefirst Soviet ICBM to have a Multiple Independently targetable Reentry Vehicle (MIRV)and the first to use a cold launch system. The UR-100MR / SS-17 intercontinentalballistic missile was assessed as being capable of delivering a throw-weight of 6,000 lb toa range of 5,500 nm. The throw-weight consists of a post-boost vehicle and either one orfour reentry vehicles.

The overall dimensions of the SS-17 were determined by the characteristics of the SS-11UR-100 silos in which the UR-100MR missile was planned for deployment. Thediameter of both stages was increased in relative to that of the UR-100, and is 2.25 m forthe first and 2.1m for the second stage. The UR-100MR uses asymmetricaldimethylhydrazine and nitrogen tetraoxide propellants. The first stage uses a closed-cyclesingle-chambered sustainer engine and a four-chambered open-cycle control motor. Thesecond stage is equipped with a single-chamber open-cycle sustainer, placed inside thelower part of the fuel tank. The flight control during the first stage uses deflecting thecontrol motor chambers, while the second stage uses gas injected into the diverging partof the nozzles. Solid propellant retrorockets are used to separate the stages.

The rocket MR UR-100 was placed in previously hardened SS-11 UR-100 silos. Themissiles in their transport-launch canister were inserted into the silo with the use of twoshock-absorption belts. The SS-17 uses a sabot cold launch or pop-up launch system thatfacilitated modifying existing SS-11 facilities.

SS-17 Mod-1 - This initial version of the SS-17 carried 4 MIRV warhead with ayield of 0.3-0.75 Mt each, an instrument module with a command structure andsolid-propellant rocket motor comprise the post-boost vehicle. According toWestern estimates each RV weighed about 900 lbs. The missile had an inertialguidance system with an estimated CEP of 0.34 nm for 1975 and a potential CEPof 0.28 nm in 1980. Its development was approved in September 1970 andconducted by KB Yuzhnoye (OKB-586) which was headed by V. F. Utkin. Pop-up tests which improved the mortar launch technique began in May 1971. The fullscale flight-design tests of Mod1 and 2 were conducted at the Baikonurcosmodrome test site from 26 December 1971 and 17 December1974. Flighttesting was first detected by the West on 15 September 1972. The first regimentwith MR UR-100 missiles was put on alert on 06 May 1975 and its deploymentbegan on 30 December 1975.

SS-17 Mod-2 - The Mod-2 missile carries only a single warhead with a yield of 4-6 MT.

SS-17 Mod-3 - On 16 August 1976 a governmental order to improve the UR-100MR performance characteristics was issued. The preliminary design of thisMR UR-100UTTh missile known as SS-17 Mod3 was completed by KB

Yuzhnoye (OKB-586) in December 1976, receivingthe industrial index number15A16. Like the SS-17 Mod-1 it carries four MIRV warheads, but it incorporatedenhanced survivability and was equipped with an improved commando systemand a modernized nose cone. The flight-design tests began on 25 October 1977and were finished on 15 December 1979. The Mod-3 reached its IOC in 1978 andits deployment started on 17 December 1980 (simultaneously with the R-36MUTTh).

In 1979 130 missiles were deployed in two missile fields near Yedrovo and Kostroma.From 1979 till 1980 all single warheaded missiles were replace by MIRVed missiles. Inthe years 1982-1983 all MR UR-100 missiles as well as 20 UR-100 missiles werereplaced by the MR UR-100UTTh missiles which reached their maximum operationalinventory of 150 in 1983. When the START-1 treaty was signed in 1991 the SovietUnion had 47 launchers for the MR UR-100UTTh which were all subject to dismantling.


DIA SS-17 SS-17 SS-17

NATO Spanker Spanker Spanker

Bilateral RS-16A RS-16A RS-16B

Service MR-UR-100 MR-UR-100 MR-UR-100UTTKh or MR-UR-100U

OKB/Industry 15A15 15A15 15A16

Design Bureau OKB-586Acad. V. F.Utkin

OKB-586Acad. V. F.Utkin

OKB-586 Acad.V. F. Utkin

Approved 9/1970 9/1969 8/16/1976

Years of R&D 1964-70 1964-70


1971-74 1970-75 1977-79

First Flight Test 09/15/1972failure12/26/71success

12/26/1971 10/25/1977

IOC 05/06/1975 1975 10/17/1978

Deployment Date 12/30/1975 12/30/1975 12/17/1980

Type of Warhead MIRV Single MIRV

Warheads 4 1 4

Yield (Mt) 0.350-0.750 3.5-6.0 0.550 - 0.750

Payload (t) 2.550 2.550 2.550

Total length (m) 22.52 21.6 ? 22.52 23.9

Total length w/o

Warhead (m)

20.9 20.9 20.9

Missile Diameter(m)

2.25 2.25 2.25

Launch Weight (t) 71.1 71.1 71.1 - 72

Fuel Weight (t) 63.2 63.2 63.2

Range (km) 10,200 -10,320

10,100 -10,320

10,200 -11,000


1,080 1,080 920


440-500 420-450 220-400

Number of Stages 2


Canister length w/o

Front meters (m)



1st stage 2nd stage

Length (m) 14.3, 14.9 3.2

Body diameter (m) 2.25 2.15

Fueled weight (t) 59.0

Dry weight (t)

Engine Designation RD-268 Main Engine RD-262 (15D169)

Engine Designation RD-263 VernierEngine

N/A

Design Bureau Acad. V. P. Glushko

(OKB-456)

Yuzhnoye

(OKB- 586)

Configuration One Main Engine, OneFour ChamberVerniers Engine

One Chamber

Year of R & D mainengines

1969-1973 1969-1972

Year of R & D Vernierengine

1970-1973 N/A


Fuel UDMH UDMH

Oxidizer Nitrogen Tetroxide Nitrogen Tetroxide

Burning time (sec.) 130 195

Main Engine ThrustSea Level/Vacuum(Tonnes)

117/126 14.5 44 Vacuum

Verniers Thrust SeaLevel/Vacuum(Tonnes)

28.230 /? N/A

Main Engine SpecificImpulse SeaLevel/Vacuum (sec.)

?/319 331 Vacuum

Vernier engineSpecific Impulse SeaLevel/Vacuum (sec.)

259/301 N/A

Basing Mode Silo

Hardness

Launching Technique Mortar Launch

Deployed boosters

Test Boosters

Warheads Deployed

Training Launchers


Deployment Sites


Kostroma Kostroma

Vypolzovo Yedrovo

SS-17/RS-16 in Launch Canister SS-17/RS-16Missile

SS-17/RS-16Stage 1

SS-17/RS-16 and SS-19/RS-18Emplacement Equipment

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UR-100N / SS-19 STILLETOOnce regarded by some as the "backbone" of the Soviet ICBM force, the fourthgeneration UR-100N / SS-19 intercontinental ballistic missile is a two-stage, tandem,storable liquid-propellant missile. The SS-19 is approxiamately 80 feet long and 8 1/2feet in diameter. It was a competing design with the SS-17 Spanker, though in fact bothwere deployed to partially replace the SS-11 force.

The UR-100N is similar to the UR-100, but with an increased diameter and longerpropellant tanks its launch weight was more than doubled and the throw-weight wasincreased over three-fold. The UR-100N uses asymmetrical dimethylhidrazine andnitrogen tetraoxide propellants. The first stage consists of four autonomous closed-cyclesingle-chambered rocket motors. The second stage has a closed-cycle single chamberedsustainer and a four chambered open cycle control motor with four rotating nozzles. Theguidance and control system of the SS-19 is identical to that of the SS-18, and permitsremote monitoring of missile status while on alert, as well as automatic pre-launchpreparation, remote missile targeting before launch and in-flight control of the missile viaa flexible pitch control program. The UR-100N silos were constructed at the same sites asthe UR-100U silos but were completely dismantled and rebuilt to increase thesurvivability of the new missiles. The UR-100N was launched in the hot mode throughthe thrust of the first stage sustainer engine.

The SS-19 has been deployed in three configurations.

SS-19 Mod-1 - Through the increase of throw-weight and reduction of the size ofthe warheads relative to the UR-100 the UR-100N carries six MIRV warheadswith a yield of 550 KT each according to Russian sources [Western estimatessuggested a yield of one- to two-megatons]. According to Western estimates thebooster alone was limited to a range of 4900 nm but the total system, booster plusPBV, was assessed as being capable of delivering all six RVs to a maximumrange of 5200 nm. Development was approved on 19 August 1970 and developedby V. N. Chelomey. The flight tests of the UR-100N were conducted at theBaikonur cosmodrome from 09 April 1973 through October 1975. The missilewas initially deployed on 30 December 1975, though according to Westernestimates it achieved an initial operational capability in 1974. The first regimentwith UR-100N missiles was put on alert on 26 April 1975 and by the end of 1975a total of 60 launchers were deployed. The missile employed an inertial guidancesystem that was is estimated by some Western sources to have an operational CEPof 0.3 nm in 1975 with a potential CEP of 0.25 nm by 1980. However, due to thehasty deployment of the UR-100N a major design flaw was overlooked. Traininglaunches that took place after its deployment revealed a significant reduction ofaccuracy due to resonant oscillations of the missile. Subsequently all deployedmissiles were modified to eliminate the problems.

SS-19 Mod-2 - Otherwise similar to the Mod-1, this variant carries a singlewarhead with a yield reported by Russian sources of between 2.5 and 5 MT.

Between 1976 and 1978 the UR-100N reached its maximum operationalinventory of 180 missiles, of which 60 carried a single warhead. Both of these SS-19 Mods were attributed "hard target kill" capabilities by the West.

SS-19 Mod-3 -The development of an improved version was authorized on 16August 1976. The upgrades to the missile involved the development of improvedengines and modification of the command system. The extent of protection from anuclear strike at their silos was considerably improved. The flight-design tests ofthe improved version that received the designation UR-100NUTTH wereconducted between 26 June 1979 and 26 October 1979. Its deployment began on05 November 1979.

The first regiment with the UR-100NUTTH was put on alert on 06 November 1979.Between 1980-1982 UR-100N missiles with a single warhead (SS-19 Mod 2) werereplaced by the UR-100NUTTH (SS-19 Mod 3). The replacement of all UR-100Nmissiles was completed in 1983. In 1984 the UR-100NUTTH reached its maximumoperational inventory of 360 missiles. From 1987 on they were gradually replaced bynew missiles. The silo-based version of the SS-24 replaced some SS-19s.

When the START-1 treaty was signed in 1991 the Soviet Union had a total of 300 UR-100NUTTH missile stationed in Russia and Ukraine. After the dissolution of the SovietUnion Ukraine claimed ownersip of the missiles located on its territory. In compliancewith the START treaty provisions Ukraine is in charge of the dismantling the launchersfor the SS-19 missiles. However, all nuclear warheads that were deployed in Ukrainewere dismantled by Russia.

Some 170 launchers remain in Russian territory, of which 10 were deactivated but notdismantled. In December 1995 Strategic Rocket Forces Commander Colonel GeneralIgor Sergeyev announced a policy under which the service life of the SS-19 would beextended from 10 years to 25 years. The missiles will remain on alert at least through2005, and the missiles that were deployed in the early 1980s will serve beoynd this.

Following the ratification of the START-II treaty by the Duma, Russia is obliged todismantle all ground-based ICBMs with multiple warheads. Under the treaty provisions atotal of 105 of the UR-100NUTTH missiles can be retained provided they aredownloaded to carry only one warhead instead of six.



NATO Stiletto Stiletto Stiletto

Bilateral RS-18A RS-18AUTTKh

RS-18B

Service UR-100N UR-100N UR-100NU

OKB/Industry 15A30 15A30 15A35

Design Bureau OKB-52,KB Salyut,

Acad. V.N.Chelomey

OKB-52, KBSalyut,

Acad. V. N.Chelomey

OKB-52, KBSalyut,

Acad. V. N.Chelomey

Approved 8/19/1970 8/19/1970 8/16/1976

Years of R&D 1964-73 1964-1973

Engineering and

Testing

1973-75 1973-75 1977-79

First Flight Test 9/15/1972failure &12/28/1973success

4/9/1973 10/26/1977

IOC 4/26/1975 1975 1979

Deployment Date 12/301975 12/30/1975 11/5/1979

Type of Warhead MIRV Single MIRV

Warheads 6 1 6

Yield per Warhead(Mt)

0.5 0.550.750

2.5 - 5.0 0.5-0.75

Payload (t) 4.350 4.350 4.350

Total length (m) 24.0 24.0 24.3

Total length w/o

Warhead (m)

21.1 21.1 21.1

Missile Diameter(m)

2.50 2.50 2.50

Launch Weight (t) 103 -105.6

105.6 103.4 - 105.6

Fuel Weight (t) 93.1 93.1 93.1

Range (km) 9,650 10,000 10,000

CEP (m)

(Russian Sources)

? ? 920

CEP (m)

(Western Sources)

350-550 250-400 220-380

Number of Stages 2


Canister length w/o

front meters (m)


Booster guidance system Inertial

1st stage 2nd stage 3rd. Stage

Length (m) 17.2 2.8

Body diameter (m) 2.5 2.5 2.5

Fueled weight (t) 86.3 86.3

Dry weight (t)

Engine Designation RD-0233 / RD-0234 RD-0235(14/15D113)

N/A

Vernier EngineDesignation

N/A RD-0236(15D114)

N/A

Bus EngineDesignation ThirdStage

N/A N/A RD-0237

Design Bureau MainEngines

OKB-154, Acad. S.A. Kosberg

OKB-154,Acad. S. A.Kosberg

N/A

Design Bureau VernierEngine

N/A OKB-154,Acad. S. A.Kosberg

N/A

Design Bureau BusEngine Third Stage

N/A N/A OKB-154,Acad. S. A.Kosberg

Configuration Cluster of fourengines

One engine N/A

Configuration VernierEngine

N/A Four vernierchambers

N/A

Configuration Busengine Third Stage

N/A N/A Four chambers

Years of R & D 1969 1974 1969 - 1974 N/A

Years of R & D VernierEngine

N/A 1969 - 1974 N/A

Years of R & D BusEngine Third Stage

N/A N/A 1969 - 1974

Propellants Liquid Liquid Liquid

Fuel UHMH UDMH UDMH

Oxidizer Nitrogen Tetroxide NitrogenTetroxide

NitrogenTetroxide

Burning time (sec.)

Main Engine ThrustSea Level/Vacuum(Tonnes)

46.961/52.958 - 53.1 24.5 Vacuum N/A

Verniers Thrust SeaLevel/Vacuum(Tonnes)

N/A 1.6 Vacuum N/A

Third Stage BusEngine Thrust Vacuum(Tonnes)

N/A N/A 0.5 Vacuum


187.8442/207.8319 30.9 Vacuum 2.0 Vacuum

Main Engine SpecificImpulse Sea Level/Vacuum (sec.)

291 / 310 320 Vacuum N/A

Vernier EngineSpecific Impulse SeaLevel/Vacuum (sec.)

N/A 293 Vacuum N/A

Bus Third StageEngine Specific

N/A N/A ?

Impulse Vacuum (sec.)

Basing Mode Silo

Hardness

Launching Technique Hot

Deployed boosters

Test Boosters

Warheads Deployed

Training Launchers

Space Booster Variant Yes SL-X- ? , Rockot

Deployment Sites


Khmel?Nitskiy Derazhnaya

Kozel?sk Kozelsk

Pervomaysk Permovaysk

Tatishchevo Tatishchevo

SS-19/RS-18 in Launch Canister SS-19/RS-18Missile

SS-19/RS-18Stage 1





SS-17/RS-16 and SS-19/RS-18Emplacement Equipment


UR-200 / SS-X-10 SCRAGThe 1961 Global Rocket 1 (GR-1) requirement chartered a competition for thedevelopment of a Fractional Orbital Bombardment System. Yangel offered the R-36.Korolev proposed the 8K713, which was cancelled in 1964 prior to flight testing due toengine delays. Chelomei proposed the UR-200, which was cancelled following theOctober 1964 ouster of downfall of Khrushchev, who had been Chelomey's politicalpatron.

The UR-200 intercontinental ballistic missile was a two-stage, tandem, cryogenic liquid-propellant missile with a nominal payload of approximately 7000 lb. With approximatelythe same launching weight as the R-16 missile (138.0 T), the UR-200 was designed tocarry a very large payload (3.3 T or 2.7 T depending on the nose cone]. The UR-200 wasunique in that it was the first and only Soviet ICBM for which attitude control duringfirst-stage flight was provided by hinged/gimbaled engines. The missile was to be surfaceand silo launched from former R-16U silos.

Development of the UR-200 was approved on 16 March 1961, to serve simultaneously asan ICBM and as a space launch vehicle. The UR-200 missile was the first missile to bedeveloped by the NPO Mashinostroyeniya (OKB-52) under designer V. N. Chelomey. InNovember 1963 flight-design tests began at the Baikonur cosmodrome, and a total ofnine launches were conducted, after which the program was terminated. The last flighttest on 20 October 1964, was the only one to the 6,500 nm Pacific test range, and wasapparently successful.

The UR-200 was not deployed operationally. The UR-200 was initiated as atechnologically conservative alternative to the SS-9 SCARP, and used cryogenic liquidfuel (Liquid Oxygen and Kerosene). The successful development of the storablehypergolic propellants on the SS-9 rendered this approach obsolete, and in 1965 thedevelopment of the UR-200 missile was cancelled. The exact reasons for terminating theSS-10 weapon system program are unknown, but are believed to be related to theprobable use of a cryogenic propellant combination and the success of the SS-9 weaponsystem.

The UR-200 flight tests were associated with the designation SS-X-10, although Westernintelligence mistakenly associated these flights with the GR-1 missile that was displayedin parades in Red Square. Although the GR-1 missile had not been flight tested, it wasparaded in Red Square and did receive the US-designation SS-X-10 SCRAG. The GR-1missile was correctly identified as being a FOBS configuration, although open sources atthe time evidently assumed that the FOBS parading in Red Square and the FOBSundergoing flight tests were the same system. In fact, the initial FOBS flight tests wereconducted by the competing UR-200 missile. It is unclear when US intelligenceunderstood that the parade missile and the test missile were two different systems.

SpecificationsDIA SS-X-10

NATO N/A

Bilateral N/A

Service UR-200/UR-200B

OKB/Industry 8K81/8K83

Design Bureau OKB-52 , KB Salyut, Acad V.N. Chelomey

Approved 3/16/1961 & 8/1/1961




IOC Not operational

Deployment Date Not deployed, terminated1964/1965

Type of Warhead 1

Warheads Single

Yield (Mt) 5 & 15

Payload (t) 2.690 - 3.9 - 4.0

Total length 34.65

Total length w/o warhead 30 – 32

Missile Diameter 3

Diameter of Stabilizers 4.2

Launch Weight (t) 136 -138

Fuel Weight (t)

Range (km) 12000 & 14000

CEP (m) (Russian Sources)

CEP (m) (Western Sources) 1800-5500

Number of Stages 2

Canister length (m)

Canister length w/o

Front meters (m)


Booster guidance system Inertial autonomous with radiocorrection

1st stage 2nd stageLength (m) 16.9 – 19.4 12.9Body diameter (m) 3 2.2Fueled weight (t)Dry weight (t)Engine DesignationMain Engines

RD-0203/RD-0204

(8D44/8D45)

RD-0206/RD-0207 (8D46)


N/A Four Verniers

Design Bureau OKB-154, Acad. S,A, Kosberg

OKB-154, Acad. S, A, Kosberg

Configuration Cluster of FourEngine

One Main Engine and FourVerniers

Years Of R & D 1961-1964 1961-1964

Propellants Liquid LiquidFuel UDMH UDMHOxidizer (AT) Nitrogen

Tetroxide(AT) Nitrogen Tetroxide

Burning time (sec.)Main Engine ThrustSea Level/Vacuum(Tonnes)

50.0/57.0 58.7 Vacuum

Vernier Engine ThrustSea Level/Vacuum(Tonnes)

N/A 3.1 Vacuum


200 62.5 - 71.1 Vacuum

Specific Impulse MainEngines (sec.)

278/311 297

Specific ImpulseVernier engine (sec.)

N/A 322 - 326

Basing Mode Soft Site Land BasedHardness N/.A

Launching Technique HotDeployed boosters N/ATest BoostersWarheads DeployedDeployment Sites N/ATraining Launchers N/ASpace Booster Variant No

UR-500 / [PROTON]On 09 August 1961, Premier Nikita Khrushchev openly threatened the West with a newand terrifying weapon, the orbital H-bomb. "You do not have 50- or 100-megaton bombs,we have bombs more powerful than 100 megatons. We placed Gagarin and Titov inspace, and we can replace them with other loads that can be directed to any place onEarth." Although the US had hypothesized orbital bombs, this was the first publicindication that the Soviets were actively pursuing this course of action. Within a fewmonths, however, American analysis of the threat diminished its proportions.

SpecificationsMod-1 = 2Stages

Mod-2 = 3 Stages

DIA SS-LX-? "City Buster"ICBM

SS-LX-? FOBS

NATO N/A N/A

Bilateral N/A N/A

Service UR-500 UR-500, UR-500K

OKB/Industry (8K82) (8K82)/(8K82K)

Design Bureau OKB-52Acad. V.N.Chelomey

OKB-52 Acad.V.N. Chelomey

Approved 4/24-29/1962

4/24- 29/1962

Cancellation ICBM5/15/1964

ICBM 5/15/1964

Years of R&D 1961-1965 1961-1967


1962-1965 1962-1970

First FlightTest

7/16/1965 11/22/67

IOC N/A N/A

DeploymentDate

N/A N/A

Type ofWarhead

1 1

Warheads Single Single

Yield (Mt) 50 – 100 –150

(35-45)

30 – 50 (45 –55)

Payload (t) 12.2 - 14 14.0 –17.0

Total length(m)

37 – 46.28

Total length

w/o warhead(m)

30.68 44.3

MissileDiameter (m)

7.4 with 1.6strap-ontanks, 4.1core tank

7.4 with 1.6 strap-on tanks, 4.1 coretank

Launch Weight(t)

600 620 - 621.9

Fuel Weight (t)

Range (km) 10,000 12,000


N/A N/A


N/A N/A

Basing Mode Hardenedlaunchcomplex

Hardened launchcomplex

Number of Stages 2 3Canister length w/o front meters (m) N/A

N/A

N/A

N/ACanister diameter (m) N.A N/A

Booster guidance system Inertialautonomous

Inertialautonomous

1st stage 2nd stage 3rd. StageLength (m) 21.07 – 21.18 Strap-on

Tanks 19.914.56 6.857

Body diameter (m) 7.4 With 1.6 Strap-onTanks, 4.1 Core Tank

4.1 4.1

Fueled weight (t) 449.8 172.1 46.562Dry weight (t) 32.5 – 34.5 12.1 4.185Main EngineDesignation

RD-253(11D48)(11D43)

RD-0208/RD-0209 or(three)RD-0210/(one)RD-0211

RD-0210/RD-0211 or RD-0213/RD-0214


N/A N/A RD-0214 FourChamberVernier Engine

Configuration Cluster of Six Engines Four Engine One EngineDesign Bureau OKB-456, Acad. V. P.

GlushkoOKB- 154Acad. S. A.Kosberg

OKB-154,Acad. S. A.Kosberg

Years of R&D 1961-1965 1961-1964 1961 – 1967Propellants Liquid Liquid LiquidFuel UDMH UDMH UDMHOxidizer N204 = Nitrogen

TetroxideN204 =NitrogenTetroxide

N204 =NitrogenTetroxide

Burning time (sec.) 127 - 130 210-230 240Verniers Thrust SeaLevel/Vacuum(Tonnes)

N/A ? 3.21 x 4 =12.8493Vacuum


147 – 148.8884 –150.25 / 166.7347

233.6 Vacuum 58.4 Vacuum


6 x 147 - 150.25 =901.5

4 x 58.4 – 59.4= 233.6Vacuum

58.4 – 59.4 +12.8493 =71.2493Vacuum

Main Engines SpecificImpulse SeaLevel/Vacuum (sec.)

284.9/310.0 326.5 326.5

Vernier EngineSpecific Impulse SeaLevel/Vacuum (sec.)

N/A N/A ?

Hardness N/ALaunching Technique Hot launchDeployed boosters N/ATest Boosters N/AWarheads Deployed N/A

Training Launchers N/ASpace Booster Variant SL-LX-?,

SL-9/Proton/D, Proton 1-3B

SL-12/Proton K, Zond, (UR-500L1),

Lunar, Venera, Mars,

SL-13/Proton K, Proton-4, Salyut, Mir,Proton-K

START Locale US-DesignationN/A N/A

RT-1 ICBM

SpecificationsDIA

NATO

Bilateral

Service RT-1 RT-1-63

OKB/Industry (8k95-63) (8K95-1963)

Design Bureau OKB-1, Acad.S. P. Korolev

OKB-1, Acad.S. P. Korolev

Approved 11-20-59 11-20-59

Years of R&D 1958/59 -1962 1962,-1963/1964

Engineering and Testing 1960 –1963 1962 -1963

First Flight Test 04/28/1962failure3/18/1963successcancelled

9-11/ /1965, 2failures onesuccesscancelled

IOC N/A N/A

Deployment Date N/A N/A


Warheads 1 1

Yield (Mt) 0.5 -1.0 0.6 -1.0

Payload (t) 0.5 - 0.8 0.8

Total length (m) 18.0 18.3

Total length w/o warhead (m)

Missile Diameter (m) 2.0 2.0

Launch Weight (t) 35.5-36.0 (34) 34 –35.5

Fuel Weight (t)

Range (km) 1,850-2,000 2,400-2,500


CEP (m) Western Sources)Number of Stages 3 3Canister length (m)Canister length w/o

front meters (m)Canister diameter (m)Booster guidance system Inertial Inertial

1st stage 2nd stage 3rd StageLength (m) 4.6-4.8 3.9-4.0 2.8Body diameter (m) 1.6 x 4 1.5 x 4 1.4Fueled weight (t)Dry weight (t)Engine DesignationconfigurationDesign BureauYears of R & DPropellants Solid Propellant Solid

PropellantSolidPropellant

Fuel Solid Propellant SolidPropellant

SolidPropellant

Oxidizer Solid Propellant SolidPropellant

SolidPropellant

Burning time (sec.) 30-32

17.5 -30 30 - 42

Thrust Sea Level/Vacuum(Tonnes)

100 51 25


204 223

Basing Mode N/AHardnessLaunching Technique Hot LaunchDeployed boosters 0Test BoostersWarheads Deployed 0Deployment Sites 0Training Launchers 0Space Booster Variant N/A

http://www.fas.org/nuke/guide/russia/icbm/rt-1_2.jpg

RT-2 - SS-13 SAVAGEThe RT-2 is a three-stage missile with sequentially arranged stages and a single reentryvehicle. According to Western estimates, the missile was capable of delivering a 1200 lbreentry vehicle to a maximum operational range of 5500 nm with a CEP in the range of0.7 to 1.0 nm. The three sustainer stages, using solid-propellant motors, were connectedby trellised trusses. Four trellised aerodynamic stabilizers were used to stabilize themissile during the active trajectory leg. The flight control was implemented with the helpof four split nozzles. With a nose cone of 500 kg it had a maximum range of 10,000-12,000 km, which was reduced to 4,000-5,000 km when employing a heavier nose coneof 1,400 kg. The guidance/control system incorporated a gyro-stabilized platform withfloating gyros and pendulous accelerometers.

Three variants of the SS-13 reentry vehicle have been identified. The Mod 1 variant had aballistic coefficient of approximately 300 lb per sq ft and a CEP assessed in the West ofabout 1.0 nm. The Mod 2 has a ballistic coefficient of approximately 730 lb per sq ft anda CEP assessed at about 0.7 nm. Both had a yield in the range 0.6 to 1.5 MT, according toWestern sources.

The system was deployed in hardened and dispersed unmanned silos. Silo and launchcontrol hardness was estimated by Western sources at 1300 psi overpressure. Because ofthe heavy weight of the missile it was transported in parts. The first stage was separatedfrom the second and third stage. The assembly of a missile was directly carried out in thesilo. The silo door was sealed and the ensuing special climate conditions in the siloguaranteed an extended storage of the solid-propellant. The missile launch was effectedthrough a new technique that was essentially the breadboard of a subsequently usedmethod called "mortar launch". Water was poured into the bottom of the launch canister,while in the tail unit of the missile a shroud provided for isolation. During the ignition ofthe first sustainer stage the steam that formed underneath the missile popped the missileout of the silo. The readiness for missile firing was 3-5 minutes.

A railway based version of the RT-2 missile was also studied, but the project neveradvanced beyond the preliminary design phase.

The task of developing a solid-fuel missiles with a range of 10-12 thousand kilometerswas approved by the ministerial Council on 20 November 1959, with Korolev's OKB-1in charge of carrying out the design.

The development of this ICBM was scheduled to be conducted in two separate phases.The first phase provided for the development of a missile designated as RT-1 with arange of 2500-3000 kms using solid fuel. The RT-1 missile was developed andunderwent flight test but was not deployed. With a launch weight of 35.5 T and a payloadof 800 kg it had a limited range of only 2,000 km, the same as the R-12.

The preliminary design of the RT-2 missile was finished in 1963. The flight tests wereconducted in two phases from February 1966 through November 1968. It was firstdetected by Western intelligence during a 1,050 nm short-range flight test on 26 February1966. During the first phase of tests, from February through July 1966, seven successfullaunches from the test site in Kapustin Yar were carried out. The missiles were launchedfrom adapted silos and the nose cones were successfully deployed. During the second testphase between 03 October 1966 and 04 November 4, a total of 16 successful missilefirings out of a total of 25 launches took place on the test site in Plesetsk. A total of 21 ofthe 25 missiles were tested on an intermediate range basis with the nose cone falling on atraining site on Kamchatka and four were tested on maximum range with the nose conefalling into the Pacific Ocean.

On 18 December 1968 deployment of the RT-2 missile began. According to Westernestimates, the initial operational capability was probably achieved in 1969. Maximumdeployment was reached in 1972. The missile deployment areas of missiles RT-2 wereorganized in area of Yoshkar Ola. Despite the hardness of the silos and the relativesimplicity of operation, the operational capabilities of the RT-2 were limited due to asmall throw-weight and the short operational lifetime of the solid-propellant motors.These characteristics limited the deployment to only 60 RT-2 missiles.

In 1968 the development of a modernized version with a sophisticated control system andcountermeasures for overcoming an ABM system was undertaken by KB Arsenal. Themissile received the designation RT-2P. The flight tests RT-2P were conducted fromDecember 1969 tthrough January 1972, and on 28 December 1972 the first missiles weredeployed.

In 1974 the RT-2M variant was deployed. This system was developed by Nadiradize,which finally took over the program in 1973.

The expected service time of the RT-2 and RT-2Ps were estimated to be 10 years.Periodic static tests of motors on firing stands which were carried out after extendedstorage allowed an extension of the time the missiles could remain in service. Themissiles remained in service for more than twenty years, and were phased out by themiddle of 1996. Some have been replaced by the "Topol" missile.



NATO Savage Savage Savage

Bilateral RS-12 RS-12 RS-12

Service RT-2 RT-2P RT-2M

OKB/Industry 8K98 8K98P 8K98M

Design Bureau OKB-1, Acad.S. P. Korolev

OKB-1 Acad.S. P. Korolev& TsKB-7,Arsenal, Acad.A. D.Nadiradizewhich finallytook over in1973

TsKB-7,Arsenal,Acad. A. D.Nadiradizewhich finallytook over in1973

Approved 04/04/1961 12/18/1968

Years of R&D 1958-68 1969-72


1966-68 1969-72

First Flight Test 2/26/1966IRBM &11/4/1966ICBM

01/16/1970

IOC 7-1-1969 1972

Deployment Date 12/18/1968 12/28/1972 1974

Type of Warhead Single Single Single

Warheads 1 1 1

Yield (Mt)Russian Sources

0.75-1.0 0.75-1.65 .466-.467

Yield (Mt)Western Sources

0.6-1.5 0.6-1.5

Payload (t) 0.545 0.6-1.4 0.5- 1.0

Total length (m) 21.27 21.265 21.13


19.7 19.66 ? 19.7 19.8

Missile Diameter (m) 1.95 1.95, 2.0

Diameter of Stabilizers(m)

3.618 3.618 3.618

Launch Weight (t) 46.1 ? 51 51.6 ? 51.9 50

Fuel Weight (t) 43.9 43.9

Range (km) 9,400 ? 9,500 10,000-10,200 10,000


1,800 - 2,000 1,300 ?1,500 1,500 - 1,800


1,850 - 2,000 1,500 ?1800

Number of Stages 3

Canister length (m) N/A

Canister length w/o front meters (m) N/A

Canister diameter (m) N/A



Mod1 Mod2 Mod3 Mod1 Mod2 Mod3 Mod1 Mod2 Mod3

Length (m) 8.7 9.2 9.2-9.5

4.74 5.08 4.8 3.827 5.45 4.5-4.7

Body diameter (m) 1.84 1.84 1.9 1.49 1.49 1.5 0.98-1.06

0.98-1.06

1.0

Fueled weight (t) 34.55 34.55 35 9.6 11.28 3,5 4.64 ?

Dry weight (t) 30.67-30.8

30.8 9.78 3.6 ?

Solid MotorDesignation

15D23 15D23P 15D24 15D24P1 15D25 15D94 15D31/94

Propellants- SolidPropellants

Solid Solid Solid Solid Solid Solid Solid Solid Solid

Burning time 75.37 75.37 59 60.6 45-46 49

Solid Motor ThrustSeaLevel/Vacuum(Tonnes)

91 100 44 44.6 -44.77

22 18

Specific Impulse(sec)

237 /263

269.5 271

Basing Mode Silo

Hardness 1290 psi/LCC at 1430 psi

Launching Mode Hot

Deployed boosters 40

Test Boosters 8

Warheads Deployed 40

Training Launchers 2


Deployment Sites


Yoshkar Ola Yoshkar Ola

SS-13/RS-12 EmplacementEquipment

SS-13/RS-12, Stage 1 SS-13/RS-12, Stages 2 and 3 as aUnit

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RT-20P / SS-15 SCROOGEThe RT-20P missile was the first Soviet mobile ICBM, although Western sourcesgenerally viewed the SS-X-15 as a theater-range ballistic missile. Western intelligencecorrectly determined that the missile had a storable liquid-propellant second stage, butuncertainty remained as to whether the first stage used either a liquid or solid propellants.Western sources were also puzzled as to whether the missile was a two- or three-stagesystem.

The RT-20P was a two-stage missile which was unique in using dis-similar solid andliquid propellants in the first and second stages -- the first stage used solid propellantwhile the second stage used liquid propellants. The engine of the first stage featured fourrotating nozzles to conduct flight control. The second stage had a single chamberedsustainer using asymmetrical dimethylhydrazine and nitrogen tetraoxide. The flightcontrol of the missile was attained by injecting spent turbine gas into the diverging part ofthe four sustainer nozzle.

With a launch weight of 30.2 tons, according to Russian sources the missile could eithercarry a payload of 545 kg delivering a single warhead with a yield of 550 Kt up to 11,000km, or a payload of 1410 kg and a 1.5 Mt warhead up to 8,000 km. Western sourcesbelieved that the missile was capable of delivering a 1000-lb reentry vehicle to a range of5,300 nm with a CEP of 1.0 to 1.5 nm.

During the development of the RT-20P three different basing modes were considered:road-mobile, railway and silo, but only the road-mobile basing mode was actuallydeveloped realized. The missile was placed in a transport-launch canister and fired from aautomotive launcher created on the basis of a heavy T-YUM tank. The launch from thecontainer was conducted using the mortar launch technique.

A new command structure substantially increased the time the missile could bemaintained in an operational mode. The missile had an inertial guidance system, and theapplication of new high-precision gyroscopic devices allowed improved accuracy.Additionally, an improved capability for remote input of mission data implemented.

The missile was designed by KB Yuzhnoye (OKB-586) which finished the design inDecember 1964. On 24 August 1965 its development was officially approved. Althoughthe missile was first displayed in the Moscow parade of November 1965, the flight testprogram did not begin until October 1967. Apparently the first test associated by Westernintelligence with this program was detected on 12 February 1968. This test was a failure.A total of nine test launches were conducted from the Plesetsk test site. After a total ofeight detected flight tests, the program apparently was abandoned following a successfulflight on 07 August 1967. The development of the RT-20P missile was officially haltedin October 1969, and the SS-X-15 was not deployed operationally.

SpecificationsDIA SS-X-15 (SS-XZ-15)

NATO Scrooge

Bilateral

Service RT-20PRT-20PII - silo version

OKB/Industry 8K99 (15II696)



Approved 8/24/1965

Engineering and Testing 1963-1967/69

First Flight Test 10/1967

IOC 1969

Deployment Date Not deployed 10/__/1969


Warheads 1

Yield (Mt) 0.5 or 1.5

Payload (t) 0.545 or 1.410


Total length w/o warhead(m)

16.2


Launch Weight (t) 30-30.2


Range (km) 11000 or 7000-8000


2000-4000


600-1800

Number of Stages 2Canister length (m) 18.90Canister length w/o front meters (m) NACanister diameter (m) 2

Booster guidance system1st stage 2nd stage

Length (m) 6.12 8.4Body diameter (m) 1.8 1.8Fueled weight (t) 16.7 8.9Dry weight (t)Liquid EngineDesignation

N/A RD-857 (15D12) (8K94)


RDTT 15D15 N/A

Design Bureau Acad. M. K. YangelYears of R&D 1963-1967 terminatedPropellants Solid Liquid StorableFuel N/A UDMHOxidizer N/A AT=AK-27P, N204, Nitrogen

TetrioxideBurning time (sec.) 210 + 5Thrust Sea Level /

Vacuum (Tonnes)

60 114-115


? 329.5 vacuum

Basing Mode Ground mobile & silo concept (SLBM?)HardnessLaunching Technique ColdDeployed boosters 0Test BoostersWarheads Deployed 0Deployment SitesTraining LaunchersSpace Booster Variant NA

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RT-21 / SS-16 SINNERThe "Temp-2S" missile was the first attempt to develop a mobile ICBM. that received thewestern designations SS-X-16 Sinner, According to Western assessments, the SS-16probably was intended originally for both silo and mobile deployment, using equipmentand a basing arrangement comparable to that used with the SS-20. The RT-21/SS-16intercontinental ballistic missile is a three-stage, tandem, solid-propellant missile with apost-boost vehicle (PBV) operating after third-stage burnout. The SS-16 is 65 feet longand 6 1/2 feet in diameter. Although equipped with the same bus system as the SS-20mobile missile, the SS-16 was never tested in a MIRV configuration.

The Temp-2S was a three-stage solid-propellant missile with an autonomous inertialguidance/control system. It was started from a transport launch canister. The containerwas installed on the mobile launcher on a wheel landing gear. With a launching weight of44 tons the rocket could deliver a payload of 940 kg to a maximum range of 9,000 kmaccording to Russian sources. It carried a single warhead with a yield of 0.65-1.5 Mt anda CEP of 450 m to 1640 m according to Russian sources. The missile was assessed byWestern intelligence to be capable of delivering a throw-weight of about 2,100 lb to arange of 5,000 nm, with the PBV providing the capability for an additional rangeincrement of about 500 nm for the 1,000-lb class reentry vehicle known to have beentested. The missile used an inertial guidance system providing a CEP assessed byWestern intelligence to be about 0.4 nm.

The development of the missile began with a decree of the Ministerial Council on 10 July1969. The main developer was the Moscow Institute of Thermal Technology under itschief designer A. D. Nadiradzye. The flight tests of the "Temp- 2S" began on 14 March1972, which was detected by Western intelligence. Through the end of1974 a total of 26missile launches were conducted on the training site in Plesetsk. The last missile firingthat took place in April 1976 ended in failure.

According to Russian sources the SS-16 Temp-2S was not introduced into the operationalinventory, although Russian sources affirm that the first two rocket regiments equippedwith the "Temp-2S" were put on alert on 21 February 1976. According to Westernestimates, the SS-16 was deployed beginning in 1978. According to Western sources, atthe time of the signing of the SALT II Treaty in June 1979 as many as 200 missiles hadbeen built, of which as many as 60 were stored on the test training site in Plesetsk.According to Western data by the middle of 1978 as many as 50 missiles could have beendeployed in Plesetsk. As of 1983 the American assessment was that available informationdid not allow a conclusive judgment on whether the Soviets deployed the SS-16, but didindicate probable deployment.

The Soviet Union agreed in SALT II not to produce, test, or deploy ICBMs of the SS-16type and, in particular, not to produce the SS-16 third stage, the RV or the appropriatedevice for targeting the RV of that missile. The missile appeared to share a number ofcomponents with the Soviet SS-20, an intermediate range ballistic missile (IRBM). As

the Parties had agreed that land-based launchers of ballistic missiles which are notICBMs should not be converted into launchers of ICBMs, the United States sought thisban on the SS-16 in order to prevent verification problems which might have arisen if theSS-16 program had gone forward, since in that case distinguishing between SS-16 andSS-20 deployments would have been very difficult. In 1985 the US governmentdetermined that somewhat ambiguous evidence indicated that the SS-16 activities atPlesetsk were a probable violation of SALT II, which banned SS-16 deployment.

By 1985 all supporting equipment had been removed from the training sites and the INF-Treaty finally ruled out the deployment of the SS-X-16.

SpecificationsDIA SS-16

NATO Sinner

Bilateral RS-14

Service RS-14/Temp-2S

OKB/Industry 15Zh42

Design Bureau (MIT) Moscow Institute of ThermalTechnology, NII-1, Acad. A. D.Nadiradze

Approved 3/6/1966 - 3/ 4/1966 IRBM, 7/10/1969officially




IOC 2/21/1976, Halted in 1977

Deployment Date 3/11/1976Late 1975 - US Estimate


Warheads 1

Yield (Mt) 0.65-1.500

Payload (t) 0.940



16.9


Launch Weight (t) 41.5 - 44.2

Fuel Weight (t)

Range (km) 9,200-10,500


450-1,640


360-480

Number of Stages 3


Canister length w/o

front meters (m)



1st stage 2nd stage 3rd stage BusStage

Length (m) 8.58 4.4 3.9


Fueled weight (t) 26.63 8.7 8.7

Dry weight (t)


Propellants SolidPropellant

Solid Propellant SolidPropellant

Burning time (sec.)

Solid Motor Thrust SeaLevel/Vacuum(Tonnes)

Specific Impulse SeaLevel/Vacuum (Sec.)

Vacuum Vacuum

Basing Mode Ground mobile

Hardness

Launching Technique Mortar Cold Launch

Deployed boosters

Test Boosters

Warheads Deployed

Deployment Sites

Training Launchers


RT-2PM - SS-25 SICKLEApproximately the size of the U.S. Minuteman ICBM, the SS-25 carries a single-warheadatop a three stage system. The SS-25 is road mobile, making the missile inherentlysurvivable and capable of reload/refire operations. It can fire from field deployment sitesor through the sliding roof garage it occupies at its base. The SS-25 joined operationalSoviet SRF regiments in 1985. A total area of approximately 190,000 square kilometerscould be required to deploy a force consisting of 500 road-mobile SS-25 ICBMs. A muchhigher number of personnel for the maintenance of the mobile versions than for the fixedmissiles, and the maintenance and operation of mobile ICBMs are significantly moreexpensive.

The three stage solid propellant RT-2PM Topol became the first Soviet mobile ICBM. Itwas deployed after almost two decades of unsuccessful attempts undertaken by differentdesign bureaus. It emerged from the line of development of mobile missiles such as theSS-X-16 Temp-2S and the 'SS-20 Pioneer, and was deployed as a replacement for thewidely deployed SS-11 SEGO.

All three stages are made of composite materials. During the first stage operation theflight control is implemented through four aerodynamic and four jet vanes. Four similartrellised aerodynamic surfaces serve for stabilization. During the second and third stageof flight gas is injected into the diverging part of the nozzle.With a throw-weight of 1000kg the "Topol" carries a single warhead with a yield of 550 Kt and an accuracy (CEP) of900m according to Russian sources [or 300m according to Western sources].

The missile is deployed in a transport-launch canister stationed on a mobile launchvehicle. The Transporter Erector Launcher is mounted on cross-country 7-axle chassiswhich incorprates jacks, gas and hydraulic drives and cylinders, with a power of severalhundred tons, for jacking and leveling of the launcher, speeded up (combat) and sloweddown (maintenance) elevation of the container with the missile to the vertical position.The TEL is accompanied by a Mobile command post, which carries support facilitiesmounted on cross-country 4-axle chassis with unified vans. The complex is equippedwith an onboard inertial navigation system which provides a capability to conduct thelaunch independently from its field deployment sites. This topo-geodesic support andnavigation subsystem, created by the “Signal” Research Institute, provides a quick andhighly precise tie-in of the launcher in a field position and enables its crew to carry outmissile launches from any combat patrol route point. The launch can also be carried outat regimental bases from the garrison garage, which has a sliding roof.

The order to begin the development of this missile was approved on July 19, 1977 andcarried out by the Moscow Institute of Thermal Technology headed by A. D. Nadiradzye.The flight tests were conducted on the Plesetsk test site from 08 February through 23December 1985. During this period the battle management system constituted the mainproblem that had to be resolved. After the first test series was successfully conducted inApril 1985, the first regiment with Topol missiles was put on 23 July 1985. Through this

time work on improving the battle management system continued. The first regimentwith "Topol"-missiles employing a modernized mobile command center (in area the ofIrkutsk) were put on alert on 27 May 1988. The test missile firings were finallycompleted on 23 December 1987.

At the time of the signing of the Start-1 treaty in 1991 the Soviet Union had deployedsome 288 Topol missiles. Deployment continued, and at the end of 1996 a total of 360Topol missiles were deployed.

The Topol missile was deployed at previously developed deployment sites. After theINF-Treaty was signed in 1987 several SS-20 Pioneer deployment sites were adapted forthe SS-25 Topol missiles. The United States expressed specific concerns during the INFtreaty negotiations. When the SS-25 missile system was deployed in the field, with itsmissile inside the canister and mounted on the launcher, the US contended that thecanister might conceal an SS-20 missile. The one distinguishing characteristic betweenthe two systems, US treaty negotiators argued, was that the SS-25 had a single nuclearwarhead, while the SS-20 had three warheads. After considerable discussion, the SovietUnion agreed to a provision in the treaty allowing the inspecting party the right to useradiation detection equipment to measure the fast neutron intensity flux emanating fromthe launch canister. A launch canister with a missile inside containing a single warhead(SS-25) emitted a different pattern of fast neutrons than did one with a missile havingthree warheads (SS-20). In the Memorandum of Agreement of 21 December 1989, theUSSR and the U.S. agreed on procedures on how measurements would be taken duringan on-site inspection.

As the provisions of the SALT-2 agreement prohibited the deployment of more than onenew missile (which became RT-23UTTh), it was officially declared by the Soviet Unionthat the SS-25 Topol was developed to upgrade the silo based SS-13 RT-2P. The USgovernment disputed this view, contending that the missile was clearly more than 5%larger and had twice the throw-weight as the SS-13.

An SS-25 with two MIRVs may have been tested in 1991, and the missile was tested atleast once with four MIRV warheads, but no further development of a mutiple warheadversion was carried out. This became an issue during the conclusion of the 1991 STARTnegotiations, at which time the US pressed for a definition of "downloading" (removingwarheads from missiles) that would complicate any Soviet attempt suddenly to deploymultiple warheads on the SS-25.

Russia plans to to reequip approximately 400 silos in which obsolete SS-11, SS-13 andSS-17 missiles are located. Under the START-II Treaty Russia is permitted to place 90single- warhead solid fuel missiles in reequipped SS-18 ICBM silos. On-site inspectionof SS-18 heavy ICBM silo conversions, to guard against a break-out scenario involvingspeedy reconversion of SS-18 silos, is one particularly important aspect of START IIverification in accordance with the Protocol on Procedures Governing Elimination ofHeavy ICBMs and on Procedures Governing Conversion of Silo Launchers of HeavyICBMs. US inspectors could either physically witness the pouring of the five meters of

concrete in the bottom of the silo or measure silo depth before and after the concrete waspoured. Although the Treaty prohibits emplacement in such converted silos of a missilewith a launch canister greater than 2.5 meters in diameter, and the Russians haveundertaken a political commitment to deploy in these converted launchers only a single-warhead ICBMs of the SS-25 type, the possibility exists that Russia could further modifythe converted SS-18 silos to enable them to launch a different missile than the onedeclared.

The breakup of the Soviet Union had a significant impact on the Topol program. TheMinsk Wheeled Truck-Tractor Manufacturing Plant [MAZ] in Belarus manufactured themissiles' transporter launchers, and some 90% of the components of the guidance systemwere manufactured in Ukraine.

In Belarus, as of December 1995, 63 SS-25 ICBMs originally deployed there had beenreturned to Russia. As of December 1995, Belarus had two operational SS-25 mobileICBM regiments remaining on its territory, with a total of 18 nuclear warheads. In July1992, Belarus signed an agreement with Russia placing the regiments under exclusiveRussian control. In September 1993, Moscow and Minsk signed an agreement requiringthe return of these nuclear missiles and all related missile support equipment to Russia bythe end of 1996. A total of 81 SS-25 ICBMs and associated warheads were returned toRussia from Belarus.By the late 1990s the lack of resources and qualified personnel forced the Russian Navyto cut back operations considerably, with no more than one or two regiments of themobile SS-25 missiles dispersed in the field. The remaining 40 or so regiments, each withnine single-warhead missiles, remain in garrison.

SpecificationsDIA PL-5 & SS-25

NATO Sickle

Bilateral RS-12M

Service RT-2PM/Topol

OKB/Industry 15Zh58

Design Bureau (MIT) Moscow Institute of ThermalTechnology, Acad. A. D.Nadiradze

Approved 7/19/1977



First Flight test 10/27/1982 failure, 2/8/1983success

IOC 7/23/1985 authorized, 8/2/1985

operational



Warheads 1

Yield (Mt) 0.550

Payload (kg) 1,000 ? 1,200

Total length (m) 20.5 - 21.5

Total length w/o warhead (m) 18.5


Launch Weight (t) 45.1

Fuel Weight (t)

Range (km) 10,500

CEP (m) (Russian Sources) 900


Number of Stages 3


Canister length w/o front

Meters (m)

20.0



1st stage 2nd stage 3rd stage 4th. StageBus

Length (m) 8.1 4.6 3.9 2.1

Body diameter (m) 1.86 1.55 1.34 0.8


Dry weight (t)


Propellants Solid Solid Propellant Solid

Propellant

Burning time (sec.)



Basing Mode Road-Mobile/Silo

Launch Technique Mortor/Cold


Test Boosters 5


Training Launchers

Space Booster Variant START-1

Deployment Sites


Irkutsk

Kansk

Krasnoyarsk Gladkaya

Lida

Mozyr?

Nizhniy Tagil Verknyaya Salda

Teykovo Teykovo

Yoshkar Ola Yoshkar Ola

Yur?ya Yurya

SS-25/RS-12Min LaunchCanister

Launch-Associated

SupportVehicle

SS-25/RS-12MRoad-Mobile

LauncherVersion A


LauncherVersion B


LauncherVersion A

with Missile

SS-25/RS-12M Road-MobileLauncherVersion B

with Missile

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SS-25/RS-12M, Stage 1 Driver Training Vehicle 1.0 Driver Training Vehicle 1.1

Fixed Structure for Road-MobileLaunchers

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RT-2UTTH - Topol-MSS-27

The single-warhead RT-2UTTH Topol-M is an advanced version ofthe silo-based and mobile Topol intercontinental ballistic missile.The SS-25 Topol is generally similar to the American Minuteman-2,while the more sophisticated SS-27 Topol-M is comparable to theAmerican Minuteman-3. The Topol-M is 22.7 meters (75 feet) longand has a diameter of 1.95 meters (6 feet 3 inches). The missileweighs 47.2 metric tons and has a range of 11,000 kilometers (6,900miles). The solid-propellant three-stage Topol-M missile complex,with a standardized (silo and mobile) missile, is to become thefoundation of the Russian strategic nuclear forces in the 21stcentury. It is planned to accommodate Topol-M both on self-propelled launchers as well as in silos. High survivability of themobile complex is achieved by the capability of offroad movement,of a continuous change in location and of a missile launch from anypoint along the movement route.The Moscow Institute of Heat Engineering (MIT) State Enterprise isthe only plant in Russia building such missiles today. Themodernized 45-ton Topol-M is the first strategic missile to be builtby Russia without the participation of Ukraine and CIS countries.The first test firing of a Topol-M took place on December 20, 1994.The flight and design testing of the Topol-M was successfullycompleted in 1995, and joint flight-testing is continuing, leading to a

decision to commence series production. All the launches have been a success, but large-scale serial production has not started due to a shortage of funds. On 08 July 1997 thefourth launch of a Topol-M ICBM was successfully made from the Strategic MissileForces' Plesetsk State Test Site within the framework of joint flight-testing. The eighthtest of the Topol-M missile was conducted on 03 September 1999. The missile waslaunched from Plesetsk, north of Moscow, and landed at the Kura testing site onKamchatka. On 10 February 2000 Russia successfully completed the tenth test flight ofthe Topol-M. The missile was launched from the Plesetsk cosmodrome to a target at themilitary base in Kura, on the Kamchatka peninsula in the Russian far east, 8,000kilometers away. On 27 September 2000 Russia test-fired another Topol-M, sending theSS-27 on a 4,000-mile flight from the Arctic base of Plesetsk in northern Russia to itsintended target in the Russian Far East. In this 12th test, the missile was fired from amobile launcher, rather than from a silo. It was the second SS-27 missile test in two days.

Topol-M silo lidWork on the new Topol-M ICBM is lagging seriously behind the initial timetable.Defense state order financing for the next decade provides that by 2003 there will be onthe order of 250-300 Topol-M missiles in service. A total of 1.5 trillion [old] rubles wereincluded in the 1997 budget for the development of the Topol-M missile complex. TheRussian Missile Troops are permitted to have 300 Topol RS-12M mobile missiles underthe START II Treaty, and the RVSN must acquire two Topol-M regiments annually up to2001, which will cost 3.7 billion new rubles. The Strategic Missile Force plans to deploymobile Topol-M missile systems at the end of 2002 or early in 2003. A total of R700billion would be required to place 450 Topol-M missiles in service by 2005 to maintainparity under START II. But the present 55 percent funding will permit production of atthe very most 10-15 missiles at this facility each year year. As a result the StrategicMissile Troops would have a total of approximately 350-400 ICBM warheads, not the800-900 which are permited within the framework of the START II Treaty. On 15 April1998 Acting Prime Minister Sergey Kiriyenko approved a schedule of monthly budgetappropriations for the Topol-M, which he noted would make up the core of Russia'sstrategic nuclear forces.

In December 1997 after four test launches, the first two Topol-M systems were put onalert for a trial period with the Taman Division at Tatischevo in the Saratov region. As oflate July 1998 two more Topol-M launch sites were completed and were awaitingacceptance trials. Russia put a regiment of 10 Topol-M missiles on duty in 1998. By thattime the Strategic Rocket Forces had carried out 6 successful test launches. A secondregiment of another 10 missiles entered service in December 1999. A third regiment, of10 Topol-M missiles will be deployed in 2000.

The Topol-M missile system is being commissioned in the Russian strategic nuclearforces' grouping regardless of whether heavy missiles are stood down from combat alertduty or not. It is intended that the Topol-M ICBM grouping will comprise an equalnumber of mobile and silo-launched missiles. Some 90 of the 360 launch silos vacated bythe RS-20 ICBM's, which are being stood down from combat alert duty, need to beconverted for the latter. Apart from Saratov Oblast the Topol-M systems will be deployedin Valday, the southern Urals, and the Altay.

The START II strategic arms reduction treaty, signed with the United States in 1993 butnot yet ratified by Russia's parliament, calls for Russia to replace its SS-18 missiles,which have multiple warheads, with single warhead missiles such as the Topol-M.Although deployed with a single warhead, the Topol-M could be converted into amultiple-warhead missile, which was prohibited by the START II treaty. Topol-M could

carry at least three and perhaps as many as six warheads. The Topol-M missiles could betransformed into missiles with multiple reentry vehicles [MIRV's], since their throwweight allows accommodating 3-4 warheads on a missile. The warheads could be takenfrom some of those ground-based and naval missiles which will be withdrawn from theorder of battle in coming years. The Topol-M can carry a maneuverable warhead, whichwas tested in the summer of 1998. Topol-M also has a shorter engine-burn time, tominimize satellite detection on launch.

SpecificationsDIA SS-27, SS-X-29, SS-25B

NATO

Bilateral RS-12M2

Service RT-2PM2, RT-2PM-OS

OKB/Industry 15Zh??

Design Bureau (MIT)Moscow Institute of ThermalTechnology

Approved 2/ /1993

Years of R&D 1993 - 1997

Engineering and Testing 1994 - 1997


IOC 1997



Warheads 1

Yield (Mt)

Payload (kg) 1,000 - 1,200



Missile Diameter (m) 1.86 - 1.95

Launch Weight (t) 47.2 - 47.21

Fuel Weight (t)

Range (km) 10,000 -10,500


CEP (m) (Western Sources) 350+

Number of Stages 3

Canister length (m) 21,2 - 23.0

Canister length w/o

front meters (m)

19.44



1st stage 2nd stage 3rd stage 4th. BUS

Length (m) 8.04?

Body diameter (m) 1.86 - 1.95 1.61 1.58


Dry weight (t)

Design Bureau for theSolid Motors

MIT, NPOSoyuz

MIT, NPOSoyuz

MIT, NPOSoyuz

Engine Designation


Solid Propellant SolidPropellant

Burning time (s)


Specific Impulse (m/s)

Basing Mode Silo/Ground mobile

Hardness

Launching Technique

Deployed boosters

Test Boosters

Warheads Deployed

Deployment Sites

Training Launchers


RT-23 / SS-24 SCALPELComparable in size and concept to the US Peacekeeper, the SS-24 is cold-launched with10 warheads. The missile is deployed both as rail-mobile and silo-based. The silo-basedSS-24 was intended to replace the SS-19 Stilletto in the Russian strategic inventory. TheSS-24 rail missile systems is subject to elimination under the provisions of the START-IITreaty.

The RT-23UTTh is a solid-propellant missile with three stages within a constant diameterbody. The first stage of the silo-based missile uses a rotating nozzle, whereas therailway–based version is equipped with a fixed nozzle partially inserted in the motorcombustion chamber. The engines of the second and third stages deploy extendablenozzles during flight to increase the motor's specific impulse without the need to increaseof the overall dimensions of the missile. During the first stage flight control is attainedthrough deflection of the sustainer nozzle, and during the second and third stage bydeflecting the combat stage and by fairing-mounted aerodynamic vanes.

Both silo-based and rail-mobile missiles have an autonomous inertial guidance systemusing an onboard digital computer. The silo-based system uses a two-package block ofcontrol instruments made of radiation-resistant electronic elements. The railway-basedmissile has only one-package block of control instruments.

A total of 10 warheads [each with a yield of 550 KT], a post-boost vehicle with aguidance/control system and a propulsion system are inside the nose cone. Theguidance/control system provides a CEP of 500 meters according to unofficial Russianestimates, which gives the missile a hard-target-kill capability. The missile is deployed ina transport-launching canister from which it is launched through the mortar starttechnique. To conduct a railway launch the sliding roof of the car opens, the container iserected and the missile is launched with the help of a solid propellant gas generator. Themissile can be launched from any point of the route.

The length of the two versions are the missile were determined by the dimensions of thesilo or the railway launcher. The silo-based missile therefore has a nose cone tip flap thatis activated when the launch is initiated while the railroad based missile has a folded nosecone that is extended when the launch is conducted.

The creation of the RT-23 UTTh was the culmination of a long-term effort to create asolid-propellant ICBM for multiple basing modes which was initiated on 13 January1969.

15Zh44 - SS-24 PL-4 The difficulties with which the developing institute KBYuzhnoye (OKB-586) was confronted during the development of the railway-based SS-24 led to a redefinition of the task on 23 July 1976. Only a silo-launchedversion of the RT-23 was considered. The preliminary design was completed inMarch 1977 but it was considered unsatisfactory, and in December 1979 a second

design with an improved propulsion system and a front end was finished. The newdesign provided using reentry vehicles that were identical to that of the R-36M /SS-18 missile. The suspended activities to build a railway based RT-23 (15Zh52)missile were resumed, and this design was finished in June 1980. The flight-design tests of the silo-launched RT-23 (15Zh44) began on 26 October 1982. As aresult of several failures during the flight-tests, this version was cancelled on 10February 1983 by the Soviet Defense Ministry.

15Zh52 - SS-24 Mod-0 On 09 August 1983 a further effort to develop a silo,railway and road-mobile missile designated as RT-23UTTh was approved, but theroad-mobile stationing mode was subsequently abandoned. The tests of therailway based RT-23 (15Zh52) were successfully completed in April 1985, and inNovember 1987 it was experimentally adopted.

15Zh61 - SS-24 Mod-1 The RT-23UTTh tests of the railroad SS-24 Mod-1version (15Zh61) that is almost identical to the 15Zh52 began on 27 February1985 and were finished in December 1987 The deployment of these missilesstarted on 28 November 1989, and the first regiment with railroad-based missileswas put on alert on 20 October 1987. Altogether 36 railway-based RT-23UTThmissiles were initially deployed. They were deployed in three garrison areas: 12launchers at Kostroma (400 km east of Moscow), 9 launchers at Bershet (1,250km east of Moscow), and 12 launchers at Krasnoyarsk in Siberia. The MilitaryRailroad Missile Complex (Boyevoy Zheleznyy Raketnyy Kompleks BZhRK)consists of three launch cars [each with a single missile], a command and controlcar, cars for personnel, and several diesel locomotives. The rail-mobile versioncould operate on any Soviet rail line that was unobstructed by overhead electricalpower lines, a total of 145,000 km of track.

15Zh60 - SS-24 Mod-2 The silo-based version (15Zh60) known as SS-24 Mod-1was tested from 31 July 1986 through November 1988. The deployment of thesemissiles in silos formerly occupied by SS-17 Sego ICBMs, started on 28November 1989, and the first regiment of silo-based missiles was activated on 19August 1988. Altogether 56 silo-based RT-23UTTh missiles were initiallydeployed, with 10 at Tatishchevo in Russia and 46 at Pervomaysk in Ukraine.

The US Defense Department stated in September 1991 that production had ended withapproximately 90 missiles deployed. A total of 46 silo-based RT-23UTTh missileslocated in Ukraine were phased out and dismantled in compliance with the provisions ofthe START-1 treaty. They were denuclearised and their warheads have been transferredto Russia. By 1994 most of the rail-mobile systems remained in garrison due to lack offunding. By April 1997 10 silo-based and 36 railway based RT23-UTTh missiles werestill deployed on Russian territory. Following Russian ratifiication of the START-2 treatyin early 2000, all RT-23 UTTh missiles are subject to dismantling.

With the breakupof the Soviet Union in 1991, most design and production facilities forthe SS-24 belonged to Ukraine. Ukraine had no interest in continuing to produce theseICBMs, and the production line was closed in 1995.

It has been suggested that these rail-mobile land-based missiles, which have been parkedin their garrisons, may be placed back on patrol in response to American missile defenseand associated arms control initiatives.

SpecificationsR & D Mod- Mod-2 Mod-1

DIA SS-24PL-04

SS-24 SS-24V SS-24

NATO Scalpel Scalpel Scalpel Scalpel

Bilateral RS-22B RS-22A RS-22V

Service RT-23 RT-23 RT-23 UTTKh RT-23 UTTKh

OKB/Industry 15Zh44 15Zh52 15Zh60 15Zh61

Design Bureau SKB-586,NPOYuzhynoyAcad. V.F. Utkin

SKB-586,NPOYuzhnoyeAcad. V.F. Utkin

SKB-586,NPOYuzhnoyeAcad. V. F.Utkin

SKB-586,NPOYuzhnoyeAcad. V. F.Utkin

Approved 7/23/1976 6/1/1979 8/9/1983 8/9/1983

Years of R&D 1/1969?3/1977

11/1982 -1987

1983 - 1989 1983 - 1989


1985-87

First Flight Test 10/26/82Failure,12/1982Success

4/ /1984 7/31/1986 2/27/1985

IOC canceled 10/20/87 8/19/1988 12/1987

Deployment Date Canceled 11/ /1987 11/28/1989 11/28/1989

Type of Warhead MIRV MIRV MIRV MIRV

Warheads 10 10 10 10

Yield (Mt) 0.55 0.35 -0.55

0.35 -0.55 0.3 -0.55

Payload (t) 4.05 4.05 4.05 4.05

Total length (m) 23.3 23.4 -23.8

18.8 - 23.4 23.3

Total length w/o 18.8, 19 19 19 19

warhead (m)

Missile Diameter(m)

2.4 2.4 2.4 2.4

Launch Weight (t) 104.5 104.5 104.5 104.5

Range (km) 10,000 10,000 -11,000

10,100 -11,000

10,100 -10,450


500 500 500 500


150-250 150-250 150-250 150-250

Basing Mode Silo Silo Railroad

Number of Stages 3

Canister length (m) 21.0 - 22.4

Canister length w/o

Front meters (m)

19.4


Booster guidance system Inertial autonomous

1 Stage 2ndStage

3rd Stage BusStage

Length (m) M1 9.7 4.8 3.6

Length (m) M2 9.5

Body diameter (m) 2.4 2.4 2.4 2.4

Fueled weight (t) M2 52.5

Fueled weight (t) M1 53.7

Dry weight (t)

Design Bureau

Solid Motor Designation 15D305 15D339


SolidPropellant

SolidPropellant

Burning time (sec.)

Solid Motor Thrust SeaLevel/Vacuum (Tonnes)

?/210 107 21

Specific Impulse (sec.)

Hardness

Launching Technique Cold


Test Boosters


Training Launchers

Space Booster Variant Yes, concept only Space Clipper

Deployment Sites


Kostroma Kostroma

Pervomaysk Pervomaysk

Tatishchevo Tatishchevo

Bershet Bershet

Krasnoyarsk Krasnoyarsk



SS-24/RS-22 (silo)Emplacement Equipment

SS-24/RS-22 (silo) in LaunchCanister

SS-24/RS-22 (silo), Stage 1

SS-24/RS-22(rail-mobile)

in LaunchCanister

S-24/RS-22(rail-mobile),

Stage 1

SS-24/RS-22Rail-Mobile Launcher

SS-24/RS-22 Launch-AssociatedRailcar 1

Launch-Associated

Railcar (1.1)

SS-24/RS-22 Launch-Associated Railcar 2

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SS-24/RS-22 Launch-Associated Railcar 2.1

Fixed Structurefor Rail-Mobile

Launchers

RSS-40 KuryerOn 6 October 1991 the USSR rejected development of a new small, mobile ICBMundertaken by the Moscow Institute of Heat Engineering (MIT) State Enterprise. TheKuryer was in no way inferior to its American analog, the small, mobile Midgetmanmissile complex. This system could have taken the place of Topol-M. The complex wasfully prepared for flight tests, but the political leadership yielded to the United States atthat time and did not permit them to be conducted. Nevertheless, the basic components ofthe complex were tested piecemeal. This missile was being developed to include newmaterials, fuel, a control system and other new design and technological solutions.

Burya La-350Buran RSS-40A design for an experimental cruise missile (EKR) with a cruising speed of Mach 3 and arange of 1,300km was developed at the OKB of S. Korolev in 1951-53. It was to consistof a booster with [liquid-fueled rocket engines (derived from the R-11 rocket withstorable fuel) and a cruising stage with a supersonic ramjet engine (SPVRD) developedby the OKB of M. Bondaryuk. The technical challenges of intercontinental cruisemissiles (MKRs) were not as great as those for ballistic missiles of such long range. Acelestial navigation system could provide adequate accuracy for hitting targets.

On 20 May 1954 a ministerial decree authorized the development of two parallel projects.The Burya was assigned to the OKB of S. Lavochkin [which had experience insupersonic fighters], and the Buran was the project of the OKB of V. Myasishchev[which was established to develop long-range bombers]. Myasishchev's Buran wasdesigned for a larger warhead than the Burya, and had a large takeoff mass and thrust.The work of the Lavochkin on the Burya OKB moved quickly, and by 1956, when theMyasishchev OKB was finishing the design engineering of the Buran, the first models ofLavochkin's Burya had already been created.

The flights of the Burya began in July 1957, at the same time as the flight testing of theR-7 ICBM developed by the Korolev OKB. The Soviet leadership decided soonafterward to curtail the work on the Buran. The final flight of the Burya was conductedon 16 December 1960, following which further work was discontinued.

Although the source of the information is uncertain, American publications beginningaround 1960 made reference to a "large winged antipodal T-4A bomber underdevelopment in the USSR," and even included drawings. However, by the mid-1960s allreferences in the open literature to such projects vanished, suggesting that such projectswere merely Cold War rumors. The fact of the existence of these projects was notconfirmed in the open literature until the end of the Cold War, and the provenance of theearly reports remains obscure.

SpecificationsCharacteristics Navaho Burya Buran

Launch mass, tonnes 66.2 96 125

Mass of warhead, tonnes 2.25 2.19 3.50

Total length of system, meters 25.1 19.9 24.0

Boosters

Quantity 1 2 4

Length, meters 23.1 18.9 19.1

Diameter of body, meters 1.83 1.45 1.20

Thrust at launch, tonnes of force 128.45 2 x 68.61 4 x 55

Fuel Components:

oxidizer liquid oxygen nitric acid liquid oxygen

combustible ethyl alcohol amines kerosene

Cruising Stage:

Length, meters 20.7 18.0 23.3

Diameter of body, meters 1.83 2.20 2.40

Wingspan, meters 8.72 7.75 11.6

Wing area, meters2 38.9 60 98

Number of SPVRDs 2 1 1

Diameter of SPVRDs, meters 1.22 1.70 2.00

Cruising thrust, tonnes of force 2 x 3.94 7.65 10.6

Maximum range of flight, km 5,400 8,500 8,500

Cruising altitude of flight, km 22-24 18-20 18-20

Cruising speed of flight, Mach 3.25 3.10 3.10

Start of development 1950 1954 1954

Date of start of flight testing 6 Nov 56 1 Jul 57 -

Total number of launches 11 17 -

of which, failed 10 3

Date of end of flight testing 18 Oct 58 16 Dec 60 -

Shutdown of project July 1957 December 1960 -

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R-11FM / SS-1b ScudThe first Soviet SLBM, the liquid-propellant missile R-11FM, was a modified version ofthe R-11 Scud-A. This single-stage missile with a nonseparable warhead was equippedwith a single-chamber liquid rocket engine and a pressurized fuel supply system. Flightcontrol was accomplished with control jet motors and four aerodynamic stabilizers. Themissile was deployed in a dry tube that penetrated the hulls of the submarine. The launchwas conducted from the surface, prior to which the missile was elevated to the edge ofthe tube and fixed with the help of special racks. Unlike the R-11, the R-11FM featured ahermetically sealed instrumental and propulsion compartment and a command stucturecapable of receiving data from the navigation system of the submarine on launch..

The development of the R-11FM was authorized by the government on 26 January 1954.S.P. Korolev who was at that time chief designer of OKB-1 NII-88 was assigned thedevelopment of the D-1 launch system and the R-11FM missile. Other institutionsworking on the project included: NII-885 Minraliopoma (command structure, chiefdesigner N.A. Pilyugin), OKB-2 HII-88 (propulsion systems, chief designer A.M.Irayev), NII-49 (navigation systems, director N.A. Charin), МNII-1 (navigationsystems, director E.I. Ellyer), OKB-34 (creation of the dynamic platform, chief designerYe. G. Rudyak).

The development of the R-11FM missile was carried out in three phases. The first twotook place at the State Central Taining Site Number 4 at Kapustin Yar, during which themissile was launched from a fixed and then from a dynamic platform. . During Septemberand October 1954 three missiles were launched from a fixed platform similar to thedesignated submarine launcher. Between 25 May and 30 July 1955 a total of 11 launcheswere conducted from a dynamic platform. The third phase of tests were carried out on asubmarine The first submarine launch was successfully completed on 16 September1955,from the submarine "B-67" of the V-611 (Zulu) class, located in the White Sea close tothe Kola peninsula. Seven of the eight tests between 16 September and 13 October 1955were successful.

In August 1955 the R-11FM project was transferred to SKB-385 in Zlatoust. Chiefdesigner V.P. Makyeyev of SKB-385 was responsible for creating the designdocumentation, conducting modifications and and flight tests, to adjust series productionand to deliver the missile.

To ensure combat readiness after long periods of on-board storage, service tests of themissile and launch system were conducted in August and October 1956 by the Northernfleet. The first long-range patrol of the "B-67" submarine with R-11FM missiles began on16 August 1956. Covering a route through the White and Barents seas, the boat sailedsurfaced and submerged at various speeds, spending two days on alert and conductingmissile fiings afterwards. On 12 September and 03 October 1956 missiles that had beenstored onboard the submarine for 37, 47 and 82 days were successfully launched.

After these tests, OKB-1 participated in the improvement of the missile and acted asarchitectural supervisor whereas SKB-385 assumed responsibility for all furtheractivities. The missile documentation was completed in late 1956 and preparation forserial production was initiated. In 1957 manufacturing of propulsion systems and missilesto be tested from a fixed platform began. After they were completed the missile was test-launched from a dynamic platform in the autumn of 1957. The last test phase betweenMarch and May 1958 consisted of four submarine launches, of which three weresuccessful.

Deployment of the R-11FM missile began on 20 February 1959 on the 611AB [ZULU V]and 629 [GOLF I] class submarines.

Although the R-11FM missiles were designed to use RDS-4 nuclear explosives, it isreported that during regular patrols they were not equipped with nuclear explosives. Thenuclear warheads were stored at the coast, to be transferred to the submarines in times ofcrisis. Between 1958 and 1967 a total of 77 missile firings were conducted of which 59were successful. In 1967 the D-1 launch system and the the R-11FM missiles werewithdrawn from operational service.

Western intelligence in the 1960s was evidently somewhat confused by the relationshipbetween the R-11FM and R-13 programs. Despite the differences in the physical designsof these missiles, the R-11FM was regarded as simply the interim reduced-range versionof the longer range R-13 follow-on.

SpecificationsDIA SS-1b

NATO Scud

Bilateral

Service R-11FM

OKB/Industry 8K11/8A61FM

Design Bureau OKB-1 NII-88/SKB-385

Approved

Years of R&D


First Flight Test

IOC

Deployment began 2/20/1959

Launch system D-1/D-2

Submarine 611 AB Zulu V

Type of Warhead Single, inseparable

Warheads 1

Yield (mt) 0.1/0.5

Payload (t) 975-1000




Launch Weight (t) 5.4-5.6

Fuel Weight (t)

Range (km) 150/167

CEP (m) (Russian Sources) 1.5 km on range, 0.75 on azimuth

CEP (m) Western Sources)

Number of Stages 1

Warheads Deployed


Engine Designation

Propellants Liquid

Fuel Kerosene T-11

Oxidizer 20% UDMH 80% Nitrogen Acid

Burning time (s)

Verniers Thrust Sea Level/Vacuum(kn)

Specific Impulse (s)

Launching Technique Surfaced

R-13 / SS-N-4 SARKThe R-13 was a single-stage storable liquid-propellant missile with a separablemonoblock reentry vehicle. Equipped with a single combustion chamber rocket enginewith turbopumps, it had a four-chamber flight control engine. The R-13 was the firstSoviet SLBM to use such vernier engines for flight control instead of gas or aerodynamiccontrol surfaces. Additionally, to stabilize the missile in early flight, four aerodynamicstabilizers were used. These were considerably smaller than the fins used on the R-11FM.The SS-N-4 could deliver a 2800-lb reentry vehicle a maximum operational range of 300nm. The reentry vehicle had a nuclear warhead with a yield estimated in the west at 1.2 to2.0 MT, though Russian sources place the yield at 1.0 MT. It had an inertial guidancesystem and a CEP of 1 to 2 nm according to western intelligence estimates.

Western intelligence in the 1960s was evidently somewhat confused by the relationshipbetween the R-11FM and R-13 programs. Despite the significant differences in thephysical designs of these missiles, the R-11FM was regarded as simply the interimreduced-range version of the longer range R-13 follow-on.

The short range of the R-11FM missiles rendered submarines armed with this missilevulnerable to antisubmarine defense systems, highlighing the need for a longer-rangesystem. On 25 August 1955 the governmental ordered the development of a sea-basedballistic missile with a range of 400-600 km carrying a nuclear warhead. The D-2 launchsystem with R-13 missiles was authorized on 11 January 1956. In early 1956 OKB-1 NII-88 finished the the preliminary design, after which the project was transferred TO SKB-385, which conducted all further activities. The design was completed in 1957 and inDecember 1958 the engine tests of the R-13 missile began. Between June 1959 andMarch I960 flight tests of the R-13 on fixed and dynamic platforms were conducted onthe State Central Training Site in Kapustin Yar. Submarine tests began in November1959 and were completed in August 1960. Altogether 15 out of 19 launches weresuccessfully carried out at the training site and 11 out 13 on submarines. During the timethe R-13 missile was deployed (1960-1972) 225 out of 311 launches were conductedsuccessfully.

The D-2 launch system and the R-13 missiles were deployed on 13 October 1961 on 629-class Golf and 658-class Hotel submarines. Several improvements were implementedthereafter, with the missiles' combat readiness increased from three to six months, anddepot storage time was increased to seven years. The SS-N-4 was believed to have beenassigned both a peripheral and an intercontinental mission in the past. Peak operationaldeployment was reached in 1962, with phase-out from the intercontinental missionbeginning in 1964 and phaseout from the peripheral mission beginning in 1967. By 1973the missile was believed to be assigned only a peripheral mission and was carried onlyaboard the Golf-I Class diesel-electric submarine, which required surfacing beforemissile launch. The normal reaction time is 20 to 25 minutes. The reaction time underconditions of peak alert is six to eight minutes, and the allowable hold time under theseconditions is about one hour.

SpecificationsDIA SS-N-4

NATO Sark

Bilateral

Service R-13

OKB/Industry 4K50

Design Bureau SKB-385

Approved

Years of R&D


First Flight Test 1959

IOC


Launch system D-2/D-3

Submarine Golf & Hotel class


Warheads 1

Yield (mt) 1

Payload (t) 1.6




Diameter of Stabilizers (m) 1.9


Fuel Weight (t)

Range (km) 600

CEP (m) (Russian Sources) 4,000

CEP (m) Western Sources) 1,800 - 3,900

Number of Stages 1

Warheads Deployed

Booster guidance system

Engine Designation

Propellants Liquid

Fuel AK-27I

Oxidizer TG-02

Burning time (s)



Launching Technique Surfaced


Zulu Class submarine modified for two SS-N-4 missiles mountedin sail, for SLBM test program 1955

Missile flight test program began 1956

Initially deployed aboard Zulu Conversion submarine 1957

IOC for early model of reduced range 1958

IOC for full-range model 1960

Peak operational deployment (105 missiles aboard 37 submarines) 1962

Missile production terminated Mid-1964

Beginning of phase out 1965

Phase out of Golf-I Class submarines and SS-N-4 SLBMs complete January1975

R-15The R-15 missile, which was supposed to have a range of about 1,000 km, was developedby OKB-586 at Dnepropetrovsk. Unlike the D-1 and D-2 launch systems, with the D-3launch system the R-15 missile would be fired directly out of the missile tube withoutprevious elevation of the missile.

In 1955 chief designer V.P. Funikov of SKB-143 [now MBM Malakite] undertook thedesign of a nuclear powered submarine [designated Project 639] with a displacement of6000 tons that was intended to carry three R-15 missiles. The development of the D-3launch system was officially authorized on 20 March 1958. During 1958 OKB-16developed a design for a diesel-engine electric submarine able to carry one R-15 missile.Because of the large overall dimensions and weight of the missile, these systems hadpoor technical and tactical characteristics. Consequently, the development of the R-15missile, the D-3 launch system and the submarines was canceled in December 1958 whilethey were still on the drawing board.

R-21 / SS-N-5 SERBThe R-21 / SS-N-5 submarine-launched ballistic missile is a single-stage, storable liquid-propellant missile. The D-4 launch system used the "wet launch" technique, under whichthe missile tube had to be filled with water before launch. The missiles could be firedunderwater and were intended to replace the D-2 launch system on board the Golfsubmarines. According to Western intelligence estimates, the missile could deliver a2800-lb reentry vehicle having a 2.0-3.5 MT warhead a maximum operational range of700 nm. It had an inertial guidance system, and a CEP estimated by western intelligenceof 1 to 2 nautical miles.

The SS-N-5 was carried aboard both the Golf-II Class diesel-electric submarine, whichwas believed to be assigned a peripheral mission, and the Hotel-II Class nuclearsubmarine, which were assigned a strategic mission. Both submarines can launch missileswhile fully submerged and underway at about five knots. The normal reaction time is 15to 20 minutes, and their action time under conditions of peak alert is one to two minutes.The allowable hold time under peak alert conditions is about one hour. Initial operationalcapability was reached in 1963.

The project to construct an underwater launched missile started as early as 1955 andconcentrated on the R-11FM missile. On 03 February 1955, E.V. Charnko, the chiefdesigner of OKB-10 NII-88, was assigned responsibility of developing the missile, andthe chief designer of SKB-626, N.A. Ryemihatov, was responsible for developing thesubmarine infrastructure.

The development program conducted in three phases. First, R-11FM dummies were firedfrom a fixed underwater tube, then dummies were launched from tubes located on theoutside of the submarine and finally full scale test firing from a sailing submarine. Forpop-up tests, two R-11FM dummies were designed: the С4.1 and the C4.5. The first missile launch from an underwater platform was conducted on 23 December 1956. Thespecially modified "S-229" Whiskey submarine, re-designated B-613, conducted testswith a dummy missile while the submarine was submerged at a depth of 15-20 metersand sailing at a speed of 3-4 knots. Three С4.1. dummy launches were conducted in the Black sea in June 1957.

The development of the new D-4 launch system with R-21 missiles was authorized on 20March 1958. Originally, OKB-586 and its chief designer M.K. Yangel was charged withthe project but on 17 March 1959 the program was transferred to SKB-385.

After the development of the R-21 missile was authorized in 1958, the R-11FM missilecontinued in use for further tests. The modified R-11FM, designated C4.7, was used inthe third series tests, of launches from submerged submarines, that began in July 1959.Prior to the conclusion of the second phase of tests, the Ministerial Council had directedthe conversion of the "B-67" V-611 submarine to carry out the third test phase. The firstС4.7 missile firing in August 1959 from the "B-67" submarine was a failure, delaying

further tests by a year. The second test flight on 16 August1960 also ended in failurewhen the tube filled with water and the missile fell from the launch pad and crushed itsnose cone. The third submarine launch on 10 September 1960 was successful.

The K1.1 missile, a less powerful experimental version of the R-21 SS-N-5 SERBmissile, was tested in parallel to the C4.7 test program. Pop-up tests of the K1.1 missilewere conducted in the Black Sea from a 40-50 m deep fixed floating platform and the "S-229" submarine. Six launches from a platform and three from a submarine were carriedout between May 1960 and October 1961. The K1.1 missile was publicly displayed inparades in Red Square, and incorrectly identified in the West as the SS-N-5 SERB. Infact, it was a prototype missile tested in association with the development of theoperational SS-N-5.

The 629B Golf II submarine was built for testing the D-4 launch system, Joint testingbegan in February 1962 and the first underwater launch took place on 24 February 1962.A total of 27 missile launches were conducted during these tests.

On 15 May 1963 deployment of the D-4 launch system on Golf and Hotel submarinesbegan. The R-21 remained in operational service from 1963 to 1989, during which time193 out of a total of 228 launches were successful. Over this period the service life of thefueled missile was increased from six months to two years.


Estimated start of Golf Class submarine conversion January 1960

Beginning of preliminary flight testing 1961

Estimated start of underwater ejection tests 1961

Beginning of integrated system tests Late 1961

First launch detected March 10, 1962

Estimated start of Hotel Class conversion Mid-1963

IOC of Golf-II Class submarines Late 1963

IOC of Hotel-II Class submarines 1964

Peak operational inventory (57 missiles aboard 19 submarines) 1971


NATO Sark

Bilateral

Service

OKB/Industry 4K55

Design Bureau OKB-586/SKB-385

Approved

Years of R&D



IOC


Launch system D-4 with 3 missiles

Submarine Golf-II / Hotel II

Warheads 1

Yield 0.8-1.0 MT - Russian sources2.0-3.5 MT - Western sources

Payload (kg) 1,200



Missile Diameter (m) 1.3-1.4

Diameter of Stabilizers (m)


Fuel Weight (t)

Range (km) 1400

CEP (m) (Russian Sources) 2,800

CEP (m) Western Sources) 1,800 - 3,900

Number of Stages 1

Warheads deployed


Engine Designation

Propellants Liquid

Fuel

Oxidizer

Burning time (s)



Launching Technique Underwater

Firing conditions: Sea state - Up to 5Submarine Speed, kn - 4 (at 40to 50m depth)

R-27 / SS-N-6 SERBThe R-27 / SS-N-6 submarine-launched ballistic missile is a single-stage, storable liquid-propellant missile. Three variants were deployed using an inertial guidance system, whilea fourth variant [the SS-NX-13] used radio command guidance. One of the inertially-guided variants carried multiple re-entry vehicles [MRV] that were not independentlytargetted.

The missile was first seen publicly in a Moscow parade in 1967. By the mid-1970sWestern intelligence believed that the SS-N-6 Mod 1 delivered a 1500-1b reentry vehicleto a maximum operational range of 1300 nm with a CEP of about 0.6 nm. The SS-N-6Mod 2 was believed to deliver a 1,500-lb reentry vehicle to a maximum operational rangeof 1,600 nm. The SS-N-6 Mod 3 was assessed as having MRV payload consisting of two600-lb RVs or three 400-lb RVs. Both the Mod 2 and Mod 3 were thought to have a CEPof about 0.7 nm. The yield of the single RV Mod 1 and Mod 2 was believed to be 0.6 to1.2 MT. The yield of each warhead in the 2-MRV variant of the Mod 3 was estimated at0.4 to 0.8 MT, and the yield of each warhead in the 3-MRV variant at 0.1 to 0.4 MT. Theexistence of a 2-MRV variant of the Mod 3 is not reported by Russian sources.

Sixteen of the SS-N-6 missiles were carried aboard the Yankee class nuclear submarine.Missiles could be launched while the submarine was submerged and underway.According to Western estimates, normal reaction time, while the submarine wassubmerged on patrol, was about 15 minutes. Reaction time under conditions of peak alertis one minute. The allowable hold time under conditions of peak alert was one hour. TheYankee submarine demonstrated a patrol capability of 75 days, and patrols of longerduration (90 days) were believed possible, consistent with crew provisioning and morale.

The D-5 launch system with R-27 missiles originated with studies by SKB-385 in theearly 1960s to develop a ballistic missile capable of attacking sea-based targets.Development work resulted from a proposal by SKB-385 in late 1961 for thedevelopment of a launch system with a light single-stage missile for strikes againststrategic land targets. The Yankee I submarnes were the designated carrier. On 24 April1962 the project was officially authorized.

One distinctive innovation in this design was the placement of the rocket engines withinthe fuel tank in order to reduce the external dimensions of the vehicle. The missile bodywas made of aluminium alloys, and the fuel and oxidizer tanks had common bottoms.The command and control avionics systems were was placed in a hermetically sealedcontainer in the lower interior of the oxidizer tank, eliminating the need for a separateinstrument module. Another design innovation was the placement of the commandsystem's sensors on a gyro-stabilized platform. These design features characterize allsubsequent liquid-propellant SLBMs developed by SKB-385.

The propulsion system has a single-chamber sustainer and a dual-chamber control engine.The thrust chambers of the attitude control engine were oriented at an angle of 45 degrees

from the stabilization axis of the missile (instead of the usual scheme in which the fourthrust chambers are aligned along the stabilization axis). Due to an increased thrust ratiothe R-26 missile had four times the range of the R-13 missile (2400 km against 600 km)despite its similar launching weight (14.2 versus 13.7 tons).

The missile was loaded in the launching tube with the use of several metallized rubbershock absorbers. Together with the lack of aerodynamic stabilizers, this allowed asignificant reduction in the overall dimensions of the launch tube. The missile was firedfrom a flooded tube. A gas bubble generated by the missile's docking adapter dampenedthe hydraulic shock caused by engine ignition in the tube.

Testing of the D-5 launch system took place in three phases. During the first phase 12pop-up tests were conducted from a flooded platform and a converted 613 submarine.Data from these tests was used to perfect underwater launch, rocket engine and launchtube designs. The second phase from June 1966 through April 1967 consisted of 12successful launches (out of 17) from a ground platform. The test phases concluded with 6missile firings from 667А submarines of the Northern fleet. Deployment began on 13 March 1968.

On 10 June 1971 it was decided to upgrade the D-5 launch system and the R-27 missiles.The modernized missile, with a more powerful engine and improved guidance system,was designated as R-27U and the launching system received the designation D-5U. TheR-27U was designed to carry both single and multiple warheads. The upgraded missilewas supposed to have the same maximum range as the original R-27, though equippedwith three multiple reentry vehicles. The range and accuracy of the single warheadversion of the R-27U was supposed to increase in 20 and 15 percent respectively.

Between September 1972 and August 1973 a total of 16 R-27U missiles weresuccessfully launched from a submarine. On 04 January 1971 deployment of the D-5Ulaunch system began. Yankee II and upgraded Yankee I submarines were outfitted withthe new system and missiles.

The R-27U missile and D-5U launch system remained in service through 1990. Over thelife of the program the service life of the missile was increased from five years to thirteenyears.

The R-27K (SS-NX-13) modification featured a nose cone with a terminal guidancesystem. This missile, designated 4K18, was designed to attack both coastal radiocontrolinstallations and moving targets at sea. The R-27K missile was tested in 1974 on boardthe converted "K-102" 629 Golf submarine.

Between 1968 and 1988 the D-5 launch system conducted 492 missile firings, of which429 were successful. The D-5 launch system conducted more launches than any otherSoviet launch system: a peak of 58 launches in 1971 and an average of 23.4 launches peryear. During the service life of the D-5U launch system 150 out of 161 missile firings

were successful. Missile firings for military purposes were completed in 1988.Subsequently experimental launches were conducted for microgravity research purposes.

SpecificationsMod1 Mod2 Mod3

DIA SS-N-6 SS-N-6 SS-N-6

NATO Serb Serb Serb

Bilateral RSM-25 RSM-25 RSM-25

Service R-27 R-27U R-27U

OKB/Industry 4K10

Design Bureau SKB-385 SKB-385 SKB-385

Approved

Years of R&D



Deployment Date early 1969 1973 1975

Launch system D-5 D-5U D-5U

Submarine Yankee I Yankee II Yankee II

Type of Warhead Single Single MRV

Warheads 1 1 3

Yield (Russian Sources) 1.0 MT 1.0 MT 0.2

Yield (Western Sources) 0.6-1.2 MT 0.6-1.2 MT 0.1-0.8MT

Payload (t) 0.65 0.65 0.65

Total length (m) 9.65 9.65 9.65


7.1 7.1 7.1

Missile Diameter (m) 1.5 1.5 1.5

Diameter of Stabilizers (m)

Launch Weight (t) 14.2 14.2 14.2

Fuel Weight (t)

Range (km) 2400 3200 3200

CEP (km) (RussianSources)

1.9 1.3-1.8 1.3-1.8

CEP (km) WesternSources)

1.1 1.3 1.3

Number of Stages 1

Warheads Deployed


Engine Designation

Propellants Liquid

Fuel

Oxidizer

Burning time (s)

Verniers Thrust SeaLevel/Vacuum (kn)


Launching Technique Underwater "wet start"

Firing conditions: Sea state - Up to 5Submarine Speed, kn - 4 (at 40to 50m depth)

http://www.fas.org/nuke/control/start1/text/image/rfphotos/rsm25ssn6m.jpg

D-6Two versions of the D-6 launch system for solid-fuel missiles studied by OKB-7 (KBArsenal) in Leningrad between 1958 and 1960. One used missile with a single largediameter motor using propellants that were already in production for use in unguidedtactical rockets. The second version focused on a new missile incorporating new solidpropellants using a crystal oxidizer and fuel, with the first and second stages consisting ofclusters of four separate rocket motors. The overall dimensions of either missile wouldhave been too large for a launching tube inside the pressure hull, so the D-6 launcherdesign called for two tubes on each side of the outside of the hull. To fire the missiles thesubmarine would surface and the tubes would be turned into a vertical position. Thepreliminary design of the launch system was completed in 1960. The beginning ofdetailed design development of the D-6 complex was directed on 18 June 1960, but on 04June 1961 the program was cancelled.

SpecificationsDIA

NATO

Bilateral

Service

OKB/Industry

Design Bureau OKB-7 (KB Arsenal)

Approved

Years of R&D


First Flight Test none

IOC


Launch system D-6

Submarine


Warheads 1

Yield (mt)

Payload (t)

Total length (m)


Missile Diameter (m)

Launch Weight (t)

Fuel Weight (t)

Range (km)


CEP (m) WesternSources)

Number of Stages 2

Booster guidancesystem

Inertial autonomous

1st stage 2nd stage

Length (m)

Body diameter (m)

Fueled weight (t)

Dry weight (t)

Engine Designation

Propellants Solid Solid

Fuel

Oxidizer

Burning time (s)



Launching Technique Surface launch

Firing condition Sea stateSubmarine speed,kn

RT-15MThe solid-propellant RT-15M missile was the sea-based counterpart of the RT-15 land-based missile, known in the West as the SS-14 SCAMP. Both consisted of the second andthird stage of the RT-2, a prototype solid-fueled ICBM eventually deployed as the SS-13SAVAGE. The 667 Yankee submarine, originally designed to carry the liquid-fueled R-21 missiles with the D-4 launch system, was to carry the RT-15M using the D-7 launchsystems.

An order of the ministerial council on 04 April 1961 authorized the development of thesystem by SKB-385, under the industrial designation 4K22. However, SKB-385 was notparticularly enthusiastic with the RT-15M missile, regarding liquid-propellant missiles asmore promising The solid-propellant RT-15M missile, with a range of 2400 km, weighedthree times more than the liquid propellant R-27 missile which had similar rangecapabilities.

Testing lagged substantially behind the initial schedule. Initially the missile underwentpop-up tests, with 5 launches conducted on "613" submarines. Beginning in late 1963 aseries of 20 flight tests were conducted of the missile from Golf I submarines. Thedemonstration of underwater launch from a flooded platform was not completed until themiddle of 1964. However, in July 1963 the initiation of integrated testing was postponed,pending successful results with tests of the solid-fuel RT-2 ICBM. Subsequently,development of the RT-15M missile and the D-7 launch system was halted due to thelimited range and large weight and overall dimensions of the missile.

SpecificationsDIA

NATO

Bilateral

Service RT-15M

OKB/Industry

Design Bureau SKB-385

Approved

Years of R&D



IOC


Launch system D-7

Submarine 667 Delta


Warheads 1

Yield (mt) 1

Payload (t)





Fuel Weight (t)

Range (km) 2400



Number of Stages 2


Inertial autonomous

1st stage 2nd stage

Length (m)

Body diameter (m)

Fueled weight (t)

Dry weight (t)

Engine Designation


Fuel

Oxidizer

Burning time (s)



Launching Technique Underwater start

Firing condition Sea state - AnyweatherSubmarine speed,kn

R-29 / SS-N-8 SAWFLYThe R-29 SS-N-8 was the first Soviet sea-based ICBM. Deployed on the Delta-classsubmarines beginning in 1973, the missile's long range allowed submarine alert patrols inthe marginal ice seas of the Soviet arctic littoral, including the Norwegian and Barentsseas. Consequently, Soviet submarines no longer needed to pass through Western SOSUSsonar barriers to come within range their targets. And deployed close to home, they couldbe protected in "bastions" by the rest of the Soviet Navy.

The R-29 is a two-stage missile storable liquid-propellant, without an interstage section,carrying a single warhead. The missile had an aluminium magnesium alloy body withintegrated fuel tanks. The first stage sustainer and the second stage propulsion system arelocated inside the fuel tanks, thus reducing the external dimensions of the missile. Theconical blunt shaped re-entry vehicle was also located in the second stage fuel tank,oriented opposite to the flight direction. The guidance section is located in the conicalarea of the compartment where the warhead is usually placed. The propulsion systems ofboth stages consists of a single-chamber main rocket engine, and dual-chamber controlengines with moveable chambers. The R-29 was the first Soviet SLBM to use a digitalcomputer and an azimuthal stellar monitoring system for improved high accuracy and in-flight course correction.

With a launching weight of 33.3 tons the R-29 missile was capable of delivering a 1,100kg reentry vehicle to a maximum range of 7800 km, three times greater than the R-27missile. Thus its patrolling zones were substantially enlarged. According to Westernestimates in the 1970s, the SS-N-8 was capable of delivering a 1400-lb reentry vehiclewith a 0.6-1.5 MT warhead a distance of 4200 nm with a CEP of approximately 0.5 nm.

The R-29 was equipped with ballistic missile defense countermeasures. Decoys werecarried in a cylindrical container in the fuel tank of the second stage, and released duringnose cone separation.

Preliminary design work was conducted by SKB-385 in 1963, which was also in chargeof carrying out the entire project after the Soviet Defense Ministry discarded thecompeting proposals made by OKB-52 and its chief designer V.N. Chyelomyey. Thedevelopment of the D9 launch system with R-29 missiles was approved on 28 September1964.

The initial tests of the R-29 missile and the D-9 launch system took place with the BlackSea fleet. They consisted of launching full-scale missile dummies with a first stagepropulsion system and a simplified command system. Further testing was conducted fromMarch 1969 until December 1971 at the State Central Marine Test Site in Nenoksa. Atotal of 20 flight demonstration launches were conducted from a ground platform. Thefinal test phase consisted of a series of submarine launches from Delta I submarines. Thefirst submarine launch was on 15 December 1971 in the White Sea. Further tests took

place from August through November 1972, during which 18 out of 19 launches weresuccessfully conducted.

The R-29 missiles and the D-9 launch system were made operational on March 12, 1974and they are deployed on 18 Delta I submarines. The Delta Class nuclear submarine canlaunch missiles at approximately 7-second intervals while fully submerged. Normalreaction time is 15 minutes; reaction time under conditions of peak alert is about oneminute. The allowable hold time under peak alert conditions is one hour. The missilescould either be fired underwater or while the submarine was moored at their bases.

Further improvements lead to an increase in range up to 9100 km. The modernizedlaunch system designated as D-9D was made operational in 1978. It was initiallydeployed on four Delta II submarines, which carry 16 R-29D missiles instead of 12 R-29missiles. Subseqeuntly, the Delta I submarines were also outfitted with R-29D missiles.


First land-based launch from Nenoksa Naval Missile TestCenter detected June 21, 1969

Hotel III submarine used as test bed for SS-N-8 SLBM 1970

First sea launch December 25,1971

Estimated start of integrated system test Mid-1972

First detection of 12-missile tube Delta Class SSBN August 1972

Two SS-N-8 missiles launched simultaneously November 28,1972

Four SS-N-8 missiles launched within a 30-second interval December 14,1972

Initial operational capability reached Mid-1973

SpecificationsMod1 Mod2

DIA SS-N-8 SS-N-8

NATO Sawfly Sawfly

Bilateral RSM-40 RSM-40

Service R-29 R-29

OKB/Industry 4K75

Design Bureau SKB-385 SKB-385

Approved

Years of R&D


First Flight Test

IOC

Deployment Date 3/12/1974 1978

Launch system D-9 with 12 missiles D-9D with 16 missiles

Submarine Delta I Delta I & Delta II

Type of Warhead

Warheads Single

Yield (Russiansources)

Yield (Westernsources)

0.6-1.5 MT 0.6-1.5 MT

Payload (t) 1.1 1.1

Total length (m) 13





Fuel Weight (t)

Range (km) 7,800 9,100


1,500 900


900 900

Number of Stages 2

Warheads Deployed


Astroinertial

1st stage 2nd stage

Length (m)

Body diameter (m)

Fueled weight (t)

Dry weight (t)

Engine Designation


Fuel

Oxidizer

Burning time (s)



Launching Technique Underwater "wetstart"/surfaced

Firing conditions: Sea state - AnyconditionUp to 5Submarine Speed,kn --

http://www.fas.org/nuke/guide/russia/slbm/ru_nuke_slbm_rsm40_01.jpg

http://www.fas.org/nuke/control/start1/text/image/rfphotos/rsm40ssn8.jpg

R-29R/R-2S / SS-N-18 STINGRAYThe R-29R missile is the first sea-based Soviet ballistic missile carrying 3 to 7 multipleindependently targetable reentry vehicles (MIRVs), with a range of 6,500 to 8000 km,depending on the number of reentry vehicles. It is carried on the 667BDR Delta IIIballistic missile submarine, which is equipped with the D-9R launch system and 16 R-29R missiles. The Delta III is the first submarine that can fire any number of missiles in asingle salvo.

The R-29R, the R-29RL and the R-29RK were based on the R-29 single-warhead SLBM.The missiles incorporated the first two stages of the R-29 missile largely unchanged.However, instead of the single reentry vehicle and instrument module on the R-29, theR29R features a post-boost vehicle with either a single warhead or three or sevenmultiple independently targetable reentry vehicles. The single warhead missile has amaximum range of 8000 km, whereas the MIRVed missiles have a range 6500 km.

The post-boost vehicle includes an instrument-assembly module, a guidance system and apropulsion system. The propulsion system of the post-boost vehicle consists of a four-chamber liquid-propellant rocket engine providing for independent warhead targeting.The combustion chambers of the engine are placed on an external conical supportstructure. The blunt shaped warheads, oriented at an angle of the centerline of the missile,are positioned opposite of the flight direction. They are positioned in a conical shapedinternal cavity at the bottom of the forward second stage fuel tank. The bus also dispensesballistic missile defense countermeasures.

Based on the D-9 launch system, the D-9R launch system was developed in the mid-1970s to provide a capability for launching MIRVed missiles. The flight tests of the R-29R missiles took place from November 1976 throughl October 1978 in the White andBarents Seas on board of the "K-441" Delta III submarine. Of the 22 missiles that weretested, 4 carried a single warhead, 8 carried three MIRVs and 12 were tested with sevenMIRVs.

Fourteen 667 BDR Delta III submarines were outfitted with the D-9R launch system andR-29R missiles.

The SS-N-18 missile carrying seven MIRVs was not deployed. In compliance with theSTART-1 treaty all missiles are considered to carry four MIRVs.

SpecificationsMod1 Mod2 Mod3

DIA SS-N-18 SS-N-18 SS-N-18

NATO Stingray Stingray Stingray

Bilateral RSM-50 RSM-50 RSM-50

Service R-29R R-29R R-29R

OKB/Industry 3M40

Design Bureau NIIMashinostroyeniya

NIIMashinostroyeniya

NIIMashinostroyeniya

Approved

Years of R&D 1973- 1973- 1973-


First Flight Test

IOC

DeploymentDate

1979

Launch system D-9R D-9R D-9R

Submarine Delta III Delta III Delta III

Type ofWarhead

Single MIRVed MIRVed

Warheads 1 3 7

Yield (mt) 0.450 0.2 0.1

Payload (t) 1.6 1.6 1.6

Total length (m) 14.1 14.1 14.1


MissileDiameter (m)

1.8 1.8 1.8

Diameter ofStabilizers (m)

Launch Weight(t)

35.3 35.3 35.3

Fuel Weight (t)

Range (km) 8000 6500 6500


900 900 900

CEP (m)WesternSources)

Number ofStages

2 plus post boostvehicle

Warheadsdeployed

Boosterguidancesystem

Astroinertial

1st stage 2nd stage

Length (m)

Body diameter(m)

Fueled weight(t)

Dry weight (t)

EngineDesignation

Propellants Liquid

Fuel

Oxidizer

Burning time (s)

Verniers ThrustSeaLevel/Vacuum(kn)

Specific Impulse(s)

LaunchingTechnique

Firingconditions:

Sea state Submarin

e Speed,

kn

Deployedboosters

Test Boosters

WarheadsDeployed

TrainingLaunchers

http://www.fas.org/nuke/guide/russia/slbm/brrsm50.jpg




R-29RM / SS-N-23 SKIFThe R-29RM is a three-stage liquid-propellant missile carrying four or ten MIRV.Compared to the R-29R the missile has a larger launch weight (40.3 to 35.5 Tons)providing a heavier payload (2800 kg to 1650 kg) to a greater maximum range (8300 to8000 km). The R-29M incorporates a number of significant design changes relative to thepredecessor R-29R

Relative to the R-29R, the diameter of the R-29RM was increased from 1.8 meters to 1.9meters, which allowed an increase in propellant loading. The new missile's length wasincreased only slightly, from 14.1 meters to 14.8 meters, allowing the overall dimensionsof the launching tube to remained constant. The D-9RM launch system for the R-29RMmissiles is based on the D-9R system.

Unlike the R-29 and R-29R, the propulsion system of the first stage has four controlchambers. The engines of all three stages are located in the tanks. The third stagepropulsion system and the post-boost vehicle propulsion system use the same fuel tanks.The warheads are placed in an internal cavity of the concave conical bottom of the uppertank of the second stage at the periphery of the sustainer of the third stage.

NII Mashinostroyeniya began work on the development of the D-9RM launch system andthe R29-RM in 1979. A series of vehicle development launches from a floating platformwas conducted initially, followed by 16 flight tests from a ground platform andsubmarine tests. Deployment of the D-9RM launch system began in 1986.

Seven Deltra IV submarines were equipped with the D-9RM launch system. They carry16 R-29RM missiles containing four warheads each. The R-29RM missiles carrying tenwarheads were not deployed.

In 1988 the launch system was modernized providing improved accuracy, and for firingthe missiles on depressed trajectories. At that time the missile was also equipped withimproved warheads.

In late 1999 Russia announced plans to resume production of the SS-N-23. he statemissile center Design Agency named after V. P. Makeev received a state order from theRussian government to resume the manufacture of naval missiles, including the mostadvanced RSM-54 system developed by the Agency when Victor Makeev was its generaldesigner. While deployed with four warheads for the START I treaty, it was originallytested with 10 warheads and might be deployed with that number in the absence of sucharms control agreements. It has been suggested that some of these liquid-fuel missilescould be deployed on land in the absence of the START agreements. T

Specifications

DIA SS-N-23

NATO Skiff

Bilateral RSM-54

Service R-29RM

OKB/Industry 3M37

Design Bureau NII Mashinostroyeniya

Approved

Years of R&D


First Flight Test June 1983

IOC

Deployment Date 1986

Launch system D-9RM with 16 missiles

Submarine

Type of Warhead MIRV

Warheads 4 (tested with 10)

Yield (mt)

Payload (t) 2800






Fuel Weight (t)

Range (km) 8300


500


Number of Stages 2

Warheads Deployed


astroinertial

1st stage 2nd stage

Length (m)

Body diameter (m)

Fueled weight (t)

Dry weight (t)

Engine Designation

Propellants Liquid

Fuel Nitrogen Tetraoxid Nitrogen Tetraoxid

Oxidizer UDMH UDMH

Burning time (s)



Launching Technique Underwater wet start/surface

Firing conditions Sea StateSubmarine speed, kn


http://www.fas.org/nuke/guide/russia/slbm/brrsm54_1.jpg

http://www.fas.org/nuke/guide/russia/slbm/brrsm54_2.jpg






R-31 / RSM-45 SS-N-17 SNIPEThe R-31 missile, the first deployed Soviet sea-based solid-fuel missile, was a two-stagemissile with a single warhead. Compared to the liquid-propellant R-27 missile the R-31was easier to handle and had an increased range. However, despite a similar launchweight, the R-31 had a lower accuracy and half the range of the liquid-propellant R-29missile which was developed at the same time.

In the early 1970s the Soviet Navy ordered the development of new missiles and a newlaunch system intended to replace the D-5 launch system on Yankee I submarines thatwere to be overhauled and upgraded. Two different proposals were submitted by NIIMashinostroyeniya (chief designer V. P. Makyeyev) and KB Arsenal (chief designer P.A.Tyurin), and the project was awarded to KB Arsenal.

Unlike the liquid-propellant missiles R-21, R-27 and R-29, the underwater firing of theR-31 did not require filling the launch tube with water. The missile was ejected from thehermetically sealed tube by a gas generator. The missile emerged in a gas bubble, whichwas maintained with the help of a special hydrodynamic device located on the nose cone.The sustainer motor of the first stage was started after the missile emerged from thewater. The dry start allowed to reduce pre-launch preparation time substantially anddecreased the noise during launch preparation.

Flight tests of the R-31 missile from a ground platform took place in 1973. The firstunderwater launch was held on December 26, 1976 in the White Sea. Flight tests werecompleted in 1979 and in 1980 the Yankee II submarine "K-140" was outfitted with R-31missiles. Deployment was limited to a single Yankee II submarine "K-140". In 1989 theR-31 missiles were withdrawn from service.


NATO Snipe

Bilateral RSM-45

Service R-31

OKB/Industry 3M17

Design Bureau KB Arsenal

Approved

Years of R&D



IOC

Deployment Date September 1980


Submarine Yankee II


Warheads 1

Yield (mt) 0.5

Payload (t) 0.45

Total length (m) 11


10.6




Fuel Weight (t)

Range (km)



Number of Stages 2

Warheads Deployed


1st stage 2nd stage

Length (m)

Body diameter (m)

Fueled weight (t)

Dry weight (t)

Engine Designation


Fuel

Oxidizer

Burning time (s)



Launching Technique Underwater dry start

Firing condition Sea state - Anyweather

Submarinespeed, kn

R-39 / SS-N-20 STURGEONThe R-39 solid-propellant intercontinental missile is a three-stage missile with multiplere-entry vehicles. The post-boost vehicle has a guidance system, a liquid fuel propulsionsystem and 10 blunt shaped MIRVed warheads that are smaller than warheads carried onprevious missiles. The warheads are located on the rear unit of a post-boost vehicle,around the nozzle of the third stage engine.

The missile is suspended in the launch tube from a special control mounted in the nosecone, with a reference ring at the top of the tube functioning as the launch support. Thedry launch from the tube is accomplished with a gas generator located on the bottom ofthe tube in a cavity of the first stage engine nozzle. During lift-off special solid-propellantcharges create a gas bubble around the missile considerably reducing hydrodynamicresistance. Ignition of the first stage engine occurs after leaving the tube.

Flight control during the active leg of the first stage is attained by injecting gases fromthe combustion chamber of the sustainer into the nozzle through 8 symmetrically locatedinjection valves. The engines of the second and third stage have gimbaled nozzles.

Work on the R-39 missile and the D-19 launch system began in 1971 by NIIMashinostroyeniya (chief designer V. P. Makyeyev). Development was officiallyauthorized in September 1973. Flight testing was conducted in several phases. Initiallytwo series of dry launches were carried out, nine from a floating platform and seven froma specially adapted submarine. Due to first and second stage engine problems more thanhalf of the 17 flight tests at the Central Naval Test Training Site at Nenoksa wereunsuccessful.. After resolution of the engine problems 11 out of 13 launches from the"TK-208" Typhoon submarine were carried out successfully.

After intensive testing on board the "TK-208" submarine, deployment began in 1984. Thelarge Typhoon submarines were outfitted with 20 R-39 missiles each.

Soon after deployment work began on an advanced version with greater accuracy andgreater warhead coverage. Deployment of the modernized missile began in 1989.

At the end of the 1980s work on an improved version of the R-39 missile began. This wasintended to be deployed on Typhoon submarines and new "Yurin Dolgorukiy" SSBNs.Work on the new missile lagged seriously behind the initial timetable. Flight testingbegan in 1996 and the first launches terminated in failures.


NATO Sturgeon

Bilateral RSM-52

Service R-39

OKB/Industry

Design Bureau NII Mashinostroyeniya

Approved

Years of R&D 1973-`979



IOC

Deployment Date May 1983


Submarine Typhoon

Type of Warhead MIRVed

Warheads 10

Yield (mt) 0.1 each

Payload (kg) 2550



8.4




Fuel Weight (t)

Range (km)


500


Number of Stages 3

Warheads Deployed

Booster guidance Astroinertail

system


Length (m)

Body diameter (m)

Fueled weight (t)

Dry weight (t)

Engine Designation

Propellants Solid Solid Solid

Fuel

Oxidizer

Burning time (s)



Launching Technique Underwater dry start

Firing condition Sea state - Any weatherSubmarine speed, kn




http://www.fas.org/nuke/guide/russia/slbm/brrsm52ak.jpg

R-39M / Grom [Bark] / RSM-52V / SS-N-28

Russia regards as top priority the maintenance of its strategicnuclear capacity, which represents the base of its policy ofdeterrence. From this point of view, and in advance of theneed for replacing the obsolete hardware or not in conformitywith the START-II agreements (which authorize single-warhead land-based missiles, while permitting multiple-warhead sea-based missiles) a process of modernization ofhardware has been authorized. This envisages thedevelopment of missile SS-27, successor of the SS-25, andthe development of the new SS-N-28 embarked onsubmarines, and the construction of a fourth generation ofstrategic missile submarines. Russia still maintains a largeforce of nuclear-powered ballistic missile submarinesequipped with intercontinental range missiles. Although thenumber of Russian SSBNs is expected to drop considerablyover the next few years, Russia planned to modernize its forcewith the addition of the new SS-NX-28 and new Borei Classballistic missile submarines.

The new Grom SS-N-28 was designed to provide improved accuracy compared to theprevious SS-N-20, but is otherwise apparently a straightforward development of thissystem. The SS-NX-28, unlike previous Russian SLBMs, is the first to be totallydeveloped and manufactured within Russia's borders by the Makeyev Machine-BuildingDesign Bureau. The test launch of a prototype SS-NX-28 (RSM-52V) SLBM on 19November 1998 resulted in a catastrophic failure of the SLBM's booster. The missileexploded roughly 200 meters after take-off from its ground based launch station. Havinghad failed its first three test firings, and the SS-N-28 project was abandoned.

As of early 1999 it appeared that construction had ceased on the first unit of the Borei-class, pending a redesign of the ship to accomodate a different missile from the originallyintended SS-N-28.

The Typhoon submarines were initially intended to be retrofitted with the SS-N-28. Thelead unit of this class, the TK-208, had been in overhaul since 1992 with the intent ofreceiving these modifications, but it now appears that it will not return to service. TheTyphoon class submarines are slated to be withdrawn from service within a few years,and it is unlikely that other units of the class would be modified to accomodate newmissiles.

In January 2000 Rear-Admiral Vladimir Makeev, the head of the Northern Fleet's rockettest site at Nenoksa, Arkhangelsk County, stated that Typhoon submarines would be used

to test the new Bark-class strategic missiles. Makeev also stated that Bark-class missileswere to be installed on the forth generation Borey-class submarines.

The creation of D-19UTH missile complex designed for the new nuclear strategicsubmarines of the Borei-class has been undertaken at GRTs KB named after V. P.Makeev. The D-19UTH launch complex is to replace the D-9 launch complex with RSM-52 ballistic missiles. The new complex will be equipped with a solid-fuel ballistic missileof greater reliability and longer range, capable of being fired from the surface and under-water positions.

SpecificationsPrimary function:

Contractor: Makeyev Machine-Building

Power Plant:

Length:

Weight:

Diameter:

Range: 5,000+ miles

Speed:

Guidance system:

Warheads: 10 or fewer

Date Deployed:

Unit Cost:

Inventory:

611 AB ZULU VThe development of the first Soviet ballistic missile submarine started with agovernmental order for the adaptation of a diesel-powered submarine of the 611 Zuluclass to be equipped with the D-1 launching system and two R-11FM missiles. This newsubmarine designated as B-611 was developed by OKB-16. The technical design of thesubmarine was completed by the end of 1954.

Unlike its predecessors the B-611 submarine had an additional missile compartment withtwo firing tubes which passed through the strong hull. To accommodate the newlaunching complex the structure of armament was changed. The spare torpedos, minesand artillery armament were removed and at the expense of removing one of four groupsof storage compartments additional launching devices for missile firings were installed.

To fire the missile the submarine had to submerge, the cover of the launching tube wasopened and the missile was raised to the edge of the tube. The missile was fastened withthe help of two racks, which were removed at liftoff. The pre-launch preparation wereconducted underwater and lasted two hours. When submerged it took five minutes tolaunch the first missile and another five minutes to launch the second one. The launchcould be carried out at a speed of up to 12 knots.

The B-611 submarine was assembled in Severodvinsk and some parts of the submarinewere delivered from Leningrad. The construction of the first Soviet ballistic missilesubmarine was completed in September 1955 and received the tactical designation "B-62". The B-62 was Project 611A [ZULU IV] with a single R-11FM (Scud) missile. Somesources quote B-67 as the original Project 611A, however only B-62 fits the knownconstruction dates. The other submarines were Project 611AB ZULU V with two suchmissiles. In September 1955 the first ballistic missile was launched from the first B-611submarine "B-62". Between 1956 and 1958 further testing of the D-1 launch system wascarried out and in 1959 the "B-62" submarine was converted to carry out the firstunderwater missile firing.

From 1956 on the B-611 submarines were equipped with five new diesel-poweredengines and received the new designation AV-611. The first AV-611 submarines servedin the Northern fleet. The four submarines that were re-equipped in Severodvinsk werecommissioned in 1957 and served in the 40th brigade of the Northern Fleet while theAV-611 re-equipped at Komsomolsk-na-Amur served in the Pacific Fleet.

After an improved launch system was developed, the original launch systems D-1 wasremoved from operational status in 1967. In the second half of the 1960s the AV-611submarines were equipped with hydroacoustic devices and improved navigation andcommunication systems. They remained in service until the end of the 1980s.

SpecificationsSoviet Designation V-611 AV-611

US-Designation Zulu IV Zulu V

Development began January 1954

Design Bureau UKB-16

Chief designer N.N. Isanin

Builders Nr. 402 Severodvinsk Nr. 402 SeverodvinskNr. 199 Komsomol NaAmur

Construction andOutfit

1953-1956 1954-1958

Service time 1956-1964 1957-1968

Number of ships 1 5

D-1 launch system withR-11FM missiles

Armament

10-533mm torpedo tubes

Power Plant Diesel and electrical engines

Length 90.5 meters 98.9 meters

Beam 7.5 meters

Draft 5.14 meters 5.15 meters

1875 m3 Surfaced 1890 m3 SurfacedDisplacement

2387 m3 Submerged 2415 m3 Submerged

Operating depth 170 meters (design)200 meters (maximum depth)

16.5 knots SurfaceSpeed

13 knots Submerged 12.5 knots Submerged

Crew 72 men 83 men

Endurance 58 days

Class ListingBoat Chronology

# number NameShipyard

Laid Launched Comm. StrickenNotes

Down

1 B-62 402 Sevmash Dec.31/53 1970 Sonartrialsship1966

2 B-67 402 Sevmash Jun.30/56 1970

3 B-73 402 Sevmash Nov.30/57 1971

4 B-78 402 Sevmash Nov.30/57 1990

5 B-79 402 Sevmash Dec.4/57 1971

6 B-89 199 Komsomolsk Dec.13/57 1990

629 GOLFAlong with initiating development of the first experimental ballistic missile submarineunder Project V-611, the governmental order of 26 January 1954 provided for thedevelopment of a diesel-powered ballistic missile submarine. On May 1954 theheadquarters of the Navy assigned OKB-16 the task of developing the Golf submarines.The development of the Golf I submarine and its corresponding launch system D-2 wasauthorized on 11 January 1956. In March 1956 the complete technical design of thesubmarine was submitted to the Navy shipbuilding headquarters.

Originally the new submarine was designed to carry the R-11FM missiles, which had arange of 250 km, and only 150 km when carrying a nuclear warhead. Americanantisubmarine defense precluded using such a short-range missile to carry out effectivestrikes against targets at any meaningful distance from the coastline. As the developmentof the submarine encountered significant delays, it was nevertheless decided to equip thefirst three submarines with R-11FM missiles.

The basic design of the Golf submarine is based on the 641 Foxtrot, and theelectromechanical installation for a surface and underwater navigation, the hydroacousticsystem, the radar facilities and the radio communication systems were incorporatedwithout change. The 629 Golf has a cylindrical pressure hull divided into eightcompartments, with three missile tubes located in the fourth compartment.

The large fin of the submarine contains the missiles that are stored in vertical containersdirectly behind the sail. The missiles are fired by raising the launch platform to the edgeof the tube. Launches are conducted on the surface at a speed of up to 15 knots. Thebattle management system records the current flight coordinates automatically,considerably reducing the time necessary for pre-launch preparation. The pre-launchprocedures are conducted underwater and take approximately one hour. Another fourminutes was needed after the submarine surfaced, and a total of 12 minutes elapsed untilall three missiles were fired.

In comparison with the AV-611 submarine the 629 had several advantages. It wasoutfitted with an additional missile and their range was four times greater. By employingstronger steel for the pressure hull, the maximum navigable depth was increased. Therange of sailing was increased both for the surface and the underwater mode and specialfive-bladed fixed-pitch propellers were developed to reduce the noise.

In January 1959 the USSR decided to sell the construction and design plans of the 629SSBN to the People's Republic of China. After the relations between the USSR andChina deteriorated, Soviet specialists were mostly withdrawn in August 1960, though thedocumentation and equipment for the project remained in China.

The construction of submarines of the project 629 was begun in 1957 at Severodvinskand Komsomol Na Amur. Less than one year later the submarines were launched and at

the end of 1958 trial runs were carried out and the vessels were moored. By 1960 seven629 submarines had been launched, five of which were incorporated into the Northernfleet and two into the Pacific fleet. In 1961 another five submarines entered the Northernfleet and one entered the Pacific fleet. In 1962 the last two boats arrived at the Pacificfleet. A total of 23 submarines were built: 16 in Severodvinsk and 7 in Komsomol NaAmur.

In March or April 1968 the "K-129" submarine sank in the northern Pacific Ocean (1390kms northwest of Oahu harbor). According to the official version of the Soviet Navy, thesubmarine exceeded its maximum depth and came to rest on the ocean bottom at a depthof over 5 km. The collapse of the hull was detected by the American SOSUS acousticsystem, and in July 1974 parts of the submarine were recovered.

The 629 SSBNs of the Northern fleet were organized in the 16th Division that was basedin the Olyenya port. This division formed part of the 12th Squadron, which washeadquartered in Yagyelnoy. In May 1962 the Soviet government approved a plan for thedeployment of a Group of Soviet Forces to Cuba, which in October 1962 precipitated theCuban Missile Crisis]. Initially the plan called for the deployment of a squadron ofsubmarines, comprising the 18th Division of missile submarines of the Project 629 class[NATO Golf or G-class], consisting of 7 submarines each with 3 R-13 [SS-N-4] missileswith range of 540 km. This element of the plan was in fact not implemented. InSeptember 1968 two 629A submarines were transferred from the Northern to the Pacificfleet and another four from October 1971 till November 1974. At the end of the 1970s the16th Division, consisting of six 629A submarines, was transferred from the Northern tothe Baltic fleet.

The 629 submarines that served in the 29th submarine division of the Pacific Fleet werefirst based on Kamchatka and later on in the Pavlovsk bay. In the middle of the 1970sseven 629A submarines were still in service in the Pacific Fleet.

In 1989 four 629A submarines still served in the Baltic and two in the Pacific Fleet. In1990 however, all submarines were decommissioned.

Variants

Golf III - Between 1969-1974 the "K-118" was outfitted with 6 launchers to carryout tests of the R-29 (SS-N-8) ballistic missiles. Its' displacement was increased to4000 tons and the updated submarine received the designation 601.

Golf IV - Between 1969 and 1973 the "K-102" submarine was converted underthe Project 605 in order to conduct tests of the R-27K (SS-NX-13) ballisticmissiles. It was lengthened in 18,3 meters and outfitted with four launchers.

Golf V - In 1976 one submarine ("K-153") was outfitted with a launcher to carryout tests of the R-39 missile. The submarine received the new designation Project619.

Golf SSQ - Between 1973 and 1979 the submarines "K-61", "B-42" and "K-107"were converted in Vladivostok under the Project 629R into a command post, withthe missile and torpedo tubes removed.

SpecificationsSoviet Designation 629 629A

US-Designation Golf I Golf II

Development began January 1956 March 1958



Builders Nr. 402 SeverodvinskNr. 199 Komsomol Na Amur


1958-1962 1966-1972

Service time Since 1959 1967-1990

Number of ships 22 14 (converted from GolfI)

D-1 launch system with3 R-11FM missilesD-2 launch system with3 R-13 missiles

D-4 launch system with3 R-21 missiles

Armament




Beam 8.2 meters


2,794 tons Surfaced 2,300-2,820 tons SurfacedDisplacement

3,553 tons Submerged 2,700-3,553 tonsSubmerged


15 knots Surface 15-17 knots SurfaceSpeed

12.5 knots Submerged 12-14 knots Submerged

Crew 80 men 83 men

Endurance 70 days


# Number

Name

Shipyard LaidDown

Launched

Commisioned

Stricken

Notes

1 B-92 402Sevmash

----------

----------

01/20/1960

1991 redesignated K-96 (orK-61)12/1976 project 629Rconverted toSSQ,redesignated BS-167

2 B-40 402Sevmash

----------

----------

1959-62 1991 redesignated K-72project 629A converted(Golf II)1974 redesignated K-372

3 B-41 402Sevmash

----------

----------

1959-62 1991 redesignated K-79project 629Aconverted(Golf II)

4 B-42 402Sevmash

----------

----------

1959-62 1991 redesignated K-831978 project 629Rconverted toSSQ,redesignated BS-83

5 B-121

402Sevmash

----------

----------

1959-62 ----------

redesignated K-1021973 project 605converted(Golf IV)

6 B-125

402Sevmash

----------

----------

1959-62 ----------

redesignated K-167

7 B-45 402Sevmash

----------

----------

1959-62 ----------

redesignated K-8812/28/1966 first project629A converted(GolfII)

8 B-61 402Sevmash

----------

----------

1959-62 1991 redesignated K-93project 629Aconverted(Golf II)

9 B-15 402 ------ ------- 1959-62 1974 redesignated to K-113

Sevmash ---- --- project 629Econverted(minelayer)

10

K-118

402Sevmash

----------

----------

1959-62 12/1976 project 601converted(Golf III)

11

K-36 402Sevmash

----------

----------

1959-62 1980 redesignated K-106

12

K-91 402Sevmash

----------

----------

1959-62 1980

13

K-107

402Sevmash

----------

----------

1959-62 1991 1977 project 629Rconverted toSSQ,redesignated BS-107

14

K-110

402Sevmash

----------

----------

1959-62 ----------

project 629Aconverted(Golf II)

15

K-153

402Sevmash

----------

----------

1959-62 1992 projext 629Aconverted(Golf II)1978 project 619converted(Golf V)1991 redesignated BS-153

16

K-142

402Sevmash

----------

----------

1959-62 1991 1967 project 629Aconverted

17

B-93 199Komsomolsk

----------

----------

1959-62 ----------

redesignated K-126project 629Aconverted(Golf II)

18

B-103

199Komsomolsk

----------

----------

1959-62 08/30/1968

redesignated K-129,lost 03/08/1968

19

B-109

199Komsomolsk

----------

----------

1959-62 ----------


20

B-113

199Komsomolsk

----------

----------

1959-62 ----------


21

K-75 199Komsomolsk

----------

----------

1959-62 ----------

redesignated B-575project 629Aconverted(Golf II)

2 K-99 199 ------ ------- 1959-62 --------- project 629A

2 Komsomolsk

---- --- - converted(Golf II)

23

K-163

199Komsomolsk

----------

----------

1959-62 ----------

project 629Aconverted(Golf II)

629A GOLF IIIn March 1958 the development of a new missile launch system D-4 with R-21 missileswas approved. It was planned to replace the D-2 launch system and allowed underwatermissile firings. The R-21 missiles could be fired from a depth of 40-50 m at a speed of upto 4 knots at intervals of 5 minutes. The time for prelaunch preparation wasapproximately 45 minutes. After the launch system reached its IOC in May 1963 the re-equipment of the 629 submarines began. The submarines equipped with the new D-4launching system were designated as 629A (Golf II). In early 1967 the upgrading of thefirst submarines under the project 629A was completed. In total 8 submarines from theNorthern and Pacific fleet were outfitted with the D-4 launch system.

The improved twenty third submarine of the Golf class (629A) incorporated twoimproved R-21 missiles.

SpecificationsSoviet Designation 629 629A

US-Designation Golf I Golf II

Development began January 1956 March 1958



Builders Nr. 402 SeverodvinskNr. 199 Komsomol Na Amur


1958-1962 1966-1972

Service time Since 1959 1967-1990

Number of ships 22 14 (converted from GolfI)

D-1 launch system with3 R-11FM missilesD-2 launch system with3 R-13 missiles


Armament




Beam 8.2 meters


2,794 tons Surfaced 2,300-2,820 tons SurfacedDisplacement

3,553 tons Submerged 2,700-3,553 tonsSubmerged


15 knots Surface 15-17 knots SurfaceSpeed

12.5 knots Submerged 12-14 knots Submerged

Crew 80 men 83 men

Endurance 70 days

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658 HOTEL I/II/IIIDevelopment of the 658 Hotel Class nuclear powered ballistic missile submarine, to beequipped with the D-2 launch system and R-13 missiles, was approved on 26 August1956. Work on the design documentation began in September 1956, and the technicalproject was completed in the first quarter of 1957. However this preliminary design wasnot developed because it would have taken too long to complete. The duties of the chiefdesigner of the project 658 were originally assigned to the chief engineer of OKB-18 P.Z. Golosovskogo. In February 1958 the project management was transferred to I.V.Mihaylov, who in October 1958 had replaced S.N. Kovalev. The deputy of the chiefdesigner was from outset I.D. Spasskiy.

The Hotel I submarine was a modification of the first Soviet atomic submarine of the 627November class. Unlike the November it was equipped with a missile compartment thathad previously been used on the Golf submarines. Additionally, small horizontalhydroplanes were added to provide better maneuverability. For high-speed underwateroperations with reduced noise, more reliable electrohydraulic-command control surfaceswere implemented using main ballast low pressure air.

The Hotel I carried three R-13 missiles and the D-2 launch system placed in verticalcontainers directly behind the sail. All three missiles could be fired within 12 minutesafter the submarine surface.

The first Hotel submarine -- "K-19" -- was laid down on 17 October 1958. Theconstruction of the boats was completed on 12 November 1960 when the last of eightHotel submarines was launched. All of them were built at the shipyard in Severodvinsk.

In March 1958 it was decided to modify the Hotel I design to accommodate the D-4launch system which could conduct submerged missile launches. This modified SSBNreceived the designation 658M Hotel II, and the chief designer of the Hotel II was S.N.Kovalev. The installation of the D-4 launching system required some structural changesof the submarine. Before launch water filled the gap between the launch tube and themissile. To fire the missiles the submarine had to come to a depth of 16m.

The upgrading of an advanced submarine under the project 658M was completed onDecember 30, 1963. Between 1963 and 1967 all Hotel I submarines but one ("K-145")were re-equipped with the D-4 launch system.

From 1969 to 1970 the "K-145" submarine was re-equipped to test the R-29 missilesconverted. It received the designation 701 (Hotel III). Its length increased up to 130 mand the displacement increased to 5500 Tons surfaced and 6400 Tons submerged. Themaximum speed was reduced up to 18 knots on the surface and 22 knots submerged. Fourlaunching racks for R-29 missiles were placed in a compartment. In 1976 the "K-145"Hotel III was introduced into the Navy.

The two Hotel I submarines that were launched in 1960 were sent to the Western Theaterand formed a brigade together with 627A submarines. From this brigade in January 1961a flotilla consisting of two divisions was organized which included all the Project 658missile-submarines . In March 1964 the division was transferred to Gadzhiyevo base aspart of the 12th squadron, which subsequently became the Northern Fleet 3rd Flotilla. Bythe late 1960s the division began to fill with new 667A Yankee I submarines, and in late1970 one Hotel II submarine was transferred to the 18th division at Gremihu. The Hotelsubmarines of the Northern fleet were removed from operational status during 1986-1991.

Two 658 Hotel I submarines ("K-178" and "K-55") were transferred to the Pacific Fleetin September 1963 and 1968 and served in the 45-th division of atomic submarines onKamchatka. Both submarines were subsequently converted into the Hotel II class. Theywere decommissioned in 1988 and 1990.

A series of serious emergencies occurred on board Hotel I "K-19". In February 1961 adepressurization in the first containment of the reactor occurred. The next accidenthappened in the summer of 1961 while the "K-19" was on its first patrol mission during anaval exercise in the Atlantic Ocean close to Southern Greenland. On 04 July 1961 thepatrolling submarine's port side pumps ensuring circulation of heat-exchanger gave out.The crew managed to restore the integrity of the air-tight cooling jacket.. As a result ofthe radiation 22 men were killed. Subsequently from 1962-1964 the reactor compartmentof the "K-19" was completely removed and replaced. On 15 November 1969 the "K-19"crashed with the American submarine "Gato" (SSN-615), which had pursued the Sovietsubmarine in the Barens Sea. As a result of the impact the acoustic systems located in thebow were completely destroyed and the covers of the torpedo tubes were deformed.

On 24 February 1972 a fire broke out onboard "K-19" while the submarine was returningfrom patrol and was at a depth of 120 meters some 1300 km northeast of Newfoundland.The rescue operation of the submarine lasted more than 40 days and was severelyhampered by storms. More than 30 ships of Navy participated in the recovery operationand by early April the boat was towed back to the base of the Northern fleet. However, asa result of the emergency 28 crew members lost their lives.

SpecificationsSoviet Designation 658 658M

US-Designation Hotel I Hotel II

Development began August 1956 March 1958

Design Bureau OKB 18

Chief designer C.H. Kovalev

Builders Nr. 402 Severodvinsk


October 1958 -December 1962

1963-1967

Service time January 1961-1967 1964-1991

Number of constructedships

8 7 (converted 658 submarines)

D-2 launch systemwith3 R-13 missiles


Armament

4-533mm torpedo tubes,4- 400mm torpedo tubes

Power Plant 2 pressurized water reactors, 190 MW each2 steam turbines, 17.500 hp each

Length 114 meters

Beam 9.2 meters

Deposit 7.31 meters

Displacement 4080 m3 Surfaced5000 m3 Submerged

Operating depth 240 meters (design)300 meters (maximum)

Speed 18 knots - Surface26 knots - Submerged

Crew 104 men

Endurance 50 days


# number

Name Shipyard LaidDown

Launched

Comm. Stricken

Notes

1 K-19 402Sevmash

10/17/1958

08/08/1959

11/12/1960

1991 07/04/1961reactoraccident1962-64 refit1963-67project 658Mconverted(Hotel II)11/15/1969

collided withUSS SSN-61502/24/1972fire andnucleartorpedoaccidentconverted toSSQN06/04 reactoraccidentnicknamed"Hiroshima"in storage inPolyarny

2 K-33 402Sevmash

--------- --------- 07/05/1961

1988-90

1963-67project 658Mconverted(Hotel II)

3 K-55 402Sevmash

--------- --------- 08/12/1962

----------

1963-67project 658Mconverted(Hotel II)project 658Tconverted toSSNin reserve inPavlovsk

4 K-178

402Sevmash

--------- --------- 12/**/1962

----------

commissionpossibly06/30/19641963-67project 658Mconverted(Hotel II)project 658Tconverted toSSNin reserve inPavlovsk

5 K-40 402Sevmash

--------- --------- 12/28/1962

1988-90

1963-67project 658Mconverted(Hot

el II)1977 becameSSQN,redesignated KS-40

6 K-16 402Sevmash

--------- --------- 06/15/1963

1988-90

1963-67project 658Mconverted(Hotel II)

7 K-145

402Sevmash

--------- --------- 12/19/1963

----------

1963-65project 658Mconverted(Hotel II)1966 project701converted(Hotel III)in storage inSevmorputnaval shipyard

8 K-149

UkrainskyKomsomlets

402Sevmash

--------- --------- 02/12/1964

1988-90

1963-67project 658Mconverted(Hotel II)1969 named

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667A YANKEE IIn 1958 OKB-18 started the development of a new ballistic missile submarine. Initiallywork was undertaken on two versions, of which only one was authorized. A.S.Kassatsiyer, the author of both versions was designated as chief designer. Thedevelopment of the submarine faced significant problems regarding the launch system.During elimination of the problems the project underwent fundamental changes and as aresult the completely new submarine design received the new designation 667A. The newchief designer was S. I. Kovalev. The revised 667A submarine was both developed andauthorized in 1962.

The external contours of the submarine were designed to achieve minimal resistancewhen operating under water. Unlike previous submarines, the horizontal hydroplaneswere arranged on the sail. The cylinder-shaped pressure hull is divided into 10compartments and has an exterior diameter of 9.4m.

The SSBN 667A is equipped with the D-5 launch system and 16 R-27 missiles with arange of about 2400 km. They are arranged in two rows in the fourth and fifthcompartments. The missiles can be launched from a depth of 40-50 meters below thesurface, while the submarine is moving at a speed of up to 3-4 knots. The missiles arefired in four salvos each comprising four missiles. The time needed for pre-launchpreparation is 8 minutes, and within a salvo the missiles are fired at intervals of 8seconds. After each salvo the submarine needs three minutes return to the launchingdepth and between the second and third salvo it takes 20-35 minutes to pump water fromthe tanks into the launching tubes.

The primary propulsion machinery includes two self-contained units [port and starboard],each of which consists of a pressurized water reactor reactor, and an independentturbogear assembly. The maximum speed when submerged is 27 knots. The auxiliarypropulsion motors can be used for torpedo firing, to maintain electric power duringemergency and provide for stand-by capability of the boat while on the surface.

To reduce the noise of the submarine special propellers were created, the pressure hullwas covered with sound-absorbing rubber and the external hull was covered with aantihydroacoustic coating. The footings under the main and auxiliary propulsion systemsare also isolated by a layer of rubber.

The 667A SSBNs were equipped with the "Cloud" battle management system whichcould receive signals up to a depth of 50 meters with the help of the towed antenna"Paravan." The first four 667A Yankee submarines employed the "Sigma" navigationsystem whereas the follow-on ships were equipped with the "Tobol" -- the first Sovietnavigational system that used a satellite navigation system. This system provided reliablenavigation in the Arctic Region and in the Pacific Ocean and also sustained theoperational capability of the missiles at high latitudes down to 85 degrees.

The first 667A Yankee submarine, with the tactical designation K-137, was launched in1964 at the Northern machine-building enterprise in Severodvinsk. In July 1967 thesubmarine "K-137" completed sea trials and at the end of 1967 it was introduced into theNorthern fleet. Between 1967 and 1974 a total of 34 strategic submarines of the 667Aclass were build. 24 submarines were launched in Severodvinsk and 10 in Komsomolskna Amure.

In 1972-1983 the Yankee submarines along with older submarines were re-equipped withthe D-5U launch system and R-27U missiles. The R-27U missile had a greater range -- upto 3000 km -- and carried multiple reentry vehicles. The upgraded submarine wasdesignated as 667AU.

In 1967 the first 667A ballistic submarines to form part of the Northern fleet wereincorporated into the 31st division of strategic submarines, which was based in the port ofSayda. At the end of the 60s the 19th division of strategic submarines was also equippedwith 667A submarines. Both divisions formed part of a structure consisting of 12squadrons, which in December 1969 was transformed into the 3rd flotilla of submarines.

Two divisions of 667A submarines of the Pacific fleet — 8th and 25th- - were based atKamchatka. In the middle of the 1970s a unit of 667A SSBNs was transferred toPavlovsk.

In May, 1974 near the Navy base in Petropavlovsk a ballistic missile submarine of the667A class collided with the American attack submarine "Pintado" (SSN-672) in a depthof about 65m. The Soviet submarine was only lightly damaged.

On 03 October 1986 on board of the ballistic missile submarine "K-219" of the 667AUclass an explosion took place that sparked off a fire. The cause was a depressurization ofthe reactor pit. The submarine was located 970 km east of the Bermuda Islands. The crewof a boat managed to surface the submarine and muffle the reactors. As a result of theaccident four people were killed. The submarine was towed but on 06 October it had tobe scuttled into a depth of 5,500 meters. The United States Navy normally does notcomment on submarine operations. But the US Navy issued a statement regarding therelease of the book "Hostile Waters" and an HBO movie of the same name, based on theincidents surrounding the casualty of the Russian Yankee submarine K-219. The UnitedStates Navy "categorically denies that any U.S. submarine collided with the RussianYankee submarine (K-219) or that the Navy had anything to do with the cause of thecasualty that resulted in the loss of the Russian Yankee submarine."

Between 1979 and 1994 all Yankee submarines were removed from operational statusand their missile compartments cut out to comply with arms control agreement ceilings.During their operation time the 667A and 667AM Yankee submarines had carried out590 patrols all over the world. Two of the submarines were taken out of service in 1979,two in January 1980, one in January 1981, two in January 1982, one in November 1982,one in June 1983, one in January 1984, two in April 1985, two in March 1986, two in1987, and the rest in 1988 and 1989.

A number of Yankee ballistic missile submarines were modified to perform othermissions.

In 1977 the "K-140" submarine was equipped with the first D-11 Soviet sea basedsolid-fuel missiles and received the designation 667AM Yankee II. The 12 P-31missiles loaded on the submarine could be fired from a depth up to 50 meters. Thetorpedo tubes could be reloaded in less than in one minute using a "dry" launchtechnique. Its submerged displacement increased to 10,000 tons.

The submarine "K-420" was converted to test the "Meteorite" (SS-N-24) cruisemissiles. The re-equipped submarine received the designation 667M (YankeeSSGN or Yankee Sidecar). The length and the width of the SSBN were increasedup to 153 m and 15-16 m respectively. Outside of the pressure hull 12 launchersfor the SS-N-24 missiles were located. The re-equipment began in December1982 and the first launches of a cruise missile was conducted in December 1983.

From 1982 to 1991 some Yankee I SSBNs were equipped with 20 up to 40launchers of SS-N-21 "Grenade". They were designated as 667AT (YankeeNotch). Unlike the "K-420" that was converted to carry the SS-N-24 missiles, theshape of the deck behind the cabin was not altered. The displacement of thesubmarine was increased up to 11,500 tons and the body was lengthened to 140meters.

From 1979-1984 the ballistic missile submarine "K-403" was converted into asubmarine for special purposes designated as Yankee Pod. Instead of a missilecompartment, it had was equipped with radio equipment and a towedhydroacoustic station.

In 1990 the SSBN "K-411" was converted under the project 09774 (YankeeStretch) into a carrier of supersmall "KS-411" submarines.

Between 1988 and 1994 most converted Yankee submarines were removed fromoperational status. The converted K-411 (Yankee Stretch) and K-420 (Yankee Sidecar)are reliably reported to remain in service, and some reports also suggest that K-395 [aYankee Notch] and K-403 [Yankee Pod] may also remain in service.

SpecificationsSoviet Designation 667A

667AU Navaga667 Am Navaga

US-Designation Yankee I Yankee II

Development began 1958

Design Bureau Central Design Bureau for Marine Engineering "Rubin"

Chief designer S.H. Kovalev O.YA. Margolin

Builders SeverodvinskKomsomolsk na Amure

Construction and 667A: 1964-1974 1977-1980

Outfit 667AU: 1972-1983

Service time 667A: 1967-1983667AU: 1972-1994

1980-1990

Number of ships 34 1 converted

667A: D-5 launch systemwith16 R-27 missiles

667AU: D-5U launchsystem with16 R-27U missiles


Armament

4-533mm torpedo tubes2-400mm torpedo tubes

Power Plant 2 pressurized water reactors2 steam turbines, 52.000 hp each

Length 132 meters

Beam 11.6 meters

Deposit 8 meters

7760 m3 SurfacedDisplacement

9600 m3 Submerged 10000 m3 Submerged

Maximum depth 400 meters

12 knots SurfaceSpeed

25 knots Submerged 24 knots Submerged

Crew 120 men 130 men

Endurance 70 days


# number

Name

Shipyard LaidDown

Launched

Comm. Stricken

Notes

1 K-137

Leninets

402Sevmash

11/09/1964

08/28/1966

11/05/1967

----------

1994 deactivated1998 planned toscrap

2 K-140

402Sevmash

----------

----------

12/30/1967

1990 08/23/1968 reactoraccident1977-80 project

667AM converted(Yankee II)

3 K-26 402Sevmash

----------

----------

09/03/1968

----------

4 K-32 402Sevmash

----------

----------

10/26/1968

1999 1999 dismantled

5 K-216

402Sevmash

----------

----------

12/27/1968

----------

in storage in SaydaBay

6 K-207

402Sevmash

----------

----------

12/30/1968

----------

7 K-210

402Sevmash

----------

----------

08/06/1969

----------

in storage inSeverodvinsk

8 K-249

402Sevmash

----------

----------

09/27/1969

----------

9 K-253

402Sevmash

----------

----------

10/28/1969

----------

10

K-395

402Sevmash

----------

----------

12/05/1969

1982-91 project667AT("Grusha")converted toSSGN(YankeeNotch)1999 remainsoperational

11

K-408

402Sevmash

----------

----------

12/25/1969

----------

1982-91 project667AT("Grusha")converted toSSGN(YankeeNotch)

12

K-411

402Sevmash

----------

----------

08/31/1970

project 09780converted to amidgetcarrier(YankeeStretch),redesignatedKS-411remains operational

13

K-418

402Sevmash

----------

----------

09/22/1970

1999 project667AT("Grusha")converted toSSGN(Yankee

Notch)

14

K-420

402Sevmash

----------

----------

10/29/1970

1979-80 project667M("Andromeda")converted toSSGN(YankeeSidecar)

15

K-423

402Sevmash

----------

----------

11/13/1971

----------

project667AT("Grusha")convertedtoSSGN(YankeeNotch)

16

K-426

402Sevmash

----------

----------

12/22/1970

----------

17

K-415

402Sevmash

----------

----------

12/30/1971

1994 1982-91 project667AT("Grusha")converted toSSGN(YankeeNotch)1994 dismantled

18

K-403

402Sevmash

----------

----------

08/20/1971

1978-80 project09774("Akson")converted to aspecial operationship(YankeePod),redesignated toKS-4031999 remainsoperational

19

K-245

402Sevmash

----------

----------

12/16/1971

----------

20

K-214

402Sevmash

----------

----------

12/31/1971

----------

21

K-219

402Sevmash

----------

----------

12/31/1971

1986 10/06/1986 lost

22

K-228

402Sevmash

----------

----------

12/31/1972

1995?

dismantled

23

K-241

402Sevmash

----------

----------

12/23/1971

1994?

dismantled

2 K- 402 --------- --------- 12/09/1 ------ in storage in

4 444 Sevmash - - 972 ---- Severodvinsk

25

K-399

199Komsomolsk

----------

----------

12/24/1969

----------


26

K-434

199Komsomolsk

----------

----------

10/21/1970

----------

27

K-236

199Komsomolsk

----------

----------

12/27/1970

----------


28

K-389

199Komsomolsk

----------

----------

1970 ----------

29

K-252

199Komsomolsk

----------

----------

1971 ----------

30

K-258

199Komsomolsk

----------

----------

1971 ----------

31

K-446

199Komsomolsk

----------

----------

1971 ----------

32

K-451

199Komsomolsk

----------

----------

1971 ----------

33

K-436

199Komsomolsk

----------

----------

1972 ----------

34

K-430

199Komsomolsk

----------

----------

1972 ----------

http://www.fas.org/nuke/guide/russia/slbm/yankee_DNSC8704342_JPG.jpg

http://www.fas.org/nuke/guide/russia/slbm/yankee_DNST8700760_JPG.jpg





667AM YANKEE IIIn 1977 the "K-140" submarine was equipped with the first D-11 Soviet sea based solid-fuel missiles and received the designation 667AM Yankee II. The 12 P-31 missilesloaded on the submarine could be fired from a depth up to 50 meters. The torpedo tubescould be reloaded in less than in one minute using a "dry" launch technique. Itssubmerged displacement increased to 10,000 tons.

The Nunn-Lugar Cooperative Threat Reduction program is scheduled to dismantle 25Delta-class, five Typhoon-class, and one Yankee-class ballistic missile submarinescapable of launching over 400 missiles with over 1,700 warheads, by the year 2003. Asof September 1999 US specialists had helped disassemble one Yankee- and six Delta-class submarines, while the Russians had destroyed another five ballistic missile subs ontheir own using American equipment.

SpecificationsSoviet Designation 667A

667AU Navaga667 Am Navaga

US-Designation Yankee I Yankee II



Chief designer S.H. Kovalev O.YA. Margolin

Builders SeverodvinskKomsomol Na Amur


667A: 1964-1974667AU: 1972-1983

1977-1980

Service time 667A: 1967-1983667AU: 1972-1994

1980-1990

Number of ships 34 1

667A: D-5 launch systemwith16 R-27 missiles

667AU: D-5U launchsystem with16 R-27U missiles


Armament



Length 132 meters

Beam 11.6 meters

Deposit 8 meters

7,760 tons SurfacedDisplacement

9,600 tons Submerged 10,000 tons Submerged





Self-sufficiency 70 days


# number Name Shipyard LaidDown

Launched Comm. Stricken Notes

1 K-140 402 Sevmash ----------

---------- 12/30/1967 1990 08/23/1968reactoraccident1977-80project667AMconverted(YankeeII)

http://www.fas.org/nuke/guide/russia/slbm/pl667am.jpg

667AR YANKEE NOTCHThe submarine "K-420" was converted to test the "Meteorite" (SS-N-24) cruise missiles.The re-equipped submarine received the designation 667M (Yankee SSGN or YankeeSidecar). The length and the width of the SSBN were increased up to 153 m and 15-16 mrespectively. Outside of the pressure hull 12 launchers for the SS-N-24 missiles werelocated. The re-equipment began in December 1982 and the first launches of a cruisemissile was conducted in December 1983.

From 1982 to 1991 some Yankee I SSBNs were equipped with 20 up to 40 launchers ofSS-N-21 “Grenade”. They were designated as 667AT (Yankee Notch). Unlike the "K-420" that was converted to carry the SS-N-24 missiles, the shape of the deck behind thecabin was not altered. The displacement of the submarine was increased up to 11,500tons and the body was lengthened to 140 meters.

Between 1988 and 1994 most converted Yankee submarines were removed fromoperational status. Some reports suggest that K-395 [a Yankee Notch] may remain inservice.

SpecificationsSoviet Designation 667AT Navaga

US-Designation Yankee Notch

Development began

Design Bureau Central Design Bureau for Marine Engineering"Rubin"

Chief designer S.H. Kovalev

Builders Severodvinsk, 'Komsomol Na Amur


1982-1991

Service time 1983-1994?

Number of ships 6

Armament 20-40 SS-N-21 "Grenade" missiles




Length 132 meters

Beam 11.6 meters

Deposit 8 meters

Displacement 9.250 tons Surfaced11,500 tons Submerged


Speed 12 knots Surface25 knots Submerged

Crew 120 men

Endurance 70 days

http://www.fas.org/nuke/guide/russia/slbm/667ar_1.jpg

http://www.fas.org/nuke/guide/russia/slbm/667ar_10.jpg

http://www.fas.org/irp/dia/product/yank_n.jpg

http://www.fas.org/nuke/guide/russia/slbm/yankee_notch_DDST8911751_JPG.jpg

667B DELTA IIn comparison with the Yankee submarines the Delta submarines have a greaterdisplacement and larger external dimensions. The pressure hull of the 667B submarineconsists of ten compartments.

The 667B submarines were equipped with D-9 launch systems and 12 R-29 missiles. Therange of the R-29 missiles allowed the 667B to maintain constant combat patrol in remoteareas. They are also capable of maintaining combat alert when moored at their bases. TheDelta-class submarines could deploy on alert patrols in the marginal ice seas of the Sovietarctic littoral, including the Norwegian and Barents seas. Consequently, unlike theirpredecessors they no longer needed to pass through Western SOSUS sonar barriers tocome within range their targets. And deployed close to home, they could be protected in"bastions" by the rest of the Soviet Navy. The submerged firing of the missiles can beconducted in a single salvo while the submarine is moving at a speed of 5 knots. A highdegree of automation allowed a significant reduction in the time required for pre-launchpreparations in comparison with the Yankee class. To improve the accuracy of themissiles, the Delta I submarines are equipped with the "Tobol-B" navigation system andthe "Cyclone-B" satellite navigation system.

The development of the 667B Delta I submarine was authorized in 1965, with the RubinCentral Design Bureau for Marine Engineering was in charge of the program. The Delta Isubmarine "K-279" was build at the Northern machine-building enterprise inSeverodvinsk and was incorporated into the Northern fleet on 22 December 1972.Between 1972 and 1977 18 Delta I submarines were launched, 10 in Severodvinsk and 8in Komsomol Na Amur.

In 1973 the 667B submarine was incorporated into a division of strategic submarines ofthe Northern fleet based at Yagyelnaya bay. The formation of the 41st division ofstrategic submarines consisting of Delta I submarines was completed the same year. In1974 the division was incorporated into the 11th flotilla of submarines. The Delta Isubmarines which belong to the Pacific fleet form the 25th division of strategicsubmarines and are based on Kamchatka. In the early 1990s the submarines weretransferred to the Pavlovsk base in Primorye. The zones of patrol of the Northern fleetsubmarines were located in the area around Greenland and the Barents Sea, two or threedays away from the submarine bases. The Delta I submarines that served in the Pacificfleet began patrols in 1976.

In 1991 nine Delta I submarines served in the Northern and Pacific Fleet. Theirdecommissioning began in 1994, and by 1997 the missile compartments were scheduledto be removed. It is anticipated that all 667B submarines will be decommissioned incompliance with the provisions of the START-1 treaty. The prcise tatus of individualhulls, including the dates on whcih they may have been withdrawn from service, cannotbe readily determined from the public record.

As of June 2000 the Russian Navy claims that it operates 26 strategic nuclear submarinescarrying 2,272 nuclear warheads on 440 ballistic missiles. This force is said to consist of5 Typhoon class submarines, 7 Delta-IV class submarines, and 13 Delta-III classsubmarines [which only adds up to 25, not 26 submarines]. Not all of these submarinesare presently seaworthy. The Russian Navy reportedly believes that 12 strategic nuclearsubmarines with ballistic missiles represent the minimum necessary force structure.


SpecificationsSoviet Designation 667B Murena 667 BD Murena-M

US-Designation Delta I Delta II

Development began 1965 November 1967




Severodvinsk


1971-1977 1973-1975

Service time 1973- 1975-1996




Armament

4-533mm torpedo tubes 4-533mm torpedo tubes2-400mm torpedo tubes

2 pressurized water reactorsPower Plant

2 steam turbines, 52.000 hpeach

2 steam turbines, 55.000hp each

Length 139 meters 155 meters

Beam 12 meters

Deposit 9 meters

Displacement 9000 m3 Surfaced 10500 m3 Submerged

11000m3 Surfaced 13000 m3 Submerged





Endurance 80 days


# number


Launched

Comm. Stricken

Notes

1 K-279

402 Sevmash 1971

01/**/1972

12/22/1972

----------

10/30/1986collided withUSS SSN-7101992 inreserve1998 plannedto scrap

2 K-447

402 Sevmash ----------

1973 ---------- ----------

1994 defueled

3 K-450

402 Sevmash ----------

1973 ---------- ----------

4 K-336

199Komsomolsk

----------

1974 ---------- ----------

hull NO.possibly K-366

5 K-385

402 Sevmash ----------

1974 ---------- ----------

6 K-417

199Komsomolsk

----------

1974 ---------- ----------

7 K-457

402 Sevmash ----------

1974 ---------- ----------

05/05/1998missile fuelleak,inreserve

8 K- 402 Sevmash ----- 1974 ---------- ------- hull NO.

465 ----- --- possibly K-453

9 K-460

402 Sevmash ----------

1975 ---------- ----------

10

K-472

402 Sevmash ----------

1975 ---------- 1999 1999dismantled

11

K-475

402 Sevmash ----------

1975 ---------- 1999 1999dismantled

12

K-477

199Komsomolsk

----------

1975 ---------- ----------

13

K-497

199Komsomolsk

----------

1975 ---------- ----------

14

K-171

402 Sevmash ----------

1976 ---------- ----------

15

K-500

199Komsomolsk

----------

1976 ---------- 1999 remainsoperational ??

16

K-512

70 LetVLKSM

199Komsomolsk

----------

1976 ---------- ----------

10/28/1988named1991unnamed

17

K-523

199Komsomolsk

----------

1977 ---------- ----------

18

K-530

199Komsomolsk

----------

1977 ---------- 1999 remainsoperational ??

http://www.fas.org/nuke/guide/russia/slbm/667b_1.jpg

667BD DELTA IIThe 667BD was primarily developed to increase the number of missiles on strategicsubmarines. Its development was approved in June 1972 under the direction of the RubinCentral Design Bureau for Marine Engineering. The 667B Delta I served as the basis forthe main design features. The pressure hull was lengthened by 16 meters in the area ofthe fourth and fifth compartments where four additional missile tubes were located. Thedisplacement increased in 1,500 tons, and the full speed decreased 1 knot.

The 667BD submarines are equipped with the D-9D launch system and 16 R-29DDmissiles. During the development of the new ballistic missile submarine several measureswere applied to decrease the radiated noise level. The steam turbines include a two-spoolsystem of shock-absorbers, the pipelines and hydraulic devices are isolated from the hullsand a new hydroacoustic coating was applied.

The first 667BD entered the Navy on 30 September 1975. Between 1973 and 1975 foursubmarines of this project were constructed at the Northern machine-building enterprisein Severodvinsk. The 667BD submarines formed part of the 3rd flotilla of submarines ofthe Northern fleet based in the Yagyelnaya bay. In 1996 one submarine was removedfrom operational status.

It is anticipated that all 667BD submarines will be decommissioned in compliance withthe provisions of the START-1 treaty.


SpecificationsSoviet Designation 667B Murena 667 BD Murena-M

US-Designation Delta I Delta II

Development began 1965 November 1967




Severodvinsk

Construction and 1971-1977 1973-1975

Outfit

Service time 1973- 1975-1996




Armament

4-533mm torpedo tubes 4-533mm torpedo tubes2-400mm torpedo tubes

2 pressurized water reactorsPower Plant

2 steam turbines, 52.000 hpeach

2 steam turbines, 55.000hp each

Length 139 meters 155 meters

Beam 12 meters

Deposit 9 meters

9000 m3 Surfaced 10500 m3 SubmergedDisplacement

11000m3 Surfaced 13000 m3 Submerged





Endurance 80 days


# number


Launched

Comm. Stricken

Notes

1 K-182

ShestidesyatiletieVelikogoOktyabrya

402Sevmash

04/**/1973

01/**/1975

09/20/1975

----------

11/04/1977named1996 inreserve

2 K-92 402Sevmash

04/**/1973

01/**/1975

12/17/1975

----------

1996 inreserve

3 K-193

402Sevmash

1974 1975 12/30/1975

1999 12/1997prepared for

decommissioning1999dismantled

4 K-421

402Sevmash

1974 1975 12/30/1975

----------

1996 inreserve2000planned to bedefuelled

http://www.fas.org/nuke/guide/russia/slbm/pl667bd1.jpg

http://www.fas.org/nuke/guide/russia/slbm/667bd_2.jpg




667BDR DELTA IIIThe development of the 667BDR Delta III ballistic missile submarine began in 1972 atthe Rubin Central Design Bureau for Marine Engineering. This strategic submarine isequipped with the D-9R launch system and 16 R-29R missiles, and is the first submarinethat can fire any number of missiles in a single salvo.

The R-29R missile is the first sea-based Soviet ballistic missile carrying 3 to 7 multipleindependently targetable reentry vehicles (MIRVs), with a range of 6,500 to 8000 km,depending on the number of reentry vehicles.

The Delta III is equipped with the "Almaz -BDR" battle management system ensuringfiring of deep-water torpedos. The inertial navigational system "Tobol-BD" is of theDelta II was replaced with the "Tobol-M-1" system, and subsequently with the "Tobol-M-2". The Delta III is also equipped with the "Bumblebee" hydroacoustic navigationalsystem to determinate its position through hydroacoustic buoys. Instead of thehydroacoustic system "Kerch" was used on the 667BD submarines, the Delta III uses thenew "Rubikon" hydro-acoustic system.

The advanced Delta III SSBN entered service in 1976, and by 1982 a total of fourteensubmarines were commissioned. All of them were build at Severodvinsk. The operationallifetime of these submarines is estimated to be 20-25 years. The Delta III submarineswhich served in the Northern fleet formed a division and were based in the port of Saydain the Yagyelnaya bay and in the Olyenya port. In the early 90s the ballistic missilesubmarines were transferred to Yagyelnaya. The Delta III that served in the Pacific Fleetformed a division of SSBNs which is based on Kamchatka.

When the START-1 treaty was signed in 1991 five 667BDR SSBNs still served in theNorthern (3 - in Yagyelnaya, 2 - in Olyenyey ) and nine in the Pacific Fleet. One Delta IIIsubmarine of the Northern fleet was decommissioned in 1994. The Nunn-LugarCooperative Threat Reduction program is scheduled to dismantle 25 Delta-class, fiveTyphoon-class, and one Yankee-class ballistic missile submarines capable of launchingover 400 missiles with over 1,700 warheads, by the year 2003. As of September 1999 USspecialists had helped disassemble one Yankee- and six Delta-class submarines, while theRussians had destroyed another five ballistic missile subs on their own using Americanequipment.

As of June 2000 the Russian Navy claims that it operates 26 strategic nuclear submarinescarrying 2,272 nuclear warheads on 440 ballistic missiles. This force is said to consist of5 Typhoon class submarines, 7 Delta-IV class submarines, and 13 Delta-III classsubmarines [which only adds up to 25, not 26 submarines]. Not all of these submarinesare presently seaworthy. The Russian Navy reportedly believes that 12 strategic nuclearsubmarines with ballistic missiles represent the minimum necessary force structure.According to media reports a classified presidential decree of 04 March 2000 establishedthis force goal for the period through 2010.

SpecificationsSoviet Designation 667BDRM Dolphin

US-Designation Delta IV






1975-1981

Service time 1976-

Number of ships 7

D-9 RM launch system with16 R-29R missiles

Armament



Propellers 2 × 7 blade fixed-pitch

Length 155 meters

Beam 11.7 meters

Draft 8.7 meters

Displacement 8,940 tons Surfaced10,600 tons Submerged

Operational depth 320 meters (design)400 meters (maximum depth)

Speed 13-14 knots Surface22-24 knots Submerged

Crew 130 men

Endurance 80 days


# number

Name Shipyard LaidDow

Launched Comm. Stricken

Notes

n

1 K-441 26ZvezdaKPSS

402Sevmash

1975 1976 12/**/1976

----------

04/1992unnamed1996 inreserve

2 K-424 402Sevmash

----------

---------- 1977 ----------

1997 inreserve

3 K-449 402Sevmash

----------

---------- 1977 ----------

1996 inreserve

4 K-455 402Sevmash

----------

---------- 1978 ----------

1998-99inreserve

5 K-490 402Sevmash

----------

---------- 1978 ----------

1998-99inreserve

6 K-487 402Sevmash

----------

---------- 1978 ----------

1998-99inreserve

7 K-44 402Sevmash

----------

---------- 1979 ----------

1997 inreserve

8 K-496 402Sevmash

1976 01/**/1978

1979

9 K-506 402Sevmash

1977 01/**/1979

1979

10

K-211 402Sevmash

1977 01/**/1979

1980

11

K-223 402Sevmash

----------

---------- 1980 ----------

1998-99inreserve

12

K-180 402Sevmash

1978 12/**/1980

1980

13

K-433 402Sevmash

----------

---------- 1981 ----------

1997 inreserve

14

K-129 402Sevmash

1979 12/**/1981

1981 ----------

1997 inreservepossiblystill in

operation

http://www.fas.org/nuke/guide/russia/slbm/pl667bdr.jpg

http://www.fas.org/nuke/guide/russia/slbm/pl667bdr1.jpg

http://www.fas.org/nuke/guide/russia/slbm/667bdr_1.jpg

http://www.fas.org/nuke/guide/russia/slbm/667bdr_11.jpg

667BDRM Dolphin DELTA IVThe 667BDRM Delta IV submarine, which was constructed parallel to the Typhoonclass, is a further modification of the previous Delta. In comparison with the Delta IIIsubmarine the diameter of the pressure hull was increased and the bow was lengthened.As a result the displacement of the submarine was increased by 1,200 tons and it was 12meters longer. To increase the reliability of the pressure hull, the tip and intercut-offbulkheads are made of specially processed steel.

The Delta IV submarines employs the D- 9RM launch system and carries 16 R-29RMliquid-fueled missiles which carry four multiple independently targetable reentryvehicles.Unlike previous modifications, the Delta IV submarine is able to fire missiles inany direction from a constant course in a circular sector. The underwater firing of theballistic missiles can be conducted at a depth of 55 meters while cruising at a speed of 6-7 knots. All the missiles can be fired in a single salvo.

The 667BDRM Dolphin submarines are equipped with the TRV-671 RTM missile-torpedo system that has four torpedo tubes with a calibre of 533 mm. Unlike the Delta III,it is capable of using all types of torpedos, antisubmarine torpedo-missiles andantihydroacoustic devices. The battle management system "Omnibus-BDRM" controlsall combat activities, processing data and commanding the torpedo and missile-torpedoweapons. The "Shlyuz" navigation system provides for the improved accuracy of themissiles and is capable of stellar navigation at periscope depths. The navigational systemalso employs two floating antenna buoys to receive radio-messages, target destinationdata and satellite navigation signals at great depth. The submarine is also equipped withthe "Skat- VDRM" hydroacoustic system.

During the development of the 667BDRM SSBN several measures were included toreduce its noise level. The gears and equipment are located on a common base isolatedfrom the pressure hull, and the power compartments are also isolated. The efficiency ofthe antihydroacoustic coatings of the light outer hull and inner pressure hulls have beenincreased. Newly designed five-bladed propellers with improved hydroacousticcharacteristics are employed.

The development of the Delta IV submarine began on 10 September 1975 by the RubinCentral Design Bureau for Marine Engineering. The first Dolphin submarine waslaunched in January 1985 and in December 1985 the first Dolphin submarine wasintroduced into Northern fleet. Between 1985 and 1990 seven Dolphin SSBN wereconstructed by the Sevmashpredpriyatiye Production Association in Severodvinsk.

Initially all the Delta IV submarines were based with the Northern Fleet at Olenya. Allthe submarines of this class serve in the 3rd flotilla of strategic submarines of theNorthern fleet, which has relocated to Yagyelnaya.

The operational lifetime of these submarines is estimated to be 20-30 years, though inorder to operate a ship for this period requires that a major overhaul be performed every7-8 years. Otherwise, a submarine's service life shrinks to 10-15 years. The four-yearrepair works on the first Delta-IV (K-51) submarine were completed in November 1999at Zvezdochka shipyard in Severodvinsk. The submarine was expected to operate from itshome base in Gadzhievo at the Kola Peninsula for 5-7 more years.

As of June 2000 the Russian Navy claims that it operates 26 strategic nuclear submarinescarrying 2,272 nuclear warheads on 440 ballistic missiles. This force is said to consist of5 Typhoon class submarines, 7 Delta-IV class submarines, and 13 Delta-III classsubmarines [which only adds up to 25, not 26 submarines]. Not all of these submarinesare presently seaworthy. The Russian Navy reportedly believes that 12 strategic nuclearsubmarines with ballistic missiles represent the minimum necessary force structure.According to media reports a classified presidential decree of 04 March 2000 establishedthis force goal for the period through 2010.

SpecificationsSoviet Designation 667BDRM Dolphin

US-Designation Delta IV

Development began September 1975





February 1981-1992

Service time December 1985-

Number of ships 7

D-9 RM launch system with16 R-29 RM missiles

Armament



Propellers 2 × 7 blade fixed-pitch

Length 167 meters

Beam 12 meters

Draft 8.8 meters

Displacement 11,740 tons Surfaced

18,200 tons Submerged

Operational depth 320 meters (design)400 meters (maximum depth)


Crew 130 men

Endurance 80 days


# number

NameShipyar

d LaidDown

Launched

Comm. Stricken

Notes

1 K-51 402Sevmash

02/23/1981

01/**/1985

12/29/1986

1996-11/1999deactivated for refit2000 in service

2 K-84 402Sevmash

11/**/1984

12/**/1985

02/**/1986

in service

3 K-64 402Sevmash

11/**/1985

12/**/1986

02/**/1988

in service

4 K-114

402Sevmash

12/**/1986

09/**/1987

02/**/1989

late 1999 planned todismantle atZvezdochka

5 K-117

402Sevmash

09/**/1987

09/**/1988

03/**/1990

in service

6 K-18 402Sevmash

09/**/1988

11/**/1989

02/**/1991

in service

7 K-407

Novomoskovsk

402Sevmash

11/**/1989

01/**/1991

02/20/1992 in service

8K-???

402Sevmash

Cancelled underconstruction

9K-???

402Sevmash


http://www.fas.org/nuke/guide/russia/slbm/pl667bdrm1.jpg

http://www.fas.org/nuke/guide/russia/slbm/plbdrm.jpg






http://www.fas.org/nuke/guide/russia/slbm/delta-4_DDST8911752_JPG.jpg

http://www.fas.org/nuke/guide/russia/slbm/667bdrm_1.jpg

http://www.fas.org/nuke/guide/russia/slbm/667bdrm_11.jpg

http://www.fas.org/irp/dia/product/delta_89.jpg

941 TYPHOONDuring the Cold War the Typhoon submarines prowled the waters of the North Atlantic.These submarines do not have to submerge or go to sea to launch their long-rangemissiles. They are able to do so tied up at their docks. The Typhoon is the world’s largestsubmarine and was one of the most feared weapons of the Cold War. Each submarine iscapable of carrying twenty long-range ballistic missiles with up to 200 nuclear warheadsthat were once aimed at the United States.

The design of the Typhoon submarine is multi-hulled and bears resemblance to acatamaran. The submarine has two separate pressure hulls with a diameter of 7.2 m each,five inner habitable hulls and 19 compartments. The pressure hulls are arranged parallelto each other and symmetrical to a centerplane. The missile compartment is arranged inthe upper part of the bow between the pressure hulls. Both hulls and all compartments areconnected by transitions. The pressure hulls, the centerplane and the torpedocompartment are made of titanium and the outer light hull is made of steel. A protectedmodule, comprising the main control room and electronic equipment compartment, isarranged behind the missile silos above the main hulls in a centerplane under the guard ofretractable devices.

The submarine's design includes features to enable it to both travel under ice and for ice-breaking. It has an advanced stern fin with horizontal hydroplane fitted after the screws.The nose horizontal hydroplanes are in the bow section and are retractable into the hull.The retractable systems include two periscopes (one for the commander and one forgeneral use), radio sextant, radar, radio communications, navigation and direction-findermasts. They are housed within the sail guard. The sail and sail guard have a reinforcedrounded cover for ice-breaking.

The submarine is equipped with the D-19 launch system with 20 solid-fuel propellant R-39 missiles which have a range of up to 10,000 km. They are arranged in silos in tworows in front of the sail between the main hulls. The Typhoon has an automated torpedoand missile loading system including 6 torpedo tubes with calibres of 650 and 533 mm.

The main machinery consists of two reactors each and two steam turbines of 190 MWthat provide a maximum speed of 25-27 knots. Compared to the first and secondgeneration of SSBNs the Typhoon enjoys far greater maneuverability Despite of its largerdisplacement the Typhoons are less noisy than their predecessors. To reduce the acousticsignature a two-spool system of rubber-cord pneumatic shock-absorption is employed aswell as a block layout of gears and equipment, a new sound isolation andandrihydroacoustic coating.

The Typhoons are equipped with the "Slope" hydroacoustic system that consists of fourhydroacoustic stations. The "Slope" system allows to track 10-12 vessels simultaneously.It also employs two floating antenna buoys to receive radio messages, target designationdata and satellite navigation signals at great depth and under an ice cover.

The development of the 941 heavy strategic submarine was authorized in December1972, and on 19 December 1973 the governmental officially issued the order to designand build the 941 ballistic missile submarine. The developer was the Leningrad designbureau which is now the Central Design Bureau for Marine Engineering "Rubin". Afterintensive testing the heavy ballistic missile submarine 941-"TK-208" was commissionedin September 1980 and introduced into the Northern fleet on 12 December 1981.Between 1981 and 1989 six Typhoon submarines entered service. They formed part ofthe 1st flotilla of atomic submarines based in the Western Theater of the Northern fleetbased at Nyerpichya. A seventh vessel was begun but never finished.

The Typhoon submarines were initially intended to be retrofitted with a replacement ofthe D-19 launch system with an advanced system, and the new SS-N-28 missile. The leadunit of this class, the TK-208, had been in overhaul since 1992 with the intent ofreceiving these modifications, but it now appears that it will not return to service. All butone of the Typhoon class submarines are slated to be withdrawn from service within afew years, and it is unlikely that units of the class would be modified to accomodate newmissiles.

In 1997 two Typhoon submarines were decommissioned. The operational lifetime ofthese submarines is estimated to be 20-30 years, though in order to operate a ship for thisperiod requires that a major overhaul be performed every 7-8 years. Otherwise, asubmarine's service life shrinks to 10-15 years. Navy officials claim that it is possible toextend operations of the Typhoons until 2005-2007.

The Nunn-Lugar Cooperative Threat Reduction program is scheduled to dismantle 25Delta-class, as many as five Typhoon-class, and one Yankee-class ballistic missilesubmarines capable of launching over 400 missiles with over 1,700 warheads, by the year2003. In 1999 Secretary of Defense Bill Cohen approved the contract to begindismantlement of the first Typhoon nuclear submarine. If and when all of thesesubmarines are dismantled, 1,200 nuclear weapons will be removed from operationalsystems.

As of June 2000 the Russian Navy claimed that it operates 26 strategic nuclearsubmarines carrying 2,272 nuclear warheads on 440 ballistic missiles. This force was saidto consist of 5 Typhoon class submarines, 7 Delta-IV class submarines, and 13 Delta-IIIclass submarines [which only adds up to 25, not 26 submarines]. Not all of thesesubmarines are presently seaworthy. According to one published report as of 1999 only asingle Typhoon remained operational [probably TK-20], and most estimates wouldsuggest that no more than three boats were in service by early 2000.

In January 2000 it was reported that three of six Russian Typhoon-class submarineswould remain in active operation to test the new Bark-class strategic missiles, contrary toboth the plans of the Co-operative Threat Reduction program and reports that Bark-classmissiles had been cancelled due to design failures. The Russian Navy reportedly believesthat 12 strategic nuclear submarines with ballistic missiles represent the minimum

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necessary force structure. According to media reports a classified presidential decree of04 March 2000 established this force goal for the period through 2010.

SpecificationsSoviet Designation 941 Akula

US-Designation Typhoon

Development began December 1973





March 1977-September 1989

Service time December 1981-

Number of ships 6


Armament



Propellers 2×7 blade fixed-pitch shrouded

Length 170-172 meters

Beam 23-23.3 meters

Draft 11-11.5 meters

Displacement 23,200-24,500 tons Surfaced33,800-48,000 tons Submerged

Maximum divingdepth

500 meters


Crew 150 men (50 officers)

Endurance 90-120 days

Class Listing

Boat Chronology

# number

Name

Shipyard LaidDown

Launched

Comm. Stricken

Notes

1 TK-208

402Sevmash

03/03/1977

09/23/1980

12/12/1981

1992 missile accident,deactivated for refit2001 reactivated?

2 TK-202

402Sevmash

10/01/1980

04/26/1982

12/28/1983

2000 1997- deactivated forrefueling2000 dismantled

3 TK-12

402Sevmash

04/27/1982

12/17/1983

12/27/1984

1997- deactivated forrefueling2000 in reserve

4 TK-13

402Sevmash

01/05/1984

02/21/1985

12/29/1985

1997- undergoingoverhaul2000 in reserve

5 TK-17

402Sevmash

02/24/1985

08/**/1986

11/06/1987

in serviceslated fordismantlement ??

6 TK-20

402Sevmash

01/06/1987

07/**/1988

09/04/1989

in service

7TK-210

402Sevmash


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935 BoreiOn 16 October 1996 Commander in Chief of the Russian Navy ADM Feliks Gromovannounced that work would start on a new-generation strategic nuclear-poweredsubmarine, which he said would be "two or three times more powerful" than anysubmarine currently in the fleet.

The keel of the fourth-generation strategic missile submarine Yuri Dolgoruky was laiddown at the Sevmash State Nuclear Ship-Building Centre at Severodvinsk on 2November 1996. The keel-laying was postponed for a week after poor weather made itimpossible for high ranking officials to attend, including First Deputy Defense MinisterAndrei Kokoshin, Presidential Chief of Staff Anatoly Chubais, Moscow mayor YuriLuzkhov, and Admiral Gromov. Kokoshin described the new Yuri Dolgoruky as a state-of-the-art submarine with "substantial improvements" over those currently in service, andChubais termed the new submarine "a totally unique thing, a submarine for the nextcentury."

The city of Moscow is sponsoring the project, as the lead vessel is named after PrinceDolgoruky, the traditional founder of the city. The wages of shipyard workers and thecrew of the new boat will [reportedly] be paid by the city in the event that the federalgovernment is unable to pay. So-called "Presentation" weapons were commonplace in theRed Army during the Great Patriotic War. Presentation weapons were almost always theresult of monetary collections taken up locally and voluntarily, and offered towards thecost of various vehicles or other items in the name of some personality or entity. Thus,the workers of a factory, town, or even just local citizens could take up a collection and"buy" a tank or aircraft (etc.) in the name of their Factory, group, or perhaps a local oreven national figure -- contemporary or historical.

One of the oldest Russian annals, the Lavrenty Chronicle, was compiled in NizhnyNovgorod at the request of Prince Dmitry Konstantinovich. It contains "The Instructionsto His Children of Vladimir Monomakh". Vladimir Monomach ruled in Kiev, the thencapital of the Russian state, between 1113 and 1125. He was the father of YuriDolgoruky, the founder of Moscow. The meeting of Prince Dolgoruky and PrinceSvyatoslav Olgovich on 04 April 1147 in Moscow is the oldest mentioning of Moscow inchronicles.

This is the first submarine of the new Borei-class [Boreas], with a length of 170 meters, abody diameter around 10 metres, and a submerged speed of over 25 knots (over 45km/h).With about half the displacement of the Typhoon, the 935 class will nonetheless carry 20SLBMs of a new type.

The lead unit of Russia's fourth generation ballistic missile submarine would havereached initial operational capability by 2004, if the current plan of launching it by 2002remained on track. But the Navy leadership's plans to launch one new-generationsubmarine per year beginning in 2002 appear unrealistic with the planned financing of

national defense. Consequently no more than 9-12 missile-armed submarines with a totalof 800-1,000 warheads are likely to remain in the naval strategic nuclear forces by 2010,although the START I and II treaties allow Russia to have up to 1,750-1,900 warheads inthe naval component.

As of early 1999 it appeared that construction had ceased on the first unit of the Borei-class, pending a redesign of the ship to accomodate a different missile from the originallyintended SS-N-28, which had failed its first three test firings and was subsequently saidto have been abandoned. The first remains under construction with a scheduled launch in2005. Other sources state the commissioning year to be 2007-2010, depending onavailability of funds.

The creation of D-19UTH missile complex designed for the new nuclear strategicsubmarines of the Borei-class has been undertaken at GRTs KB named after V. P.Makeev. The D-19UTH launch complex is to replace the D-9 launch complex with RSM-52 ballistic missiles. The new complex will be equipped with a solid-fuel ballistic missileof greater reliability and longer range, capable of being fired from the surface and under-water positions.

As of June 2000 the Russian Navy claims that it operates 26 strategic nuclear submarinescarrying 2,272 nuclear warheads on 440 ballistic missiles. This force is said to consist of5 Typhoon class submarines, 7 Delta-IV class submarines, and 13 Delta-III classsubmarines [which only adds up to 25, not 26 submarines]. Not all of these submarinesare presently seaworthy. The oldest of these boats, which entered service in 1983, willreach the end of their 20-25 year service life about the time the first 935 is commissioned.The Russian Navy reportedly believes that 12 strategic nuclear submarines with ballisticmissiles represent the minimum necessary force structure. According to media reports aclassified presidential decree of 04 March 2000 established this force goal for the periodthrough 2010.

SpecificationsBuilders:

Power Plant: nuclear reactor, geared steam turbines, shaft

Length: 170 meters

Beam: meters

Displacement: 11,750-12,250 tons Surfaced16,750-24,000 tons Submerged

Speed: + 25 knots

Crew: Officers, Enlisted

Armament: 20 R-39M Grom RSM-52V SS-N-28

Date Deployed:


# number


Launched

Commisioned

Stricken

Notes

1 ----- YuriDolgoruky

402Sevmash

10/25/1996

2005-2010?

1998redesigned andreconstructed

2402Sevmash

2006-2011? ?

3402Sevmash

2007-2012? ?

4402Sevmash

2008-2013? ?

5402Sevmash

2009-2014? ?

6402Sevmash

2010-2015? ?

7402Sevmash

2011-2016? ?

8402Sevmash

2012-2017? ?

9402Sevmash

2013-2018? ?

10

402Sevmash

2014-2019? ?

11

402Sevmash

2015-2020? ?

12

402Sevmash

2016-2021? ?

Tu-4 BULLThe massive World War One Il'ya Muromets bomber [namded after a legendary Russianfolk hero who destroyed the Tartar Army single handed] was the largest four-enginedaeroplane of its time. Designed by Igor Sikorsky, it able to carry a significant bomb loadand to engage in long distance reconnaissance missions. In 1935 Tupolev built theworld's largest passenger plane, the Maxim Gorky, which was used for propagandaflights. The Soviets began the development of a heavy bomber force prior to 1935, andby 1940 they had the largest force of four engined bombers in the world (the Soviets had10,000 to 12,000 aircraft of all types at the outbreak of World War II). However, strategicbombing played a minor role in Soviet wartime military operations.

During World War II an arrangement of aerial maneuvers code-named FRANTICcomprised the largest and most complete military projects linking the United States ofAmerica and the Union of Soviet Socialist Republics as allies against Germany. This wasthe only direct combat cooperation between the American and Soviet war efforts. TheUnited States Army Air Force conducted FRANTIC as an extension of the CombinedBomber Offensive (CBO) in Europe. The 8th and 15th Air Forces flew B-17 FlyingFortresses deep into central Europe to attack German war materiel and military bases,then continued east to land in the Ukraine. Soviet troops serviced and protected the ArmyAir Force units, which rearmed and flew of to hit more targets enroute to their homestations.

Work on a long range bomber, capable of striking at targets in deep enemy territory,began in the Soviet Union in 1943. Three American B-29 bombers flying against Japanhad landed in Siberia and were seized by the Soviets. By August 1944 the the "64" designhad been developed at OKB-156 under the direction of A.N. Tupolev, with similarcharacteristics. The maximum range of the Soviet bomber carrying a load of 4,000 kgwas planned to be 6,500 km. However, in June 1945, after development began, the SovietUnion decided to drop the project "64" and build an exact copy of the B-29 bomberinstead.

This Soviet copy of the B-29 was also built by OKB-156, under the designation B-4 orproduct "P". The project received the highest priority and was under direct control of thePolitbureau, and was supposed to be completed within two years.

In mid 1945 the three American B-29 bombers were delivered to Moscow. One planewas transferred to the Flight-test institute in Zhukovski to train pilots for preparing flighttraining manuals, the second plane was disassambled to study its' design and the thirdwas left as a yardstick. However, the Soviets decided not to attempto to copy theAmerican engine, and instead equipped the bomber with the Soviet ASH-73TK enginedesigned by A.D. Shvetsov. This engine retained the B-29's original turbocompressor andthe magnet and heat-resistant bearings. The Soviet bomber also carried improved gunturrets of Soviet design.

The Bull is a midwing, four-engine, medium bomber with two bomb bays centrallylocated in the fuselage, extending fore and aft of the wing. Defensive armament consistsof four turrets located in upper forward, lower forward, lower rear, and tail positions.

The first B-4 bomber was finished in the spring of 1947 and carried out its' first flight on19 May 1947. Flight tests continued through 1949. Full-scale production of the aircraft,under the designation Tu-4. began in 1947 at the plant Nr. 22 in Kazan and at plant Nr.18 in Kuibyshev. In 1948, an additional construction plant in Moscow, Nr. 23, wasadapted to build the TU-4. Production in Moscow began in 1950 and when totalproduction of the TU-4 finally finished in 1952, a total of 847 bombers had beenproduced [according to Russian sources -- according to Western estimates, a maximum ofabout 1,300 were deployed by 1954].

The deployment of the TU-4 bomber began in 1949, and they replaced wartime bomberssuch as the IL-4, B-25, PYE-8, B-17 and B-24 aircraft in Long-Range Aviation units.Patrolling mainly over Soviet territory, the bombers had a capability to strike at Europe,Northern Africa, the Near East and Japan.

Immediately after serial production of the Tu-4 was initiated, work began to adapt thebomber to strike at American territory. Some airplanes were outfitted to carry nuclearbombs and were designated as TU-4A. During re-equipment, the bomber was equippedwith a thermostatically controlled heated bomb bay, a suspension unit for the bomb wasdeveloped, and biological protection devices for the crew were supplied. Some TU-4bombers were equipped with aerial refueling devices, and very few were outfitted withadditional fuel tanks located under the wings. They were deployed in 1952, though themajority of the TU-4 were not re-equipped with air refueling. Although the limited rangeof the Tu-4 rendered it incapable of striking the United States and subsequently returningto bases in the Soviet Union, neither country was a stranger to one-way strategicbombardment missions, given the precedent of the FRANTIC operations in World WarII.

In 1948, work on the "Comet" missile project began. The modified version of the Tu-4bomber - the TU-4K - was supposed to be equipped with two KS-1 air to surface missilesand the "Comet-1"/"Comet-2" guidance system. The first TU-4K prototype was finishedin 1951, with production testing in 1951 and 1952. Between July 1952 and January 1953the bomber was tested, and subsequently deployed with naval aviation. In 1950 OKBTupolev studied the possibility of equipping the TU-4 with the turbo-prop engines of theTB-2 aircraft. But the flight performance was only increased by 14-20 percent, and theproject did not proceed into development. The "Burlak" weapon system was developed inthe early 1950s to protect the bomber from attacks. The TU-4 bomber towed a pair ofMIG-15 fighters as an escort. However, after proving that this was technically feasible,the project was cancelled. Some TU-4 were converted into secret command centers andthough designed primarily as a bomber, the Tu-4 could also be equipped forreconnaissance missions.

From 1954 on, the bombers Tu-4 were gradually replaced by Tu-16 medium-rangebombers, and from 1956 on by Tu-95 intercontinental bombers. Although the Sovietshave phased it out as an operational bomber, it was used for this purpose for some yearsthereafter in the Chinese Air Force. From the early 1960s on, the TU-4 were only used astransport aircraft, training aircraft and flying airforce laboratories.

In 1955 some 300 TU-4 aircraft were converted to the transport aircraft TU-4Dconfiguration, which remained in operational service through the mid-1960s. Thismodification was adapted to transportation and airdrop 28 parachute air-troopers withtheir equipment. Despite this, the aircraft bomber retained its long-range bombingcapabilities. In 1956, the TU-4 was experimentally converted into a troop carryingaircraft (TU-4T). The TU-4 served as the basis for the passenger plane TU-70 and themilitary transport aircraft TU-75. In the early 1960s, a total of six Tu-4 were convertedinto flying laboratories (TU-4LL) to support testing of piston, turbo-prop and turbojetengines. In the late 1950s some aircraft were converted to the TU-4USHS trainer.

SpecificationsSoviet Designation TU-4

US-Designation Bull

Design Bureau OKB-156 Tupolev

Manufacturer Plant Nr. 22 KazanPlant Nr. 18 KuibyshevPlant Nr. 23 Moscow

Power Plant 4 ASH-73TK engines

Thrust 1790 kw each

Length 30.179

Height 8.46

Wingspan 43m

Wing surface 161.7sqm

Speed 558 km/h (at 10250m)435 km/h (ground)

Ceiling 11.200m

Weight (empty) 35.270kg

Fuel weight 4.280kg

Maximum take-off weight 65.000kg

Normal load 6.000kg

Maximum load 9.000

Operational Range 5.400km (with a load of 3.000kg)3.580 km (with a load of 9.000kg)

Maximum Range 6.200km (with a load of 3.000kg)

Armament Six 1000-Kt bombs (TU-4)1 nuclear bomb (TU-4a)2 KS missiles (TU-4K)

Systems

Crew 7

Accomodation

Unit cost


First Flight 5/19/1947

Series production 1945-1952

Date deployed 1949

Inventory


Soviets possess partial sets of B-29 blueprints (according topost-war defector) 1943

B-29 lands at Vladivostok in flying condition and is interned July 1944

USSR acquires two more wartime B-29s November1944

Estimated start of flight testing 1945

First discovery 1946

Estimated start of series production 1947

Initial operational capability 1949

Significant operational capability 1950

Production complete 1953

Phase out complete 1960

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Il-28 BEAGLE (ILYUSHIN)The first jet bomber to enter service with the Soviet air force, the Il-28 tactical daybomber was Russia's equivalent to the British Canberra. First flown on the 08 August1948, the Il-28 entered service with bomber squadrons in 1950 and remained inproduction for many years. This jet-powered medium bomber was built in enormousnumbers [over 6000 were built by the Soviet Union and China, according to someestimates] and adapted to fulfil a variety of roles.

Designed in the late 1940s with an orthodox configuration, the Il-28 was powered byRolls-Royce turbojets supplied by Britian just before the Cold War started. Two KlimovVK-1 centrifugal-flow turbojets (developed from the Rolls-Royce Nene) were mountedbeneath the wings in pods, which extend beyond wings’ leading and trailing edges. Thehigh-mounted wings featured a straight leading edge and forward-tapered trailing edgewith blunt tips. The unswept wing contrasts with the swept tailplane but ensures pitchcontrol in high Mach dives. The tubular fuselage was cigar-shaped, and tapering to therear, with a rounded, glassed-in nose and bubble canopy. The WWII-style greenhousecontains the bombardier/ navigator's electronics and visual bombsight. The tail fin isswept-back and tapered with a blunt tip. The tail of the Beagle contains the reargunner/radio operator and two more 23mm NR-23 cannon. Flats are low-mounted on thefin, swept-back, and tapered with blunt tips. A glassed-in tail gunner compartment is tothe rear of the tail.

It is armed with two 23 mm NR-23 cannon in a fixed nose installation and two 23 mmNR-23 cannon in the tail turret. Up to 3000 kg of disposable stores can be carried in alowerfuselage weapons bay. The Il-28R variant is a three-seat tactical reconnaissanceversion with four or five cameras. This model was also used for electronic intelligencegathering with a revised electronic fit. The Il-28U variant is an operational conversiontrainer lacking radar and armament but fitted with a second cockpit in the nose.

The Il-28 was retired from the Soviet Air Force and Navy in the 1980s, serving as targettugs and ECM platforms. It also served with a large number of export customers, and wasexported to over 20 countries]. Beagles served with most of the major Arab air forces.The arrival of 50 Il-28s in Egypt in 1956 was alarming to the Israelis, and a significantfactor in the origins of the 1956 Suez War, in which all the Il-28s sent to Nasser weredestroyed on the ground. Again in 1967 and yet again in 1973, the Il-28 featured as asignificant ground target for the Israeli Air Force. During the Cuban Missile Crisis of1962, Soviet Premier Khrushchev agreed to remove the offensive missiles as well as themedium range twin-jet Il-28 "Beagle" bombers being assembled in Cuba. Il-28s also sawservice with the Nigerians during the Biafra War. East Germany and Finland flew onlythe target-towing version, without armament. By the early 1990s more than 300 Beaglesremained in service with a number of ex-Soviet allies and clients.

SpecificationsPrimary Function: Light bomber

Similar Aircraft Canberra, Yak-28 Brewer

Contractor: ILYUSHIN

Power Plant: two Klimov VK-1A

Thrust: 26.48 kN (5,952 lb st) each

Length: 57 ft, 11 in (17.6 m)

Height: 6.70 m

Wingspan: 70 ft, 5 in (21.5 m)

Speed:902 km/h at 4500 m [maximum]800 km/h at sea level876 km/h cruising speed at optimum altitude

Ceiling: 12300 m

Weight: empty 11890 kg

Maximum TakeoffWeight: 21200 kg

Range: 2400 km at 10000 m1135 km at 1000 m

Armament: Bombs, two 23-mm cannons in tail

Crew: Three

Unit Cost:

Date Deployed:

Current Users: Romania and People’s Republic of China (H-5)

Former Users: Afghanistan, Egypt, Hungary, Iraq, North Korea,Poland and Yemen

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Tu-16 BADGER (TUPOLEV)The Tu-16 was designed as an high-speed jet bomber for operations in theaters close tothe Soviet Union. Intended to replace the propeller-driven TU-4, the greatest challengeduring development was to doubling the speed to improve survivability in the face ofenemy fighters.

OKB A.N. Tupolev started working on the design of a new jet bomber soon afterdevelopment of the TU-4 was completed. The resulting design "82" consisted of a swept-wing aircraft with RD-45F or VK-1 turbojet engines. The bomber was supposed to have aspeed of Mach 0.9-0.95 with a range and payload were comparable to the TU-4.

After the bomber's operational characteristics were coordinated with the military, thegovernment officially approved the development of the "82" aircraft in 1948. Theprototype, which was the first Soviet aircraft with swept-wings, made its' first flight on24 March1949. It reached a speed of 934 km/h, 20 percent faster than the TU-14 whichalso had BK-1 engines. The "82" design was initially supposed to serve as the basis forthe "83" bomber, but with the start of serial production of the Il-28, the project wasdropped.

Based on the results of the "82" aircraft, in 1950 OKB Tupolev started developing the"492" heavy long-range bomber that had a better performance than the TU-4 and the Il-28. The design provided for a bomb load of 6000 kg, a range of 7,500 km, a speed of1000 km/h and a ceiling of 12000-13000 m. The maximum bomb load could be increasedup to 12000kg. The aircraft could be outfitted with three different types of engines: twoAM-3 engines with a thrust of 8750 kg, 4 engines ТR-3A engines (5000 kg) or 4 TR-5two circuit engines (5000 kg). As the TR-5 engines were the most reliable at that time,Tupolev was charged with the development of an experimental long-range bomber(project "88") equipped with two TR-5 engines. However, work on the AM-3 enginescontinued and was completed in August 1951.

The wings of the Badger are mid-mounted, swept-back, and tapered with blunt tips.There are fences on top of the wings and its landing gear pods extend beyond the wings’trailing edges. The Badger's engine(s) are two turbojets mounted in wing roots whichextend beyond the leading and trailing edges of the wing root. The engines also haveround air intakes. Its fuselage is long, slender, and bulging where the engines aremounted and tapered to the tail. It has a round, glassed-in nose and a stepped cockpit. Thetail is swept-back, tapered fin and flats with blunt tips. The Badger also has a tail gunnercompartment. All models of Badger are equipped for aerial refueling.

The first prototype of the "88" aircraft received the designation Tu-16 and carried out thefirst flight on 27 April 1952. During flight tests, the aircraft exceeded the expected speedbut lagged in range due to insufficient engine performance. As a result, the secondprototype had a reduced weight though less speed at small and medium altitudes. In April1953 it actually exceeded the expected range.

In December 1952, series production was initiated. In 1953 series production of the TU-16 began at the plant Nr. 22 in Kazan and in 1954, also at the plant Nr.1 in Kuibyshevand at the plant Nr. 64 in Voronezh. During production, the aircraft were outfitted with amodified AM-3 engine - the PD-3MT. While the bombers were already operational, theAM-3 and PD-3M engines were replaced by PD-3M-500 engines with improvedcharacteristics. When production of the TU-16 finally stopped in 1963, a total of 1509aircraft had been built.

Deployment of the first TU-16 bombers started in 1954. They replaced the TU-4,operating in theaters close to Soviet territory.

Badger-A - Tu-16 -- The initial production version was lighter than the firstprototype, and largely met the original performance requirement.

Badger-A - Tu-16A -- Primarily employed as a medium bomber, the TU-16Acarried nuclear bombs - the A suffix stood for Atomic. It had a re-configurablethermostatically controlled heated bomb bay compatible with nuclear weapons,and a special skin for protection against nuclear thermal effects. Externally similarto the basic Tu-16, it featured more powerful RD-3M-200 engines, and animproved self-defense gun fire control system. This was the primary productionversion, with over 700 built, many of which were subsequently converted to otherversions.

Badger-A - Tu-16E -- To increase range, the TU-16 subsequently received an airrefueling system. Some TU-16 were converted into tanker aircraft, which werefirst tested in 1955 and received the designation TU-16E [some Western sourcessuggest the designation was Tu-16Z]. However, they could still be used asbombers. This initial inflight refuelling tanker version used a novel "wingtip-to-wingtip" method, with a hose trailed from the right wingtip and snagged bygrapnel trailed by receiver, then winched into fitting in receiver's port wingtip. Italso had provision for additional transfer fuel in removeable tanks in bomb bay.

Badger-A - Tu-16M -- The Tu-16M AV-MF maritime strike version was similarto the Tu-16A with a few minor differences.

Badger-A - Tu-16N -- A secondary mission for Badger A is as a tanker. From1963 on the TU-16 was converted into TU-16N tanker aircraft. This tankerversion featured a 'Probe and drogue' system with a Yakovlev-built centerlinefueling unit in the bomb bay and ARK-5 beacon. It was mainly used to supportprobe-equipped Tu-22 and Tu-22M Blinder bomber regiments.

Badger-A - Tu-16T -- In the middle of the 1950s series production of the TU-16T started. It was equipped with an air-to-surface missile for anti-shippingpurposes, with provision for mines, depth charges or for four RAT-52 or TAN-53torpedos. This torpedo bomber version was built in limited numbers, and after1965 all TU-16T aircraft were converted into the TU-16S.

Badger-A - Tu-16S -- The Tu-16S search and rescue model, a 1965 conversionof all the TU-16T aircraft, featured additional fuel and extra radios and carried aradio-controlled lifeboat in the bomb compartment.

Badger-A - Tu-16Ye -- In the middle of the 1950s, the TU-16N and the TY-16Ye were created for electronic warfare. The Yolka ECM system featured a row

of three steerable antennas under the bomb bay and a bulk chaff-cutter/dispenser.This aircraft is designated Badger-K when fitted with two radomes rather thanthree. A few Tu-16As were rebuilt as Elint/EW platforms, though most Tu-16Yewere produced by conversion of redundant Tu-16K-10 missile Badger-D carriers.

Badger-B - Tu-16KS -- The Badger B is equipped with two Kennel air-to-surfacemissiles suspended beneath the wings. The TU-16KS began initial tests in August1954. It carried two KS-1 Kometa air-to-surface missiles with a range of 90 km,and had an operational range of 1800 km. The Kobalt-N guidance transmitter wasinstalled, though the glazed 'bomber' nose was retained. The aircraft subsequentlyserved in the Soviet Naval Air Force [AV-MF].

Badger-C - Tu-16K-10 -- In 1955 work began on using the Tu-16 as the carrierfor the K-10S (AS-2 Kipper) cruise missile for the Soviet Naval Air Force for usein an anti-shipping role. The missile's guidance system was added as an onboardsystem, with the missile mounted semi-submerged under the fuselage on thecenterline in the bomb bay area. The glazed nose was replaced by broad flatradome housing antenna for the YeN targeting radar. A missile top-off fuel tankwas housed in the bomb bay, along with a small pressure cabin for the YeN radaroperator. The TU-16K-10 prototype was finished in 1958 and series productionstarted in 1959. Deployment into the Soviet Naval Air Force began in October1961. A total of about 220 were built, many of which were subsequentlyconverted to Elint/EW platforms.

Badger-C (Mod) - Tu-16K-10-26 -- Small numbers of Tu-16K-10s were latermodified to carry KSR-2, KSR-5S and later K-26 missiles underwing.

Badger-D - Tu-16Ye -- Badger D is a modified Badger C reequipped to performan ELINT reconnaissance mission. This EW conversion of Tu-16K-10 and K-10-26 is generally similar to Tu-16A and Tu-16KS-based EW conversions (Tu-16Ye'Badger-A' and 'Badger-B'), though retaining the distinctive broad flat noseradome.

Badger-E - Tu-16R -- The TU-16R reconnaissance aircraft represented anothermodification of the TU-16 Badger which was tested from 1955 on. The Badger Eis a modified Badger A reequipped to perform photographic reconnaissance, witha camera pack in former bomb bay and the pilot's forward firing gun usuallyremoved.

Badger-E - Tu-16RM -- The Tu-16RM is a similar maritime reconnaissanceversion for the Soviet Naval Air Force [AV-MF].

Badger-E - Tu-16KRM -- Small numbers of Tu-16RMs were modified withunderwing launch rails for rocket-powered target drones.

Badger-F - Tu-16RM-2 -- Badger F is a photographic reconnaissance variant ofthe Badger E Tu-16Rs and RMs with the addition of ELINT pods beneath thewings or fuselage.

Badger-G - Tu-16K-11-16 -- The Badger G has the concurrent capability ofcarrying two Kelt AS-5 (125 nm) or two AS-6 (300 nm) air-to-surface missilessuspended beneath the wings and dropping bombs from an internal bomb bay.The new missile system K-11-16 with KSR-2 (AS-5B) and KSR-11 (AS-5B)missiles and the "Rubin-1" radar system was developed in 1962 based on amodification of equipment of the MIG-15. The Badger G/Kelt weapon system

was developed as a stand-off weapon for the LRA and for an anti-shipping rolefor the SNAF. It probably has an anti-radiation role also. The AS-6 would havesimilar roles. It is equipped for aerial refueling. A number of Tu-16As and Tu-16KSs were re-fitted with Rubin radar undernose and with provision for K-11 orK-16 missiles. The TU-16K-11-16 aircraft that were converted from TU-16, TU-16A and TU-16KS aircraft could carry either two KSR-2 or KSR-11 missilebeneath the wings. They served in the Soviet Naval Air Force.

Badger-G (Mod) Tu-16K-26 -- Development of the K-26 missile system startedin 1962, using the KSR-5 (AS-6) air-to-surface anti-ship missiles. They weredeployed on TU-16K-26 aircraft that entered service in the second half of the1960s. The Tu-16K-26 aircraft was modified to launch K-26 missiles, with launchattitude indicator on the nose glazing. The characteristics of the K-11-16 and K-26 weapon systems allowed the aircraft to retain their original bombercapabilities.

Badger-G (Mod) Tu-16K-10-26 -- During development of the TU-16K-26, theK-10 weapon system was upgraded and replaced by the K-10S system that hadtwo KRS-5 or KSR-2 missiles. The retrofitted aircraft received the designationTU-16K-10-26. After the K-10S system missiles were phased out, these aircraftcarried only KSR-5 missiles.

Badger-H - Tu-16PP or Tu-16P Elka -- The Badger H is believed to be an ECMsupport aircraft with a primary mission of sowing chaff corridors to protectfollow-on weapons-carrying aircraft. It also has a limited capability to provideactive ECM against search and acquisition radars. This stand-off jammer versionwas produced by conversion of Tu-16A or Tu-16KS, with underfuselage radomesat each end of the bomb bay, and with a new bulk chaff-cutter/dispenser servingthree chutes in the former bomb bay doors.

Badger-J - Tu-16P Buket -- The Badger J active jamming platform is estimatedto carry a multichannel click jammer to perform both stand-off and escort-activeECM. It features a ventral canoe fairing and flat plate antennas forming wingtipextensions.

Badger-K - Tu-16Ye -- Badger K probably supplements Badger F and isprobably an automatic system designed for precision ELINT collection in a densesignal environment. This EW conversion of Tu-16KS is generally similar to Tu-16Ye Badger-B, though with two rather than three underfuselage radomesmounted on the area of the former bomb bay [rather than at each end as onBadger-F].

Badger-L - Tu-16P and Tu-16PP -- The Badger-L is an advanced ELINTplatform with a self-protection active jammer and an associated thimble noseradome, along with a distinctive extended ECM tailcone.

The TU-16 remained in Soviet and later Russian service until 1993. They were usedduring the war in Afghanistan. The Badger is used by Egypt, Iraq, the People’s Republicof China (H-6), and Ukraine. In 1958, delivery of TU-16 bombers to China began, whereseries production received the designation H-6. In the summer of 1961, twenty TU-16KSwere sold to Indonesia. In the 1960s, TU-16 bombers were delivered to Egypt which also

received TU-16KS aircraft in 1967 and Tu-16K-11-16 in 1973. Iraq also received TU-16K-11-16 bombers in the 1960s.

SpecificationsDesign Bureau OKB-156 Tupolev

Manufacturer Plant Nr.22 KazanPlant Nr. 1 KuinyshevsPlant Nr. 64 Voronezh

Power Plant 2 AM-3A Turbojet engines2 PD-3M Turbojet engines2 PD-3M-500 Turbojet engines

Thrust 8,750 kg each9,500 kg each9,500 kg each

Length 34.8

Height 10.36

Wingspan 33m

Wing surface 164.65 sqm

Speed TU-16 - 900-950km/h (cruise) /1050km/h (maximum)TU-16K - 750-850km/h

Ceiling 12,800m

Weight (empty) 37,200kg

Fuel weight 36,000kg

Maximum take-off weight 79,000kg

Normal load 3,000kg

Maximum load 9,000kg

Operational Range 5,800km (with a load of 3.000kg)4,850km (with 2 missiles underneath thewings)

Range 7,200 km

AircraftModel

OperationalWt.Empty

FuelCapacity(gal)

UnrefueledCombatRadius

Payload(lb)

AltitudeOverTarget

SpeedCruise/Combat

Remarks

(lbs) (ft) (kn)

BadgerA 83,500 11,200 1,450 10-30,000 40,400 445/500 bomber

BadgerB 90,300 9,300 1,000 12,000 15,000 445/480 Kennel ASM

BadgerC 86,600 10,300 1,350 9,100 39,400 445/480 Kipper ASM

BadgerD 88,840 11,370 n.a. n.a. n.a. n.a. ELINT Recce

BadgerE 85,000 11,570 n.a. n.a. n.a. n.a. Photo Recce

BadgerF 87,000 11,570 n.a. n.a. n.a. n.a. Photo/ELINT

BadgerG 86,000 9,460 1,100 17,620 38,100 445/495 ASM

BadgerH 83,500 11,200 n.a. n.a. n.a. n.a. ECM/Chaff

BadgerJ 83,500 11,200 n.a. n.a. n.a. n.a. ECM/Jammer

BadgerK 83,500 11,200 n.a. n.a. n.a. n.a. ELINT



First discovery

Badger A 1953

Badger B July 1961

Badger C July 1961

Badger D September 1964

Badger E January 1963

Badger F 1959

Badger G July 14, 1966

Badger H March 1965

Badger J March 1965

Badger K September 1968


Public display in significant numbers May 1, 1954



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Tu-95 BEAR (TUPOLEV)The Tu-95 BEAR was perhaps the most successful bomber produced by the Sovietaviation, enjoying long service in a variety of roles and configurations. It was the onlybomber deployed by any country to use turbo-prop engines, which providedextraordinarily long endurance at speeds only slightly less than comparable turbojet-powered heavy bombers.

Development of the TU-95 intercontinental bomber began in the early 1950s after seriesproduction of the medium-range TU-4 started.. Initially, several designs were considered,including a modification of the TU-4 and production of a new aircraft with pistonengines. Prototypes of these aircraft were developed and tested from 1949 through 1951,it was concluded that bombers with piston engines could not provide adequateperformance for the intercontinental attack mission. In March 1951 development of theT-4 intercontinental jet bomber began. However, KB Tupolev did not support thedevelopment of a bomber with turbojet engines, believing that the proposed AM-3 jetengines would not provide for the required range of more than 10,000 km. As analternative, KB Tupolev proposed an aircraft with four turbo-prop engines that wouldprovide a range of more than 13,000 km and speeds of more than 800 km/h at altitudes of10,000 meters. The aircraft-design was designated as "95".

The design of the wings drew heavily on the experience gathered by Tupolev and theCentral Aerohydrodynamic Institute (TSAGI) during the development of the swept wingTU-16. The wings of the "95" were swept back at an angle of 35 degrees, allowing theplacement of a large bomb bay behind of the torsion box of the wings' central unit at theaircraft's center of gravity.

The Bear's wings are mid-mounted, swept-back, and tapered with blunt tips. Its enginesconsist of four turboprops with contrarotating propellers located on the wings. The enginenacelles extend well beyond the wings’ leading edges. The fuselage of the Bear is tube-shaped with a rounded nose that tapers to the rear. It also has a stepped cockpit and a tailgun compartment. The tail of the aircraft is a fin that is swept-back and tapered with asquare tip.

The greatest difficulties during the development were the engines. After studies ondifferent engine combinations and versions, the final design of the aircraft incorporatedfour turbo-prop engines with a thrust of about 10,000-shp. In the late 1940s, the mostpowerful turbo-prop engine available was the BK-2 prototype which had significantlyless thrust (4800-shp). In the early 1950s OKB-276 N.A. Kuznetsov developed the TV-2engine and the TV-2F booster engine with a thrust of 6,250-shp. while work on the TV-12 engine with sufficient thrust for the "95" aircraft continued.

After consideration of Tupolev's proposals, on 11 July 1951 the government officiallyapproved the development of the "95" aircraft: Two versions were built, one with eightTV-2F engines coupled through the reduction gearbox in four pusher-tractor tandem

pairs, and a second version with four TV-12 engines. N.I. Bazenkov became the chiefdesigner of all subsequent TU-95 versions. When he died in 1975, N.V. Kursanov tookover as chief designer, and from the end of the 1980s, D.A. Antonov became head of theprogram.

In 1952, the first prototype "95/1", equipped with 8 2TV-2F engines, was built at PlantNr. 156. The reduction gearbox and the four-blade contra-rotating propellers weredeveloped by OKB-120 headed by K.N. Zhdanov. Each pair generated a thrust of 12,000-shp. The first flight of the "95/1" airplane took place on 12 November 1952, but on 11May 1953 during its' 17th flight the plane crashed and burned due to an engine fire. Thesecond prototype ("95/2"), equipped with TV-12 engines, was completed in June 1954with a first flight on 16 February 1955. During tests, while carrying a load of 5000 kg, itreached a range of about 15,000 km, a speed of 993 km/h and a ceiling of 11,300 m.Series production of the aircraft -- now designated as TU-95 -- started in January 1956 atPlant Nr. 18 in Kuibyshev, while production tests were still underway.

VARIANTSWith the exception of Bear A, all models are equipped with a nose probe for aerialrefueling.

BEAR A - TU-95 / TU-95M -- The Bear A is a long-range strategic bomber thatis capable of high-altitude precision bombing. The TU-95 and TU-95M bomberswere designed to carry 9,000 kg of bombs at their maximum design range, whichcould be further increased by reducing the aircraft's range. They carried six radar-controlled turret-mounted AM-23 guns for self-defense. The first two fullyequipped Tu-95 aircraft left the plant in August 1955 and began flight tests inOctober 1955. Carrying a load of 5,000 kg, it reached a maximum speed of 850km/h and a service ceiling of 10,200 m with a maximum range of 12,100 km. Thebomb bay was 14.2 m (46.6 ft) long. The subsequent aircraft, designated as TU-95M, had more powerful and more fuel-efficient NK-12M engines that allowedincreased take-off weight. During tests in September and October 1957, it reacheda maximum speed of 905 km/h, a ceiling of 12,150 m and a range of 13,200 km.Despite falling short of range and speed requirements, deployment started inOctober 1957. During work on these aircraft, development of a bomber withimproved abilities to counter air defenses continued. In 1952 the governmentordered a high-altitude strategic bomber with a ceiling of 17,000 m. A prototypeequipped with NK-12M engines was used in tests, but development was haltedbecause the increased altitude did not increase the survivability of the bomber.Most 'Bear-As' were subsequently converted to the missile-carrying Bear-Bconfiguration. About a dozen surviving 'Bear-As' were converted to Tu-95Uconfiguration for training duties

BEAR - TU-95V -- The Tu-95V, built in 1956, was intended to carry largehydrogen bombs. As these bombs were not made operational in the end of the1950s, this aircraft was used for training purposes. Nevertheless, in 1961,overhaul of a TU-95V aircraft took place at the plant Nr. 18 in Kuibyshev. Theaircraft carried the hydrogen bomb that was tested on 31 October 1961, which

weighed about 27,500 kg and had a yield of 58 megatons. This version of theBEAR A was apparently not recognized as a distinct variant by Westernintelligence, and did not receive a separate designation.

BEAR - TU-95N -- In 1958 a single aircraft was converted into the TU-95N usedto carry the "PS" attack aircraft "RS" developed by OKB-256 P.V. Tsibina, butthis line of development proved unpromising and was soon discontinued. The factof the existence of this project was apparently not detected at the time by Westernintelligence, and this variant did not receive a separate designation in the West.

BEAR B - TU-95K / TU-95KD -- The Bear B carried one Kangaroo (350 nmrange) air-to-surface missile partially recessed within the aircraft fuselage. Themost visible change from the BEAR A TU-95M is the addition of the broad, flat-bottomed radome under the nose, which housed a 3.3-meter wide low I-band A-336Z Crown Drum scanning antenna for the missile guidance radar. Developmentof the TU-25K-20 weapon system, consisting of the TU-95K and the supersonicKk-20 (AS-3) air-to-surface missile, began in March 1955. The "K-20"nomenclature appears to encompass both the aircraft and the missile, and the "Tu-95K-20" nomenclature used by some sources may be in error]. With a range of350 km, sufficient to overcome air defenses, the air-to-surface missile was locatedunder the fuselage. The first flight of the prototype was on 01 January 1956, andthrough development continued on the missile launch and guidance system, theaircraft's airframe, and the onboard electronics. Series production of the TU-95Kbegan in the spring of 1958, with operational deployment beginning in September1959. The additional fuel tanks and the missile of the Tu-95K resulted in anincrease of weight and drag that reduced the range of the aircraft. Thisperformance deficit had to be offset by a aerial refueling. Work on this "hose-cone" system started in May 1960 and was completed in 1961. The bombers thatwere outfitted with this air refueling system received the designation Tu-95KD.Some 'Bear-Bs' were relegated to training duties.

BEAR C - TU-95KM -- In the 1960s several TU-95K and TU-95KD bombersreceived a new radio engineering and navigation system, and their designationchanged to TU-95KM [some Western sources claim that the Tu-95KM Bear-Cwas a new-build aircraft, rather than a conversion]. The Bear C is similar inappearance to the late-series Bear B Tu-95KDs, with the addition of two pairs ofreconnaissance radomes located on opposite sides of the aft section of thefuselage. Many Tu-95KMs were upgraded to the 'Bear-G' configuration and noneare believed to remain operational in the original configuration.

BEAR D - TU-95RTs -- The Bear D is a variant of Bear A which can alsoperform ELINT reconnaissance. The TU-95RTS maritime reconnaissance aircraftwas developed in the early 1960s, and conducted its' first flight test in September1962, with series production beginning in 1963 [some Western sources suggestthat the aircraft were converted from surplus Tu-95M 'Bear-As]. The TU-95RTSbegan flying with naval aviation in 1964 and was introduced into the operationalinventory by spring of 1966. The Bear-D was first identified by Westernintelligence in 1967. The new variant was distinguished by a new enlarged chinradome, and a much larger Big Bulge I-band search radar in place of the formerweapons bay. This search radar provided mid-course missile guidance, acquiring

targets for ship-, submarine- and air-launched missiles. The Tu-95RTs, althoughbuilt on the airframe of a heavy bomber, was designed and built as a maritimepatrol airplane. The TU-95RTs maritime patrol airplanes have not been and arenot heavy bombers, nor have they been equipped with air-to-surface weapons orundergone conversion. Tu-95RTs airplanes have external features distinguishingthem from heavy bombers of the Tu-95 type: they have no bomb bays, no externalcarrier beams to suspend or carry aerial bombs or missiles, and no equipmentnecessary for control of such weapons. Other differences characteristic of theseairplanes are the additional three-dimensional radomes of the surface situationsurveillance equipment under the fuselage and on the sides of the airplane. As ofmid-1991 the Soviet Union had 37 Tu-95RTs airplanes, which were based only atnaval air bases. Under the START I Treaty, all Tu-95 variants should be eitherdeployed heavy bombers, non-nuclear heavy bombers, test heavy bombers,training heavy bombers, or former heavy bombers. The START II TwelfthAgreed Statement, however, exempts the 37 existing TU-95RTs (Bear D)maritime patrol airplanes from being considered as former heavy bombers. Theproposal complements and amplifies that Agreed Statement by providinginformation on the Tu-95RTs, as well as the opportunity to verify thatinformation. The 31 July 1991 exchange of letters between Ambassadors Brooksand Nazarkin stipulated that the airplanes are for maritime operations, are notheavy bombers, and have not been equipped with air-to-surface weapons orundergone conversion; it also lists distinguishing features for these airplanes andstipulates that the Soviet Union has 37 such airplanes. The 37 airplanes were notto be based at air bases for heavy bombers or former heavy bombers, heavybomber flight test centers, or training facilities for heavy bombers. They wouldnot be considered to be former heavy bombers and thus would not be"accountable" under the Treaty limits for heavy bombers equipped for non-nuclear armaments, training heavy bombers, and former heavy bombers. In theevent the Soviet Union continued to produce such airplanes, all such newairplanes would be treated as former heavy bombers under the Treaty and subjectto inspection to confirm that they are not equipped for air-to-surface weapons.The Parties agreed that not later than 240 days after signature of the Treaty, theSoviet Union is (i) to provide photographs to aid in the identification of suchairplanes, (ii) conduct an exhibition of one such airplane, under specifiedconditions, and (iii) exhibit, upon request of the United States, the other 36 suchairplanes under specified conditions. About 15 were believed to remain in servicewith the AV-MF in 1994.

BEAR E - TU-95U -- The Bear E is a variant of Bear A modified to performphotoreconnaissance. According to Western sources about 12 were produced forNaval Aviation by conversion of surplous Tu-95Ms. The aircraft features aslightly bulged removeable reconnaissance pallet in the former bomb bay, withseven camera windows -- three side-by-side pairs of windows forward with asingle window further aft to starboard. Under the START I agreement, the Partiesagreed that all airplanes formerly known to the United States of America as BearE and now known as Bear T, which are designated by the Union of SovietSocialist Republics as Tu-95U, were to be considered to be training heavy

bombers. Red bands are painted around the rear fuselage for verificationpurposes.

BEAR F - TU-142 / TU-142M -- Bear F exists in two major versions withdiffering numbers of radomes, consisting of at least four distinct variants [up to atleast the Bear-F Mod IV]. The mission of the Bear F is the detection anddestruction of submarines. Development of the Tu-142 maritime reconnaissanceaircraft began in the mid-1960s, soon after the initiation of the BEAR D Tu-95RTS. Design changes include a new cockpit and slightly longer nose' alongwith a new undercarriage (with bulged undercarriage doors) and an extended-chord rudder. The Tu-142 lacks dorsal and ventral gun turrets. This upgradedversion of the TU-95RTS, with more powerful NK-12MV engines, began flighttests in the summer of 1968 and was deployed with naval aviation in December1972. According to Russian sources, series production took place at the plant Nr.18 in Kuibyshev and from the mid-1970s at Plant Nr. 86 in Taganrog. Westernsources report that the production line at Taganrog reopened in 1983 to build theBear-F and Bear-H. Upgrading of the TU-142 in 1972 resulted in the TU-142M,used for anti-submarine warfare. The first flight of the TU-142M [Bear F Mod 2 ]was on 04 November 1975, and deployment to the Soviet Naval Aviation beganin 1980. The Tu-142M2 [Bear-F Mod 3], which entered service around 1982,featured a new MAD in a spike-like tail fairing and a lengthened sonobuoy bay.The Tu-142M3 [Bear-F Mod 4] incorporated a new undernose sensor pacakge.First identified by Western intelligence in 1986, the Bear-F Mod 4 remained inlow volume production at the end of the 1990s. The Tu-142 (Bear F)antisubmarine warfare patrol airplanes, although designated by the Soviet Unionas a separate type of airplane from the Tu-95, have a design essentially identicalto the design of the Tu-95 heavy bomber. Under the START I agreement, allairplanes designated by the Union of Soviet Socialist Republics as Tu-142, whichare known to the United States of America as Bear F or Bear J, depending on howa particular airplane is equipped, were not considered to be former heavybombers.

BEAR F - TU-142LL -- At least one 'Bear-F' was converted to serve as an enginetestbed , with the test engine mounted in a semi-retractable cradle under thecenter-section.

BEAR - TU-95K5 -- In 1976-1977 work began on developing a new Bearmodification, the TU-95K-5, that was supposed to carry two KSR-5 [AS-6KINGFISH] missiles. However, all activities soon halted due to a decision toproduce the TU-95K-22, and the development of the TU-95MS aircraft. The factof the existence of this design project was not detected at the time by Westernintelligence, and this variant did not receive a separate designation in the West,since it did not enter flight tests or production.

BEAR G - TU-95K22 -- In the early 1970s work began on equipping olderexisting TU-95K and TU-95KD bombers with Kh-22 air-to-surface missiles andthe guidance systems that were used on the Backfire bombers. These older BEARaircraft configured to carry air-to-surface missiles (ASMs) were reconfigured tocarry the new supersonic AS-4 missile in place of the subsonic AS-3. Thesebombers received the designation TU-95K-22 and carried either one Kh-22M

missile under the fuselage or two Kh-22H missiles on pylons underneath thewings. The broad flat nose radome differs in detail from that of the Bear-B andBear-C, and accommodates the antenna for the Down Beat guidance radar for theKh-22. The comprehensive defensive avionics suite is evidenced by the numerousradomes and fairings on the fuselage, marking a fundamental shift in survivabilityideology. The self-defence armament is correspondingly reduced compared toearlier models. An extended tailcone replaced the tail turret and the dorsal turretwas removed entirely, leaving only a single ventral gun turret. First flight tests ofthe TU-95K-22 took place in October 1975 and by the end of the 1970s re-equipment of the TU-95K started. After operation testing, the TU-95K-22 wasintroduced into the active inventory in 1982. Several of these reconfigurations(BEAR G) had been completed by 1985. By 1998 more than 45 of thesereconfigured aircraft were operational.

BEAR - TU-95M-55 -- In the middle of the 1970s work on the Kh-55 long rangair-to-surface missile started. Originally planned for deployment on the new TU-160 supersonic bombers, studies were conducted to outfit the TU-95 with the Kh-55. The tests of TU-95 bombers outfitted with Kh-55 missiles, designated Tu-95M-55, started in 1978. After their completion, the project was rejected anddevelopment of a new Tu-95MS aircraft to carry the Kh-55 missiles was initiated.It is unclear whether the fact of the existence of this design project was detected atthe time by Western intelligence, and in any event this variant did not receive aseparate designation in the West.

BEAR H - TU-95MS -- The Tu-95MS aircraft is based on the Tu-142 and thusdiffers in a number of details from the TU-95. The nose of the Tu-95MS is similarto that of the Bear-C and Bear-G, but with a deeper, shorter radome, cable ductsrunning back along both sides of the fuselage. It lacks the 178-cm forwardfuselage plug of the maritime Tu-142, and retains the shorter fin and horizontal,undrooped refuelling probe of prevoius bomber variants. The rear gun turret is anew design, with a single twin-barrelled GSh-23L cannon in place of the pair ofsingle-barrel NR-23s carried on earlier models. After carrying out successful tests,the first of which was in September 1979, series production started in 1981. Withthe reopening of the BEAR production line, the Soviets began producing a new,upgraded variant of the BEAR turboprop bomber, thereby increasing their long-range bomber force. This entirely new variant of the BEAR bomber - the BEARH - became the launch platform for the long-range Kh-55 [AS-15] air-launchedcruise missile. The initial version carried Kh-55 air-to-surface missiles located inthe bomb bay on a catapult. This was the first new production of a strike versionof the BEAR airframe since the 1960s. With the BEAR H in series production, thedecline in the inventory of BEAR aircraft, characteristic of the late 1970s, wasreversed. By 1988 BEAR H bombers were regularly observed simulating attacksagainst North America.

BEAR H6 - TU-95MS6 -- The version designated as TU-95MS6 aircraft carriedKh-55 air-to-surface missiles located in the bomb bay on a rotary launcher.

BEAR H16 - TU-95MS16 -- The TU-95MS16 carried six missiles inside thefuselage and 10 missiles underneath the wings. Three underwing pylons are fitted

under each inner wing panel, the outboard pair carrying three missiles and theother two single missiles.

BEAR J - TU-142MR -- The TU-142MR was a further modification of the Tu-142M used for submarine communication relay, allowing national commandauthorities and strategic missile-carrying submarines to communicate. Theunderfuselage search radar has been removed, and the aircraft is equipped with anunderfuselage winch pod for a several kilometer long trailing wire antenna. TheTu-142 (Bear J) maritime communications relay airplane, although designated bythe Soviet Union as a separate type of airplane from the Tu-95, has a designessentially identical to the design of the Tu-95 heavy bomber. Under the START Iagreement, all airplanes designated by the Union of Soviet Socialist Republics asTu-142, which are known to the United States of America as Bear F or Bear J,depending on how a particular airplane is equipped, were not considered to beformer heavy bombers.

BEAR T - TU-95U -- About a dozen surviving 'Bear-As' were converted to Tu-95U configuration, with sealed bomb bays and a broad red band painted aroundthe rear fuselage. Under the START I agreement, the Parties agreed that allairplanes formerly known to the United States of America as Bear E and nowknown as Bear T, which are designated by the Union of Soviet SocialistRepublics as Tu-95U, were to be considered to be training heavy bombers. Mostserved with the Long-Range Aviation training center at Ryazan, and most werewithdrawn from use during 1991 and 1992

Russia, Ukraine and India (Bear F) use the Bear.

When the START-1 treaty was signed in 1991, 147 bombers and missile carriers stillserved in the Russian forces: 84 TU-MS and 63 TU-95K-22, TU-95K and TU-95M. Anadditional 11 TU-95U were used for training.

After the dissolution of the Soviet Union, one unit of Bear aircraft remained in Ukraine,with twenty three TU-95MS, one TU-95K and one TU-95M aircraft. These aircraft werepassed to Ukraine, and were subject to decommissioning under the provisions of theSTART-1 treaty. A total of 11 strategic bombers and 600 air-launched missilesexchanged by Ukraine to Russia in payment for the gas debt were transfered in mid-February 2000. Two Tu-160 bombers flew from Priluki in the Ukrainian Chernigovregion for the Russian air base in Engels. The missiles were sent to Russia by railroad.Three Tu-95MS bombers and six Tu-160 airplanes had already arrived at Engels sinceOctober 1999 in fulfilment of the intergovernmental agreements. Before being moved toRussia, 19 Tu-160 airplanes were stationed at the Priluki airfield and 21 Tu-95MS werelocated in Uzin.

At the time of the breakup of the Soviet Union, thirteen TU-95MS-16 and twenty sevenTU- 95MS-6 were based in Kazakhstan. Subsequently, all Bear aircraft located inKazakhstan were transferred to Russia.

Russian Tu-95 and TU-95MS aircraft are now deployed at two air bases A total ofnineteen TU-95MS16 and two TU-MS6, operating in the 121st heavy bomber airregiment, which forms part of the 22nd Air Division that is headquarteed in Engels AirBase in the Moscow region. At the Ukrainka airbase (73th Heavy Bomber Air Division)at Svobodny, there are 16 TU-95MS16 and 26 TU-95MS6 bombers that were redeployedfrom the Dolon airbase at Semipalatinsk in Kazakhstan. The TU-95K-22 bombers aresubject to decommisioning. In early 1997 five TU-95K-22 were decommissioned and re-equipped in Zngyelse, and five at the Ryazan training center. Eight TU-95 are located atthe flight-test institute in at Zhukovskiy [Ramenskoye], and one TU-95K aircraft servesas a static display in Ryazan.

The TU-95MS, constructed in in the middle and early 1990s, will be operational until2010 and 2015. Russia is currently working on a new air-to-surface missile to replace theexisting Kh-55.

In late June 1999 two TU-95 Bear bombers flew within striking distance of the UnitedStates as part of Moscow's largest military exercises since the end of the Cold War. Thebombers were intercepted by four US F-15 fighters and a P-3 patrol plane near Icelandand escorted in a clockwise flight around the island. The Bears, and two Blackjacks, werefrom the Donbass Red Banner 22nd heavy bomber division based at Engels Air Base eastof Moscow. They initially flew acoss the central Norwegian Sea. When they got abouthalfway across, the Blackjacks split off from the Bears and flew along the Norwegiancoastline.

On 16 September 1999 a pair of Russian Tu-95 Bear bombers were detected by the USAir Force headed toward the Alaska coast. U.S. fighter jets were sent to intercept theaircraft which had been caught on radar. Air Force officials said both bombers turnedbefore crossing into US airspace and about 90 miles from the approaching fighters. TheSoviet Union regularly tested U.S. air defenses by flying toward Alaska during the ColdWar, but this was the first time the Air Force had documented it happening since March1993.

Ten Tu-142 entered Indian service in April 1988 for long-range surface surveillance andanti-submarine warfare Negotiations are currently going on with Russia to procure 6 to 8more Tu-142 aircraft. The aircraft will be probably from refurbished ex-VVS storagestocks. India is making substantial purchases of the Novator 3M-54 Alfa missile to equipKilo class submarines and its new frigates. It is believed that an air-launched variant willbe purchased to arm the Tu-142s currently in service and the six to eight additionalaircraft being sought by the Navy. If an air-launched version of the Alfa is procured, it isanticipated that India's Tu-22M3s will eventually be equipped to fire them.

SpecificationsTU-95M TU-95K TU-95KM TU-95RTs TU-95U TU-142 TU-95K22 TU-95MS TU-142MR

Bear A Bear B Bear C Bear D Bear E Bear F Bear G Bear H Bear J

Misson BomberKangarooASMcarrier

KangarooASM plusrecceradomes

ELINTrecce

PhotoRecce

Anti-submarine

Kh-22ASM

Kh-55[AS-15]ALCM

submarinecommunicationrelay

DesignBureau

OKB-156 Tupolev

Manufacturer Plant Nr. 18 Kuibyshev Plant Nr. 18 KuibyshevPlant Nr. 86 in Taganrog

Developmentbegan

6/11/1951

First Flight 11/12/1952 1/1/1956 September1962

October1975

September1979

Datedeployed

August1957

Autum1959

Spring1966

December1972

1982 1981

Crew 8 men 7 men

Power Plant Four turboprop

Power Plant NK-12 NK-12M NK-12MV NK-12MP

MaximumEngine Power(ESHP)

12,500 12,500 14,800 15000

Length [m] 47 49.50 49.6

Height [m] 12.5 12.12 13.4

Wingspan [m] 50.05 51.10

Wing surface[m2]

283.7 288.9

Speed -Maximum 925 830

Speed Cruise(km/hr) 435 425 425 440 440 440 550

SpeedCombat(km/hr)

470 470 475 300 300 490

Ceiling[meters]

12000

Altitude Over 12000 11750 11500 14000 450 450

Target(meters)

Range (withnormal load)[km]

13200 13200 10300 10500

Range (withmaximumload)

6500

CombatRadius (km) 7600 6750 6400 6750 7125

3650[Unrefueled,3-hr loiter,15,000 ft.cruise]

Weight(empty) 70455 70910 72275 71360 71825 72500 94.400

Fuel weight 84.000kg

Fuel Capacity(gal) 29,100 26,900 26,400 29,100 29,100 30,100

Maximumtake-offweight [kg]

182000 185000

Takeoff GrossWeight (kg)Normal

165900 165900 165900 162,275 162,275 162,275

Normal load(kg) 9000 11400 11400 8500

Maximumload (kg)

20000

Armament -Primary

Bombtonnage upto 12.000kg

One H-20 missile

none none

One ortwo H-22missiles

6 Kh-55missiles(TU-95MS6)16 Kh-55Missiles(TU-95MS-16)

none

Armament - Six Am-23 Four AM-23 (23mm) two AM-23 Two GSH-

Secondary (23mm)guns in 3installations

guns in 2 installations (23mm)guns in oneinstallation

23(23mm)guns inoneinstallation

Systems CrownDrummissileguidanceradar

BigBulge I-bandsearchradar

DownBeatmissileguidanceradar



First discovery

Bear A 1955

Bear B July 9, 1961

Bear C February 1962

Bear D March 1965

Bear E April 1965

Bear F April 1972


First public display in practice for May Day flyby April 21, 1955

Public display of three (some observers say nine) aircraft May 1, 1955



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Bear H16Tu-95MS16 with

AS-15 Mod A RKV-500AALCM

Bear H6Tu-95MS6 with AS-15 Mod A

RKV-500AALCM

Bear GTu-95K22

Bear BTu-95K

Bear TTu-95U

Training Heavy Bomber

Bear A

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Bear D

Bear E

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Bear F

Bear G

Bear H

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Molot M-4 / Mya-4 / 3MMyasishchev 'Bison'The Molot (Hammer) was designed as a strategic bomber, but excessive fuelconsumption of its engines and other design shortcomings limited its range to 8,000 km,which was insufficient for striking North American targets and returning to base.Consequently, along with the development of an improved version of the bomber withmore fuel-efficient bypass engines and a new wing, a program was also initiated todevelop a specialized aircraft for aerial refueling. To facilitate operational support andformation flight in the refueling process the bomber and the tanker aircraft were intendedto have identical design and performance characteristics.

Development of an intercontinental bomber with a strike capability at US-territory beganin the early 1950s. The governmental order of 24 March 1951 provided for theestablishment of a new design bureau headed by V.M. Myasishchev. The design bureauwas in charge of organizing and manufacturing the development of the bomber whichwould have a range of 11000-12000 km, a maximum speed of 900km/h and could carry apayload of 5000 kg. The Bison was a Four-engined, swept-wing jet bomber with engineswere buried in the wing roots. An unusual feature was the tandem landing gear, withsmall stabilising wheels at the tips of the drooping wings, and a nosewheel leg extendedat take-off to achieve the correct angle of incidence.

Due to the fact that the high-power BD-5 engines for the aircraft were still in thedevelopment stage, the aircraft used four AM-3A turbojet engines developed by OKBA.A. Mikulina. The first prototype was finished in December 1952 and carried out its'first flight on 20 January 1953. It reached a speed of 947 km/h and a ceiling of 12500 m.Although the bomber had a range of only 8500 km, which did not allow strikes at USterritory, series production of the M-4 bomber began in 1955 at the plant Nr. 23 inMoscow. In July 1955, deployment of the first ten bombers started.

Bison A - M-4/2M -- The Bison A was the original version produced. It ischaracterized by a greenhouse nose and a nose refueling probe. It can be used in afree-fall strategic bombing role, but it is used primarily as a tanker for other Bisonand Bear aircraft requiring in-flight refueling. Between 1956 and 1957, the M-4was equipped with more powerful and low-consumption PD-3M and PD-3M-500A engines to increase range. And a prototype of the M-4, the M-4A, wasequipped with an air refueling system and carried out its' first flight in 1956. Soonafter series production started, studies were conducted on equipping the M-4 withthe Kh-20 air-to-surface missile to strike at targets outside of the bomber's and toovercome air defenses. However, the landing gear did not allow placement of themissile under the fuselage and accommodation of the missile above the fuselagewas rejected. In order to increase the range of the M-4 bomber, it wassubsequently outfitted with new more powerful VD-7 engines. This new bomberhad improved flight characteristics and a bigger propellant capacity relative to the

M-4, with the maximum range increased up to 11850 km. An air refueling systemincreasing range up to 15400 km, which made these bombers the first strategicbomber capable of delivering its' payload into deep enemy territory and returning.The first flight of this bomber designated as 3M bomber took place in March1956. At the end of 1956 series production of the 3M aircraft started at plantNr.23, and deployment started in 1958.

Bison B - 3M/M-6 -- The modified 3M (M-6) bomber was created in 1955. TheBison B has the same basic airframe configuration as Bison A, but it has a slightlylarger wing, a longer nose, increased fuel load, higher thrust an improvedbomb/nav system. Bison B is fitted with a nose refueling probe. Its primarymission is free-fall strategic bombing, but it can conduct alternate missions as atanker when a removable bomb-bay refueling package is installed.

Bison B - 3MS/M-6 -- The reliability of the VD-7 engines caused severalproblems and as a result, between 1958 and 1960 the bomber was outfitted withnew RD-3M-500A engines. This bomber version is designated as 3MS. The rangeof the bombers without additional fuel tanks decreased to 9400 km.

Bison B - 3MS/M-6 -- The associated 3MS2 tanker aircraft included refuelingequipment in the bomb bay. The tanker variant used the "drogue and probe" aerialrefueling technique in which the aircraft being refueled inserts a probe into adrogue at the end of a flexible hose extended from the tanker. This technique wasalso adopted by the U.S. Navy and the air forces of Great Britain, France, Italy,China and other countries. In unique contrast, the US Air Force adopted arefueling technique in which a telescoping boom is lowered from the tail portionof the tanker and enters a special socket on the aircraft being refueled).

Bison C - 3MD/M-6 / 3MN -- In 1960 the 3MD bomber was developed,characterized by a slightly larger wing, a more pointed nose, a shorter andrelocated nose refueling probe, and a larger tail radome. The Bison C has thesame operational performance. Its primary mission is free-fall strategic bombing,but it can conduct alternate missions as a tanker when a removable bomb-bayrefueling package is installed. The 1960 modification of the VD-7 engine - theVD-7B - provided better overall performance though smaller thrust wasdeveloped. The bombers outfitted with these engines received the designation3MN. Their range was increased by 15 percent though they had a lower speed anda reduced ceiling.

Bison C - 3MN-2 -- Several 3M bombers were converted into M-4-2 tankeraircraft, and during the development of the 3MS bomber the 3MS-2 tankeraircraft was developed in parallel. The tanker aircraft that was based on the 3MNreceived the designation 3MN-2. The 3MS-2 tanker aircraft air regiment was inoperational service until 1994.

Project 28 -- To overcome air defenses, a high-altitude version of the M-4(project 28) was studied but not developed prior to the in 1960 to shut down theMyasishchev OKB.

When OKB-23 was shut down in 1960, all activities to upgrade the Bisonbombers ended. In the mid 1970s a Bison was experimentally equipped with twoKh-22 two air-to-surface missiles but this version was not deployed.

3M-T / BM-T "Atlant" -- In the late 1970s a single 3M bomber was convertedto transport outsized components for the Energiya-Buran space launch systemfrom the manufacturing facility to the Baikonur launch site. The cargo, includingpropellant tanks and the Buran orbiter itself, were placed on external mountingpoints located above the fuselage. This particular aircraft had a strengthenedfuselage, a longer two-fin tail and a new flight control system. The originaldesignation of the aircraft was 3M-T but was subsequently changed to BM-T"Atlant". The first flight took place on April 29, 1981 and the first flight withfreight in January, 1982. The plane carried out a total of 150 flights.

In 1963, production of the Bison bombers stopped. A total of 93 aircraft, including tenM-4 and nine 3MD13 were built. The 3M bombers were in service with the Air Forcesuntil the end of the 1980s, and were removed in accordance with the START-1 treaty onoffensive strategic force reductions. The 3MS2 tankers remained in service through 1994.The three airplanes that had been converted to transport oversized cargo are used forpurposes unrelated to the START I Treaty; and are not reconnaissance airplanes, tankerairplanes, or jamming airplanes, and thus do not meet the definition of the term "formerheavy bomber" provided for in the Definitions Annex to the Treaty. These airplanes arenot included within the Treaty totals, though all other airplanes of the Bison type wereconsidered to be former heavy bombers.

SpecificationsSovietDesignation

M-4/2M 3M/M-6 3MS/M-6 3MD/M-6

US-Designation Bison A Bison B Bison B Bison C

Remarks Basic Aircraft Slightly lagerand improved

Slightlychanged noseand tail radome

Design Bureau Myasishchev

Manufacturer Plant Nr. 23 Moscow

Developmentbegan

3/24/1951

First Flight 1/20/1953 3/27/1956

Seriesproduction

1954-1963

Date deployed 1956 1958

Crew 8 men 7 men

Power Plant Four AM-3, or Four VD-7 Four RD-3M- Four VD-7B

Four RD-3M-500, orFour RD-3M-500A

500A

Thrust 8,750kg9,500kg10,500kg each

11,000kg each 10,500kg each 9,500 kg each

Length 47.67m 51.7m

Height 11.5m

Wingspan 50.53m 53.14m

Wing surface 326.35sqm 351.7sqm

Speed Cruise[km/h] 800 800 800 800

SpeedMaximum[km/h]

930 940 925 925

Ceiling 12,500m

Altitude OverTarget (m) 12800 12725 12725

Weight (empty)[kg]

79700 74430

Operational Wt.Empty (kg) 69500 71800 71800

Fuel Capacity(gal) 29,500 34,000 34,000

Fuel weight

MaximumTakeoff GrossWeight [kg]

165900 181800 181800

Normal load 5,000kg 5,000kg 5,000kg 5,000kg

Maximum load 18,000kg 24,000kg

OperationalRange

8,100km 11,850km 9,440km 10,950km

OperationalRange with

8,100km 15,400km 12,400km 13,600km

refuelling

UnrefueledCombat Radius(kmi)

4500 5000 5000

MaximumRange

Armament: 18.000kg of freefalling bombs

Free fallingbombs with acaliber of up to9.000kg whencarrying a loadof 24.000kg,two nuclearbombs with haweight of2.000kg or one4.000kg bomb


Bison A Bison B Bison C


First discovery 30 July 1953 1956 1960

Estimated start of series production 1953 1956 1960

Initial operational capability 1955 1958 1960

First public display (single aircraft} 01 May 1954

Public display of 13 aircraft 01 May 1955

End production 1961

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M-50 / M-52, Myasishchev 'Bounder'OKB Myasishchyev began working on the supersonic intercontinental bomber M-50 in1956. The aircraft was intended to be equipped with and the supersonic long-range M-61cruise missile, also developed by OKB Myasishchyev. The bomber had a strategic strikecapability due to its range of 10,000 km plus the 1000 km range of the missile. The M-50had forward trailing triangular wings, a wing span of 35.1 meters and a length of 57.5meters. Powered by four "16-17" engines developed by P.F. Zubets, two engine podswere mounted outboard on the wings and two less powerful engines at the tip of thewings. The prototype was constructed in 1959 and made the first flight on 27 October1959. As engines the which were supposed to equip the airplane were at that time not yetavailable, on the prototype version two VD-7 engines and two VD-7g were used. In thisconfiguration the demonstrated a speed of Mach 0.99. The second M-50, designated theM-52, carried the Zubets engines around which the aircraft had been designed. Theengine installation was modified, and a second tailplane was added to the top of the fin.

In December 1960, N. S. Khruschev, First Secretary of the Central Committee of theCommunist Party of the Soviet Union (CPSU) made a speech at the Supreme Sovietsession in which he proclaimed the inexpedience of the further development of militaryaircraft. The Soviet leader, fascinated by the triumph of Russian space technology andexploration, directed that all the tasks formerly executed by the combat aircraft beperformed by guided missiles of various types. The Council of Ministers and the CPSUCentral Committee issued a joint decree terminating work on new aircraft. The firstvictims of the decree were the Lavochkin and Myasischev aircraft design bureaus. Theyhad to fully reorganize their work. V. Myasischev was appointed director of TsAGI. Hewas very disappointed at the fact that only a few of his M-50 and M-52 long-rangesupersonic bombers were produced. In 1960 development of the M-50 bomber was haltedwhen OKB Myasishchyev was dis-established.

Surprisingly little is known about the Bounder. One writer commented that it was "anoutstanding failure which revealed an embarassing lack of understanding of the problemsof high-speed flight."

SpecificationsPrimary Function: Heavy bomber

Contractor:

Power Plant: 4*28660lb Soloviev D-15 or4*Zubetc ?? [M-52]

Thrust:

Length:

Height:

Wingspan:

Speed: M1.4

Ceiling:

Weight:

Maximum TakeoffWeight:

Range:

Armament:

Crew:

Unit Cost:

Date Deployed:

Inventory:


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S-100Work on a new large medium-range bomber began in the late 1950s, in response to thedisappointing results obtained with the TU-22 BLINDER, which was intended to replacethe TU-16 [which had not met Air Force requirements]. In 1961 the operational andtechnical requirements for the new airplane were approved, specifying a supersonicmissile-carrier with a speed of up to 3,000 km/h [since the overseas XB-70 could fly at aspeed of 3,000 km/h] and an operational range of 2000 km, capable of hitting enemyaircraft carrier battle groups out in the ocean. The design bureaus A.N. Tupolev, A.S.Yakovlev and P.O.Sukhoi competed for the project, and the results were summed up atthe scientific and technical council held in July 1962. The Tupolev design bureausubmitted the "aircraft 135" project, whose take-off weight equalled 190 tons. The designfailed to match its cruising speed to that of the required one, i.e. 2,500 km/h instead of3,000 km/h. Yakovlev proposed the Yak-35 aircraft, which resembled the AmericanHustler, with a take-off weight of 90 tons and a cruise speed of 3,000 km/h. The T-4/S-100 design submitted by KB Sukhoi was selected, with the support of the military and theState Committee Scientific and Technical Council.

The initial design developed in 1964 called for a tailless delta-wing aircraft with fourturbojet engines placed in a single "gondola" under the fuselage. The wing had a break inthe leading edge, and a small forward stabilizer was included. The plane was to beequipped with three controlled H-45 solid-fuel missiles, located under the fuselage. KBRybinsk developed the RD-36-41 engines under the direction of P.A. Kolesov. InitiallyKB Sukhoi was in charge of the project, but ultimately KB Raduga took over the task.During the design process, the arrangement of the aircraft engines was modified and thenumber of missiles was reduced to two. Construction made extensive use of titanium andsteel alloys, and the T-4 used an advanced electrohydraulic, quadruple redundancy fly-by-wire system. It was fitted with a 'droop snoot' that offered good visibility in thelanding configuration, but when the nose of the aircraft was up and locked, the pilots hadno forward visibility and all flying was on instruments.

The final design was 44.5m long, had a wing span of 22m, a wing surface of 295.7 squaremeters and a lift-off weight of 114 tons. The calculated flight-characteristics indicatedthat the bomber would have a range of 6000 km, a maximum speed of 3200 km/hr at analtitude of 20,000-24,000 meters and an absolute ceiling of 25,000-30,000 meters.

In December 1966, the Sukhoi design bureau presented the Air Force with the mock-upof the T-4 strike/reconnaissance aircraft. In 1967, the Soviet government issued a decreeordering an experimental batch of seven T-4 aircraft to be built, of which one should beused for static research and the rest to be flight-tested. A mock-up airplane was built in1968, and construction of the first prototype began in 1969 at the Series Production Plant82 in Tushino (Moscow). The first flight of the prototype T-4 took place on 22 August1972 and subsequently the plane made 10 flights which were completed in 1974. Duringthese flight trials the plane reached an altitude of 12,100 meters high and a speed of Mach

1.28. It is believed that the 'aircraft 101' that set a Mach 1.89 record over 2,000 km closedcircuit was a T-4.

Soon after testing began, preparation for construction of the first pilot batch of planes wasbegun. In 1974, work on the T-4 bomber was cancelled, given the beginning of serialproduction of the more conventionally designed TU-22M bomber.

Although frequently compared to the American XB-70 intercontinental strategic bomber,which it superficially resembled, the T-4 medium bomber was a rather smaller aircraftintended as a medium-range theater system.

Between 1967-1969, KB Sukhoi also developed a design for the rather larger variable-geometry T-4M strategic bomber, derived from the basic T-4 design. On 10 January 1969the Minister of Aviation Industry issued an order for research and development of astrategic supersonic bomber. A competition was initiated among the aircraft designbureaus of Tupolev, Myasishchev and Sukhoi. In 1969 and 1970 Sukhoi designed the T-4MS bomber that also had variable wings and which was entered into this competition forbuilding a supersonic strategic bomber. The work proceeded slowly, and the T-4MSdesign effort was ended in favor of work on the Su-27 and other high priority tactical

aircraft. In 1975 the contest between Myasishchev's M-18 design [resembling the B-1 inappearance] and Tupolev's Tu-160 was decided in favor of Tupolev.

SpecificationsT-4 (Project) "101"

Powerplant 4x jet engines 4x RD36-41

Thrust lb (kg) each 33,060(15,000) 35,262(16,000)

Length ft(m) - 145.96(44.5)

Wingspan ft(m) - 72.16(22)

Height ft(m) - 36.72(11.195)

Wing area ft^2 (m^2) - 3,182.62(295.7)

Max takeoff weightlb(kg)

264,480 (120,000) 275,500 (125,000)

Takeoff gross weightlb(kg)

220,400-242,440 (100,000-110,000)

251,256 (114,000)

Empty weight 55,600 kg 122,542 (55,600)

Fuel weight lb (kg) - 125,628 (57,000)

Wing loading lb/ft^2(kg/m^2)

- 78.54 (385)

Thrust-to-weight ratio 0.545-0.6 0.56

Cruise speed mph (km/h) 1,863(3,000) 1,987(3,200)

Range @ cruise speed(km)

4000 km

w/o drop tanks 3,726(6,000) 4,347(7,000)

w/drop tanks 4,347(7,000) -

Service altitude mi (km) 13.66-14.90(22-24) 12.42-14.90(20-24)

Takeoff run ft(m) 5,576(1,700) 3,116-3,280(950-1,000)

Landing run ft (m) 1500 m 2,624-3,116(800-950)

Landing speed - -

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T-60SIn the mid-1990s, the first priority for the air forces was the Su-T-60S multirole bomber,which had been designed to replace the Tu-22M and the Su-24 . The Su-T-60S is a long-range supersonic tactical/operational nuclear-capable bomber with built-in stealthtechnology developed by the Sukhoy Design Bureau. Although its development wasofficially secret, the Su-T-60S was reported to be in the prototype stage and ready forflight testing in mid-1996.

The T-60S project for a high-altitude, high-speed bomber was initiated by the Sukhoibureau in 1984 and originally intended to enter service in 2003. Very little information isavailable concerning either the design or current status of this aircraft. The T-60S mayconsist of a blended-body fuselage and a swing-wing construction. The design may becapable of supercruise at Mach 2, with engines possibly equipped with two-dimensionalthrust vectoring nozzles to solve the problem of insufficient area of horizontal controlsurfaces at high speeds encountered during the T-4MS development effort. The aircraftwas intended to replace the current fleet of Tu-22M supersonic bombers, although thisproject has probably been deferred.

Conjectural SpecificationsType intermediate-range strike/interdiction aircraft

Powerplants two 23,500 kg (51,800 lb) turbofans

Max speed Mach 2.04

Cruising speed Mach 2.02

Max altitude 20,000 m (65,500 ft)

Cruising altitude 15,000 m (49,000 ft)

Max range 6,000 km (3,250 nm)

Range with max load 2,200 km (1,200 nm)

Weight (empty) 32,000 kg (70,500 lb)

MTOW 85,000 kg (188,000 lb)

Max load 20,000 kg (44,000 lb)

Wing span (extended) 37 m (121 ft)

Wing span (swept) 24 m (79 ft)

Wing angle (extended) 70 deg

Wing angle (swept) 30 deg

Length 38 m (125 ft)

Height 10 m (33 ft)

Armament

maximum of 20,000 kg (44,000 lb) of free fall nuclearand conventional bombs, guided munitions, up to 8cruise missiles, including Kh-101, Kh-55MS (AS-15Kent) , Kh-15P (AS-16 Kickback)

Tu-22 BLINDER (TUPOLEV)With performance roughly similar to that of the American B-58 Hustler, the BLINDERwas capable of supersonic dash and cruises at high subsonic speeds, At least three majorvariants of the BLINDER entered operational service in the Soviet Air Forces — a free-fall bomber, an ASM carrier, and a photo/electronic reconnaissance variant.

Development of the supersonic TU-22 bomber began after the start of production of theTU-16. During preliminary studies, OKB Tupolev considered three versions: asupersonic attack bomber "98", a long range supersonic bomber "105" and anintercontinental supersonic bomber "108". The first two required swept-wings while the"108" bomber had triangular wings. In the end, the "105" design served as the basis forthe TU-22 while the design of the "98" was applied to the long range fighterplane TU-128. The "108" design was completely dropped. The original design drew heavily on theTU-16 and provided for four BD-5 or BD-7 turbojet engines. The angle of the swept-back wings was increased up to 45 degrees. The project was finally approved by theSoviet government in August 1954, despite numerous objections within the CommunistParty leadership.

This supersonic medium-range bomber is a swept-wing aircraft with two enginespositioned as the base of the tailfin. The low-mounted swept-back wings are tapered withsquare tips and a wide wing root. The landing gear pods extend beyond wings’ trailingedges. Two turbojets engines are low-mounted on the tail fin, with round air intakes. Thiseliminated the need for a complicated boundary layer separation system in the intakes,but added a 15% weight penalty, and made engine maintenance much more difficultbecause of how high they were off the ground. The fuselage is tube-shaped with a solidpointed nose and a stepped cockpit. Tail flats are low-mounted on the fuselage, swept-back, and tapered with square tips. The fin is swept-back, and tapered with square tip.

The prototype of the "105" aircraft with BD-7M engines made its' first flight on 21 June1958, but was subsequently extensively modified and upgraded. The Russians apparentlyhad engine development problems early in the BLINDER program, and BLINDERprototypes were fitted with interim engines. In April 1958, even before the first flight, thedecision was made to equip the aircraft with more powerful HK-6 engines and to build asecond prototype with BD-7M engines. As development of the HK-6 engines wasdelayed, only the second prototype was actually built, which carried out its' first flight inSeptember 1959. During testing, numerous problems arose, and a number of crewmanwere lost in crashes. Series production of this aircraft -- designated the TU-22 -- started atthe plant Nr.22 in Kazan in 1959, where more than 300 TU-22 bombers were builtthrough 1969. It entered operational service in 1962 and by 1970 there were 180BLINDER aircraft in LRA service.

Several versions of the Blinder-bomber were built:

Blinder A - Tu-22B -- Blinder A is primarily employed as a medium bomberdropping free-fall bombs, All of the ten 22B bombers were mainly used fortraining purposes. The aircraft also could be modified to serve as a tanker.Initially, converted TU-16Z planes served as tankers, but from 1972 on they werereplaced by TU-22RM aircraft carrying new onboard avionics.

Blinder B - Tu-22K -- The Tu-22K was equipped to carry one Kh-22 (AS-4Kitchen ) 250-nm range air-to-surface The TU-22K carried a missile, and couldalso carry free-fall bombs. It carried out its' first tests in 1961 and deploymentstarted in 1967 after conclusion of the testing phase.

Blinder C -- In 1962 the maritime reconnaissance aircraft TU-22P was equippedwith an air refueling system and received the designation TU-22PD. About 70'Blinder-C' reconnaissance and electronic warfare aircraft were produced

Blinder D - Tu-22U -- The - Tu-22B is a trainer version similar to Blinder A,though with a raised student cockpit.

Blinder E - TU-22RDM -- Further upgrading in the 1980s lead to the TU-22RDMreconnaissance aircraft.

From 1965 on, all Blinder aircraft were equipped with an air refueling system, consistingof a refueling probe which folds into the fuselage when not in use. And beginning in1965 the TU-22 fleet was re-equipped with more powerful RD-7M2 engines whichallowed an increase in the maximum speed up to 1,600 km/h.

The TU-22 bombers was intended to replace the TU-16, but due to its' poor performanceit was deemed unsatisfactory. Carrying a similar payload to only a slightly greater range,the Tu-22 offered no real increase in capability. Its limited range was its maindisadvantage, though the TU-22K only carried one missile whereas the TU-16 carried upto three. Unreliable and prone to accidents, the Blinder was not built in sufficientnumbers to replace the aging Tu-16 Badgers, which remained in service well into the1970s. Subseqeuntly, KB Tupolev sought to upgrade the TU-22 in the form of a newdesign [designated "106"] that was supposed to have a range of 6700km, a speed of2,000km/h and new HK-6 engines. This effort eventually led to the development of theTu-22M BACKFIRE.

The Tu-22 was used by the Soviet Union in the Afghanistan War, and served the SovietAir Force, and Navy into the late 1980’s. Iraq received about 12 Blinders in 1973, whileLibya received their 12 to 18 from 1977 to 1983. They were used by Iraq during in Iraq-Iran War, and by Libya during the conflicts in Sudan and Chad. A number of Blindersfrom each nation were lost to SAM’s of opposing nations. As of 2000, Ukraine remainsthe sole operator of the type, with the Libyan, and Iraqi aircraft thought to beunserviceable.

SpecificationsDesign Bureau OKB Tupolev

Manufacturer Plant Nr. 22 Kazan

Power Plant Two VD-7M orTwo RD-7M-2 turbojet engines

Thrust 16,000kg16,500kg

Length 41.6 m42.6 m with air refueling

Height 10-10.7 m

Wingspan 23.5 m

Wing surface 163.2sqm

Crew [3 in tandem]One pilotone navigator/systems officerrear gunner

SovietDesignation

Tu-22BTU-22RM Tu-22K TU-22P Tu-22U TU-22RDM

US-Designation Blinder A Blinder B Blinder C Blinder D Blinder E

Mission

BasicMediumBomber

AirRefuelingTanker

KitchenASMCarrier

MaritimeRecceAircraft

TandemTrainer

RecceAircraft

Developmentbegan

August1954


Series production 1959-1969

Date deployed 1962 1967 1962 1968?

MaximumTakeoff GrossWeight (kg)

85500 94000 84100 84100

Operational Wt.Empty (kg) 39050 41000-

48100 41000 39050

Fuel weight [kg] 42,500 42,500

Fuel Capacity(gal) 13,600 12,350 34,000 13,600

Combat Radius(km) Unrefueled 2450 1300-

2200 4400 n.a.

Maximum Range[km]

5,6507,150

(with airrefueling)

4900

Normal load 3000 5850

MaximumPayload (kg) 12000 12000 4500 n.a.

Altitude OverTarget (m) 11000 11000 12750 n.a.

Ceiling 13,300-14,700 meters

Speed Cruise 832 825 835 n.a.

Speed Combat 1610 1570 910 n.a.

Speed Maximum 1510 km/h (with VD-7M engines)1610km/h (with RD-7M-2 engines)

Armament:Primary

Bombsfrom250kg upto9.000kgor nuclearbombs

One H-22missile

Armament:Secondary

One R-23 (23mm) gun



First discovery

Blinder A January 1960

Blinder B 1961

Blinder C June 1965

Blinder D 1966




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Tu-22M BACKFIRE (TUPOLEV)The BACKFIRE is a long-range aircraft capable of performing nuclear strike,conventional attack, antiship, and reconnaissance missions. Its low-level penetrationfeatures make it a much more survivable system than its predecessors. Carrying eitherbombs or AS-4/KITCHEN air-to-surface missiles, it is a versatile strike aircraft, believedto be intended for theater attack in Europe and Asia but also potentially capable ofintercontinental missions against the United States. The BACKFIRE can be equippedwith probes to permit inflight refueling, which would further increase its range andflexibility.

After designing the TU-22, the Tupolev design bureau started working on a new bomberthat was based on the TU-22. Initially Tupolev considered modifying the TU-22 bychanging the angle of the swept wings and equipping it with more powerful engines.However after developing the design "106" and various analysis, the design did not meetthe flight characteristic requirements. Tupolev also developed the design "125". Theaircraft was supposed have two VK-6 engines, a range of 4500-4800 km and an operatingspeed of up to 2500 km/h. The design provided for the use of titanium alloys andadvanced electronic systems.

In 1962, the "125" design was examined by the Government but rejected, as the T-4aircraft designed by KB Sukhoi was accepted. As an alternative to the T-4 aircraft, KBTupolev developed the "145" airplane which was a modification of the TU-22. Thisairplane represented a multi-mode supersonic bomber which was capable of flying atsubsonic speed at small altitudes and at supersonic speed to overcome air defenses. Therange at subsonic speed was supposed to be 6000-7000 km. The wings are swept-backand had a variable geometry to meet the speed and range requirements. The aircraftshould carry Kh-22 air-to-surface missiles which had already been deployed on otheraircraft. After activities on the T-4 bombers were halted, KB Tupolev was officiallycharged with building the "145" aircraft in 1967. The new bomber was intended to have amaximum speed of 2300 km/h and a range of 7000 km without refueling. It received thedesignation TU-22M.

The Tu-22M designation was used by the Soviets during SALT-2 arms controlnegotiations, creating the impression that the Backfire-A aircraft was a modification ofthe Tu-22 Blinder. This designation was adopted by the US State and DefenseDepartments, although some contended that the designation was deliberately deceptive,and intended to hide the performace of the Backfire. Other sources suggest the"deception" was internal, because this made it easier to get budgets approved. Accordingto some sources, the Backfire-B/C production variants were believed to be designatedTu-26 by Russia, although this is disputed by many sources. At Tupolev the aircraft wasdesignated the AM.

Many of the development steps in manufacturing the AM were unique in their time.Special attention was given to the construction of the variable sweep wing - the basis of

the whole project. The mid-mounted wings are variable, swept-back, and tapered withcurved tips and a wide wing root. Two turbofan engines are mounted in the body, withlarge rectangular air intakes and dual exhausts. The fuselage is long and slender with asolid, pointed nose and stepped cockpit. The body is rectangular from the air intakes tothe exhausts. The tail fin is swept-back and tapered with a square tip. The flats are mid-mounted on the body, swept-back, and tapered with blunt tips. The wing consists of acenter section and two outer panels that have five fixed positions with respect to theleading edge sweep. The two-spar centre section has a rear web and bearing skin panel.The outer wings are secured to the centre section with the aid of hinged joints. The high-lift devices include three-section slats and double-slotted flaps on the outer wings(extension angle: 23~ for takeoff and 40~ for landing) and a tilting flap on the centresection.

Backfire A - TU-22MO -- The first TU-22M received the designation TU-22MObut was only produced in small quantities due to inadequate performance. InFebruary 1973 two TY-22Mo bombers were transferred to a training center.

Backfire A - TU-22M -- The first prototype of the TU-22M was finished in July1971. The test phase of the few TU-22M lasted four years, after which they weredeployed with Soviet Naval Aviation.

Backfire B - TU-22M2 -- The first large-scale modification of the TU-22M wasthe TU-22M2, which conducted first flight tests in 1973. It was equipped withNK-22 engines, had range of 5100 km and a maximum speed of 1800 km/h. Itcarried up to three Kh-22 air-to-surface missiles. The aircraft did not have anautomatic terrain-following system but was nevertheless capable of low-levelflight to overcome air defenses. In 1976, the TU-22M2 was deployed with the airforce and naval airforce. A total of 211 TU-22M2 aircraft were produced at theplant Nr.23 in Kazan between 1973 and 1983. Soon after series production of theTU-22M2 began, the aircraft received new NK-23 engines to increase speed andrange. The NK-23 is a booster version of the NK-22 engine, which did notachieve the expected goals.

Backfire B - TU-22M2Ye -- Some aircraft were outfitted with new NK-25engines and an sophisticated new flight-control system. They were designated asTU-22M2Ye, but did not achieve improved flight characteristics.

Backfire C - TU-22M3 -- During subsequent upgrades the nose was lengthened,the air intakes changed and the maximum angle of the swept-variable geometrywings increased up to 65 degrees. The aircraft received the designation TU-22M3and carried out its' first flight test on 20 June 1977. The TU-22M3 beganoperational evaluation in the late 1970s, and in 1983 it was introduced into theactive inventory. Cleared of some of the shortcomings of its predecessor thisaircraft soon proved its worth in service with long-range and naval aviation units.The range of the bomber was increased to 6800 km, the maximum speed up to2300 kms/h and the payload was twice that of the Tu-22M2. The bomber isequipped with a maximum of three Kh-22 cruise missiles or up to ten Kh-15 (AS-16) short-range missiles. It can also carry nuclear bombs. In 1985 the TU-22M3conducted high-peed flight tests at low altitude that demonstrated the capability ofcountering air defenses.

Backfire - TU-22MR -- In 1985, the long-range reconnaissance aircraft TU-22MR entered service.

Backfire - TU-22ME -- Improvement of flight and fighting characteristicscontinued, and in 1990 the TU-22ME was developed.

When the new supersonic bomber appeared at the Kazan aircraft plant in 1969, itvalidated the long-held Air Force prediction of a new Soviet bomber. In 1971, theaircraft, now designated the Backfire, was noted in aerial refueling from a tanker near thetest center of Ramenskoye, just east of Moscow. The mission of the bomber, peripheralattack or intercontinental attack, became one of the most fiercely contested intelligencedebates of the Cold War. The key variable was the estimate of the range of the aircraft. Aseries of competitive analyses to determine the range produced divergent results andfailed to end the debate.

Tupolev claimed a radius of action of only 2,200km for the early model Backfires. TheUS Defense Intelligence Agency (DIA) initially had estimated the Backfire's unrefuelledcombat radius at approximately 5,000 km, sufficient to pose a strategic threat to theUnited States, while the Central Intelligence Agency (CIA) estimate was about 3,700 km.subsequently the DIA estimate was reduced to about 4,000 km, and the CIA estimate to3,360-3,960 km.

The dominant view of the American intelligence community was that the Backfire was aperipheral attack weapon and would not play a significant role in a strategic air attack onthe United States. This view was based on the Backfire's limited payload, modest self-defense capabilities, and anticipated difficulty in staging the aircraft from northernSiberian bases. The US lacked hard evidence that the Backfires ever rehearsedintercontinental strike missions. The Air Force estimate of range and intent argued thatthe Backfire could be used for intercontinental attack -- even if the aircraft flew one-waymissions for an attack on the United States.

Athough a significant number of Backfire bombers were targeted on US naval vessels,the Backfire was the focus of a hotly contested arms control debate that focused onfailure to limit further modernization and production of Backfire fleet. Although theBackfire bomber had an exclusively theater mission, under certain circumstances, it couldbe used to strike targets in the United States. Arms control opponents contended that theUnited States left open a loophole the Soviets would eventually exploit. The UnitedStates stated that as it can be refueled in flight -- allowing it to reach the United States --the Backfire was an intercontinental bomber and should be subject to the samerestrictions as other strategic bombers. The Soviets consistently maintained that theBackfire was not a strategic bomber because of its non-intercontinental range.

During the SALT II process, the United States negotiating team obtained a statementfrom then-Soviet Premier Brezhnev that the Backfire's refueling capabilities would not beupgraded to allow them to function as intercontinental strategic bombers, and that theSoviets would only build 30 of these bombers per year. When the SALT-2 treaty wassigned in 1979, the Soviets informed the USA that it would not equip the TU-22M

bombers with air refueling devices. SALT II was not ratified, though subsequently the airrefueling system was removed from all TU-22M.

According to press reports in the late 1980s, a defector stated that the Backfire wasregularly exercised at intercontinental range, that this intercontinental range was greaterthan the Bison's, that the Backfire had a screw-in type refueling probe, that this screw-inrefueling probe was stockpiled for every Backfire at all bomber bases, and that theSoviets had an active program of camouflage, concealment, and deception to mislead theWest about the intercontinental range capability of the Backfire.

According to press reports, the Soviets tested long range ALCM'son the Backfire in the late 1970's. The CIA in 1987 made theunclassified judgment that it would consider Backfires as ALCM-carriers in the event of confirmed Soviet breakout from SALT II.The CIA's rationale for their judgment was that in the absence ofSALT II constraints, the Soviets would use the ALCM-capableBackfire to attack the United States.

The Defense Department publication Soviet Military Powerpublished in March, 1983, stated on page 26 that: "The Soviets are developing at leastone long-range air-launched cruise missile (ALCM) with a range of some 3,000kilometers. Carried by the Backfire, the Blackjack, and possibly the Bear, it wouldprovide the Soviets with greatly improved capabilities for low-level and standoff attack inboth theater and intercontinental operations."DIA stated in its unclassified February 1990Soviet Force Structure Summary publication on page 6 that: `The Backfire has anintercontinental strike capability when equipped with a refueling probe.'

The US proposed to the Soviets that they sign a politically binding declaration outside ofSTART, which would commit them to: (1) not give the Backfire an intercontinentalcapability by air-to-air refueling or by any other means; (2) deploy no more than 400Backfire; and (3) include all Backfire -- including naval Backfire--in the ConventionalForces in Europe [CFE] aircraft limits.

On 31 July 1991 the Soviet side declared as part of the START I negotiations that itwould not give the Tu-22M airplane the capability of operating at intercontinentaldistances in any manner, including by in-flight refueling. The Soviet Union stated that itwould not have more than 300 Tu-22M airplanes at any one time, not including naval Tu-22M airplanes, and that the number of naval Tu-22M airplanes would not exceed 200. Inview of the fact that there must be no constraints in the START Treaty on arms that arenot strategic offensive arms, Tu-22M airplanes would thus not be subjected to thatTreaty.

During the 1980s Backfires were used for conventional bombing raids in Afghanistan,particularly during the last year of direct Soviet involvement. By 1991 it was reportedthat, due to a shortage of spare parts, some Backfire units had mission-capable rates of30-40%. During the 1990s many Backfires were transferred from Long Range Aviation

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forces to Russian naval units in north Russia. However, by the late 1990s, at least 125were in service with Long-Range Aviation and another 47 were in service with in NavalAviation.

In December 1999 it was announced that India would lease four Tu-22M3 Backfirebombers, with the aircraft slated arrive in India as early as June 2000. India's Tu-142 andIl-38 aircraft will be upgraded in Russia. An initial batch of five aircraft will be sent toRussia and during this period the Tu-22M3s will undertake a maritime role armed withAS-20 Kayak anti-ship missiles. India is making substantial purchases of the Novator3M-54 Alfa missile to equip Kilo class submarines and its new frigates. It is believed thatan air-launched variant will be purchased to arm the Tu-142s currently in service and thesix to eight additional aircraft being sought by the Navy. If an air-launched version of theAlfa is procured, it is anticipated that India's Tu-22M3s will eventually be equipped tofire them.

SpecificationsSovietDesignation

TU-22M0 TU-22M1 TU-22M2 TU-22M3

US-Designation

Backfire A Backfire A Backfire B Backfire C

DesignBureau

OKB-156 Tupolev


Approved

Developmentbegan

1967

First Flight 8/30/1969 6/1/1971 1972 6/20/1977

Seriesproduction

1971 1973-1983 From 1977on

Datedeployed

Notdeployed

1976 1976 1981

Crew 4 men

Unit cost

Power Plant Two NK-144-22turbojetengines

Two NK-22turbojetengines

Two NK-22 turbojetengines

Two NK-25turbojetengines

Thrust 20.000kg 22.000kg 22.000kg each 25.000kg

each each each

Length 41.5m 41.5m 41.46m 42.46m

Height 11.05m

Wingspan(minimum)

22.75m 25m 25m 23.3m

Wingspan(maximum)

31.6m 34.28 m 34.28 m 34.28 m

Wing surface 183.5sqm(atminimumsweep),175.8sqm(atmaximumsweep)

Speed(cruise)

900km/h 900km/h

Speed(maximum)

1.530km/h 1.660km/h 1.800km/h 2.300km/h

Ceiling 13.000m 14.000m

Weight(empty)

53,500kg

Fuel weight

Maximumtake-offweight

121.000kg 122.000kg 122.000kg 126.400kg

Normal load 6.000kg

Maximumload

24.000kg

OperationalRange[RussianSources]

4,140km 5,000km 5,100km 7,000km

CombatRadiusunrefueld[US

4,000-5,000 km [DIA]3,360-3,960 km [CIA]

estimates]

Armament: Two GSH-23 (23mm)guns

One to three H-22missilestwo GSH-23(23mm) guns

One tothree H-22missilessix to tenH-15missiles24.000 kgof 250-9,000kg freefall bombsonedouble-barrelledGSH-23(23mm)guns


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Tu-160 BLACKJACK (TUPOLEV)The Tu-160 is a multi-mission strategic bomber designed for operations ranging fromsubsonic speeds and low altitudes to speeds over Mach 1 at high altitudes. The twoweapons bays can accommodate different mission-specific loads, including strategiccruise missiles, short-range guided missiles, nuclear and conventional bombs, and mines.Its basic armament of short-range guided missiles and strategic cruise missiles enables itto deliver nuclear strikes to targets with preassigned coordinates.In the future, after theaircraft is equipped with high-precision conventional weapons it may also be used againstmobile or tactical targets.

The Tu-160 was the outcome of a multi-mission bomber competition, which included aTupolev proposal for an aircraft design using elements of the Tu-144, the MyasishchevM- 18, and the Sukhoi a design based on the T-4 aircraft. The project of Myasishchevwas considered to be the most successful, although the Tupolev organization wasregarded as having the greatest potential for completing this complex project.Consequently, Tupolev was assigned to develop an aircraft using elements of theMyasishchev M-18 bomber design. The project was supervised by V.N. Binznyuk. Trialoperations in the Air Forces began in 1987 with serial production being conducted at theKazan Aviation Association.

The Tu-160 is characterized by low-mounted, swept-back, and tapered, variablegeometry wings with large fixed-center section. The variable geometry wings (from 20degrees up to 65 degrees) allows flight at supersonic and and subsonic speeds. Four NK-32 TRDDF [turbojet bypass engines with afterburners] of 25,000 kilograms-force powerthe T-160. The four turbofans, developed by OKB Kuznetsov in 1977, are mounted inpairs under the fixed-center section with square intakes and exhausts extending behindthe wings’ trailing edges. The fuselage's slim structure is marked by a long, pointed,slightly upturned nose section and a stepped canopy. Tail flats are swept-back, tapered,and mid-mounted on the fin. The tail fin is back-tapered with a square tip and a fairing inthe leading edge. The tail cone is located past the tail section. During the design of theaircraft, special attention was paid to reducing its signature. Measures were applied toreduce the signature of the engines to infra-red and radar detectors. Tests of thesesurvivability measures were first tested on a TU-95 aircraft in 1980.

As the most powerful combat aircraft of the Soviet Air Forces, the T-160 flies at 2,000km/hr and can exceed the 2,000 mark with a mission-specific load. The T-160 can climb60-70 meters per second and reach heights of up 15,000 meters. The bomber can berefueled during flight by IL-78 and ZMS-2 tanker aircraft. The air refueling systemconsists of a probe and drogue airborne refueling system.

The TU-160 can carry up to 12 Kh-55 long range missiles and Kh-15 short rangemissiles. The weapons bays can accommodate different loads: carries various bombs:From fee falling nuclear and regular up to 1500 kg bombs. The bomber is not equippedwith artillery armament.

The Tu-160 is equipped with a combined navigation-and-weapon aiming system, RID;[radar] for detecting targets on the ground and sea at long distances, an optical-electronicbombsight, an automatic terrain-following system, and active and passive radio-electronic warfare systems, as well as a probe-and-drogue airborne refueling system. It isequipped with K-36DM ejection seats. The cockpit instruments are the traditionalelectromechanical type. The aircraft is controlled with the aid of a central control column.The engine control throttles are located between the pilots' seats. There is a rest area, atoilet, and a cupboard for warming up food.

Studies have also been conducted on using the aircraft as a launch platform for the"Burlak" space launch vehicle, which is designed to carry payloads with a mass of 300 to500 kg in polar orbits at an altitude of 500 to 700 km. Under this concept the launchvehicle, which has a solid-fuel engine and a delta wing, would be suspended under theairplane's fuselage.

In 1981 OKB Tupolev built two prototypes of the bomber and one mock-up that wasused for static tests. The first flight test of the "70" aircraft took place on 19 December1981. During flight tests, one of the two original planes was lost. Shortly after testsbegan, series production started. In 1984, the factory in Kazan started producing thebomber which received the designation TU-160. Initial plans provided for theconstruction of 100 airplanes but when their production was stopped in 1992, only 36bombers had been built.

In May 1987, deployment of the first bombers began. Until the end of 1991, 19 TU-160bombers served in the 184th regiment in Ukraine and became Ukrainian property afterthe dissolution of the USSR. In 1992 the 121th air regiment based at the aerodrome B.G.Engels was equippd with TU-160 bombers. Subsequently the bombers were tested tocarry long range missiles.

It was reported on 02 July 1999 that the Gorbunov Kazan Air Industrial Associationreceived an order from the Ministry of Defense of Russia to complete the production ofone Tu-160 strategic bomber. According to the Association's general director NailHairullin the contract for the aircraft production was worth 45 million rubles.

In July 1999 the Minister of Defense of Ukraine Alexander Kuzmuk confirmed that Kievofficially proposed that Moscow accept as payment for the gas debts "about 10 strategicbombers Tu-160 and Tu-95". He refused to tell the exact cost of missile carriers,however, in his judgement, it would be "considerably more" than 25 million dollars foreach machine. On 12 October 1999 the Russian air force announced an agreement thatwould allow Ukraine to pay some of its multimillion-dollar energy debts by handing over11 strategic bombers. Ukraine had tried to unload the bombers since the Soviet Unioncollapsed in 1991, but talks had foundered because of differences over the price tag andother conditions. The deal includes eight Tupolev 160 Blackjack bombers and threeTupolev 95 Bears.

The 11 strategic bombers and 600 air-launched missiles exchanged by Ukraine to Russiain payment for the gas debt were transfered in mid-February 2000. Two Tu-160 bombersflew from Priluki in the Ukrainian Chernigov region for the Russian air base in Engels.The missiles were sent to Russia by railroad. Three Tu-95MS bombers and six Tu-160airplanes had already arrived at Engels since October 1999 in fulfilment of theintergovernmental agreements. Before being moved to Russia, 19 Tu-160 airplanes werestationed at the Priluki airfield and 21 Tu-95MS were located in Uzin.

SpecificationsSoviet Designation TU-160

US-Designation Blackjack

Design Bureau OKB-156 Tupolev


Power Plant 4 HK-32 turbojet engines

Thrust 25.000 kg each

Length 54.1

Height 13.1

Wingspan 35.6m (minimum), 55.7m (maximum)

Wing surface 232 sqm

Speed 2200 km/h (maximum), 1030 km/h (ground)

Ceiling 16.000m

Weight (empty) 110.000kg

Fuel weight 148.000 kg

Maximum take-off weight 275.000 kg

Normal load 9.000 kg

Maximum load 40.000

Range 14.000 km (with a load of 9.000kg)

10.500 km (with a load of 40.000 kg)

Armament 12 H-55 or 24 H-15 missiles

free falling bombs

Systems

Crew 4

Accomodation

Unit cost

Approved



Series production started 1984

Date deployed 1987

Inventory

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AS-1 KENNELSSC-2a SALISHSSC-2b SAMLETThe AS-1 air-to-surface missile is a subsonic,turbojet-powered, cruise missile with arange or 35 to 97 nm. It weighs approximately 6030-lb and has a conventional warheadof 2020-lb. For guidance, it uses a preprogrammed autopilot for launch and climb, abeam rider for mid-course, and semi-active radar for terminal flight. It has a CEP of 150ft when used in an anti-ship role and a CEP of 1.0 nm when used against land targets.Two AS-1 missiles are carried on the Badger B aircraft. Production of the AS-1 isestimated to have began in 1953, with IOC reached in 1956. It was first seen in 1961.

Two versions of the SSC-2 were developed from the Soviet "KENNEL" air-to-surfaceanti-shipping missile. They resemble a small jet fighter in appearance and are transportedon one-axle semitrailers. The field missile SSC-2a "SALISH" is launched from itstransport semitrailer which is towed by a KrAZ-214 tractor truck The SSC-2b"SAMLET" coastal missile transport semitrailer is towed by a ZIL-157V tractor truckand is not used for launching. The missile must be removed from the transport semitrailerand placed on a large rail-type launcher for firing. The "SAMLET" coastal defensemissile is the most commonly encountered cruise missile, and has been identified in EastGermany and Poland.

SpecificationsContractor

Initial operationalcapability 1956

Production terminated 1960

First detected 1961

Total length

Diameter

Wingspan

Weight

Warhead Weight

Propulsion

Maximum Speed

Maximum effective

range

Guidance mode

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Mikoyan K-10S (AS-2 Kipper)The AS-2 air-to-surface missile is a supersonic, turbojet-powered, low-level run-in,cruise missile with a range of 30 to 100 nm. The K-10S missile (Article 352), developedspecially for the Tu-16K-10 (Badger-C) aircraft as weapon against naval vessels, was inOctober 1961, together with that aircraft certified for ordnance. One K-10S missile issuspended from the aircraft, under the middle section of the fuselage. It carries either aconventional or a nuclear 2200-lb warhead. The missile weighs approximately 9120pounds. For guidance, it uses a preprogrammed autopilot for launch and climb, anautopilot with command correction for mid-course flight, and active radar for terminalflight. The guidance system combines inertial guidance during the initial flight stage andactive-radar homing close to the target. The missile can carry a nuclear warhead. It has aCEP of 150 ft when used in an anti-ship role and a CEP of 1 to 2 nm when used againstland targets.



First detected 1961

Productionterminated 1965

Type long-range anti-ship standoff missile

Wingspan 4.6-4.88 m

Length 9.5 m

Diameter 0.9 m

Launch weight 4200 kg

Max. speed 1400 km/h

Ceiling 12000 m

Maximum range 260-350 km

Propulsion Lyulka AL-5 RD-9FK liquid fuel turbojet

Guidance active radar homing

Warhead impact with delay-fuzed high explosive, 1000 kg ornuclear 1000-kg warhead

Kh-20 / AS-3 KANGAROOThe AS-3 air-to-surface missile is a large, supersonic, turbojet-powered, cruise missileweighing approximately 24,500 lb with a range of 100 to 350 nm. It carries a 5000-lbnuclear warhead. For guidance it uses a preprogrammed autopilot for launch and climb,an autopilot with command guidance for mid-course flight, and a preprogrammed dive totarget. It has a CEP of 150 ft when used in an anti-ship role and a CEP of 1 to 3 nm whenused against land targets. One AS-3 is carried aboard the Bear B and Bear C aircraft.


Type meduim- to long-range standoff missile


First detected 1961

Productionterminated 1965

Wingspan 9.2 m

Length 14.9 m

Diameter 1.9 m



Ceiling 18000 m

Maximum range 650 km

Propulsion Tumansky R-11 twin spool turbojet with afterburner,50.9 kN of thrust

Guidance beam riding

Warhead high-explosive, 2300 kg, or thermonuclear, 800 kTyield

Raduga Kh-22 (AS-4 Kitchen)Built by A. Berezhnyak's "Raduga" engineering group for Tu-22 and Tu-22M aircraft,this missile is now also arming modified Tu-95K-22 aircraft. During experimental testsconducted from the late nineteen fifties to the early nineteen sixties the Kh-22B versionhad reached a speed of Mach 6 and an altitude of about 70 km. The "Raduga" DesignBureau, first a branch of Mikoyan's OKB-2-155 Special Design Bureau, became anindependent group in March 1957. Since 1974, after the death of Alexander Berezhnyak,its chief engineer is Igor Seleznyev. The Kh-22 missile comes in three variants: 1. Kh-22N with a nuclear warhead and inertial guidance; 2. Kh-22M with a conventional loadfor use against ships and with an active-radar operating during the final flight stage; 3.Kh-22MP for breaking through enemy air defenses (overcoming enemy radars).


Type long-range tactical standoff missile

Wingspan 3.0 m

Length 11.3-11.65 m

Diameter 0.92 m

Launch weight 5780-6000 kg


Ceiling 24000 m


Propulsion liquid propellant rocket motor

Guidance active radar or passive infra-red homing

Warhead high-explosive, 1000 kg, ornuclear, 350 kT yield


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KSR-2 / KS-11AS-5 KELTThe AS-5 air-to-surface missile is a small supersonic, liquid-rocket propelled, cruisemissile weighing approximately 7760 lb. It has a maximum speed of Mach 1.2 at analtitude of 30,000 ft. and a range of 80 to 125 nm. It can carry an 1100-lb conventionalwarhead, or a nuclear warhead weighing 850 to 1200 lb. For guidance, it uses active radarhoming from launch to impact when employed in an anti-ship role, and an alternatepassive radar homing system when used in an anti-radar role. It has a CEP of 150 ft whenused in an anti-ship role, and a CEP of 1 to 2 nm when employed against land targets.

The Badger G carries two AS-5 missiles suspended beneath its wings. Production of themissile is estimated to have begun in 1963, with IOC in 1965. It was first seen in 1966.


Year 1968

Type anti-ship and ground attack standoff cruise missile

Wingspan 4.6 m

Length 9.5 m

Diameter 0.9 m



Ceiling 18000 m

Maximum range 320 km

Propulsion single stage liquid propellant rocket motor

Guidance active radar or anti-radar seeker

Warhead impact- and direct impact-fuzed high explosive, 1000kg

Service CIS, Egypt

Raduga KSR-5 (AS-6 Kingfish)The AS-6 air-to-surface missile is a supersonic, liquid-rocket propelled, cruise missileweighing approximately 13,000 lb. It has an estimated maximum speed of Mach 3.5 at analtitude of 65,000 ft. and an estimated range of 300 nm. It can carry an 1100-lbconventional or nuclear warhead. For guidance it uses a preprogrammed autopilot forlaunch and climb, an inertial guidance system or an autopilot with radio commandoverride for mid-course, and an active radar system for terminal dive when used in anantiship role. It has a CEP of 150 ft when used in the antiship role, and a CEP of 1 to 2nm when employed against land targets. The AS-6 probably is a follow-on to the AS-2and AS-5.

This is a smaller version of the Kh-22 missile, intended for Tu-16 bomber aircraft. Seriesproduction of the KSR-5 (Article D-5) anti-ship version with active-radar homing beganin 1966. Target indication is given by either a "Rubin" radar of the Tu-16K-26 or a YeNradar of the Tu-16K-10-26. The KSR-SP antiradar missile entered service in 1972, atwhich time was also built the KSR-5N version with a nuclear load. On the basis of theKSR-5 was later built the KSR-5NM airborne target for training exercises. ModifiedBadger C and Badger G aircraft carry two AS-6 missiles. The Backfire may also havebeen an AS-6 carrier, but evidence is lacking to confirm this estimate. Production isestimated to have begun in 1969,with IOC in Badger aircraft in 1970. IOC with Backfireis estimated in 1974.


operational Badger 1970

operational withBackfire 1974

Type long-range cruise missile

Wingspan 2.5 - 2.61 m

Length 10.0 - 10.52 m

Diameter 0.9 m

Launch weight 3900-4800 kg

Max. speed 3200 - 3400 km/h

Ceiling 20000 m


Propulsion two stage solid propellant rocket motor

Guidance active radar or anti-radar seeker

Warheadproximity-, impact- or impact with delay-fuzed high-explosive, 1000 kg, ornuclear, 350 kT yield 700 kg

Service CIS, Iraq


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Kh-55 GranatAS-15 KentSS-N-21 SampsonSSC-4 SlingshotThe Kh-55 strategic cruise missile is used for destroying targets whose coordinates areknown. Its guidance system combines inertial-Doppler navigation and position correctionbased on comparison of terrain in the assigned regions with images stored in the memoryof an on-board computer. The propulsion system is a dual-flow engine locatedunderneath the missile's tail. The missile carries a 200 kt nuclear warhead.

The first tests of this missile were conducted in 1978 and a few units were installed onTu-95MS aircraft in 1984. Three aircraft versions of this missile are known: Kh-55(Article 120, alias RKV-500, NATO's AS-15a), Kh-55-OK (article 124), Kh-55SM(Article 125, alias RKV-500B, NATO's AS-15b). In addition the land version RK-55(SSC-X-4) was destroyed in compliance with INF disarmament negotiations. The seaversion SS-N-21 Sampson is reportedly deployed on the Akula, Victor III, YankeeNotch, and Sierra class SSN submarines. However, since the SSC-4 coastal defensevariant is carried in a 25.6-in (650-mm) diameter canister, some analysts have suggestedthat the sub- launched variant is probably for launch only from 650-mm diameter torpedotubes.

Russian President Boris Yeltsin announced in January 1992 that he would end themanufacture of all sea- and air- launched cruise missiles. In March 2000 it was reportedthat the Russian Air Force had tested a new cruise missile with a conventional warhead. Itwas said to be a Kh-555 missile, which was developed from the Kh-55, with a range of2000 - 3000 km.

Raduga Kh-65The Kh-65 missile is a tactical modification of the strategic Kh-55. According to the firstavailable information (on data sheets at the 1992 Moscow Air Show), its range was to be500-600 km. The reason for shortening its range was that, according to terms of theSALT-2 Treaty, any aircraft carrying missiles with a range longer than 600 km will beregarded as a strategic one and the number of such aircraft is strictly limited. A full-sizedversio of the Kh-65SE was displayed for the first time in 1993 (February in Abu Dabi,then September 1993 in Zhukovskiy and Nizhniy Novgorod). The missiles shown at theexhibitions did not differ from the earlier versions except for their range, quoted as 250km when launched from low altitude and 280 km when launched from high altitude. TheKh-65 was intended for use against large targets with a larger than 300 m2 effectivereflecting surface area, particularly warships, under conditions of strong electronicinterference. It approaches the target guided by an inertial navigation system while flying

at a low altitude. Having reached the region where the target is located, it rises to a higheraltitude and its active-radar target seeking system turns on.

SpecificationsVersion Kh-55SM Kh-65SE

ContractorRaduga OKBM. I. Kalinin MachineBuilding Plant

Entered Service

Total length 8.09 m 6.04 m / 19 ft, 6 in

Diameter 0.77 m; (Kh-55 0.514 m) 0.514 m

Wingspan 3.10 m 3.10 m / 10 ft, 1 in

Weight 1700 kg 1250 kg

Warhead 200-kt nuclear 410 kg HE

Propulsion

Speed Mach 0.48-0.77 Mach 0.48-0.77

Maximum effectiverange

3000 km (Kh-55 2500km) 250-280 km

Flight Altitude 40-110 m

Guidance mode


AS 15 Mod ARKV-500A

ALCM

AS 15 Mod BRKV-500B

ALCM

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P-750 GromBL-10AS-19 KOALASS-N-24 SCORPIONSSC-5The P-750 Grom supersonic winged cruise missile with a range of 3000-4000 km wasdeveloped for replacing the Kh-55 [AS-15 KENT]. The AS-X-19 Koala was an air-launched land-attack version derived from the SS-NX-24 Scorpion submarine-launchedmissile. A pair of AS-19 missiles was expected to arm the Tu-142 Bear-H bomber. Themissile carried two warheads independently guided to hit two targets 100 km apart. Theletters BL in its American designation refer to the firing range in Barnaul, where it wastested; its Russian industrial index designation is not known. Work on the program wassuspended in 1992.

SpecificationsContractor Chelomey

Entered Service cancelled

Total length 7 meters

Diameter

Wingspan

Weight 2,000 kg

Warhead 2 x 200 kt nuclear

Propulsion turbojet or rocket/ramjet

Maximum Speed supersonic


Guidance mode 3000-4000 km

Kh-65 / Kh-SDKh-101As of 1996 it was reported that at least two next-generation strategic cruise missiles wereunder development. By late 2000 very few details had emerged concerning eitherprogram, neither of which appeared to have received Western designations. It is reportedthat Russian Air Force plans call for upgrading the Tu-95MS `Bear-H' bomber to carryup to eight Kh-101 or 14 Kh-65 cruise missiles. The status of a plan for the Tu-160 tocarry 12 Kh-101s or Kh-65s is unclear, and may have been cancelled.

The long-range Kh 101 cruise missile is under development for long-range aviation. Itwas apparebtly first launched in October of 1998 by Tu-160 during 37th Air Armyexercises. It will reportedly be employed with either a nuclear or a conventional warhead.The conventional warhead version required the use of a highly accurate guidance system,which reportedly provides a circular error probable of 12-20 meters. An electro-opticflight path correction system uses a terrain map stored in its onboard computer, as well asa TV-seeker for the terminal stage of flight. The Kh-101's launch weight is 2,200-2,400kg and its maximum speed is Mach 0.77. The range of this system probably exceeds3,000km, and some reports claim a range of as great as 5000 km.

Russian President Boris Yeltsin announced in January 1992 that he would end themanufacture of all sea- and air- launched cruise missiles. In March 2000 it was reportedthat the Russian Air Force had tested a new cruise missile with a conventional warhead. Itwas said to be a Kh-555 missile, which was developed from the Kh-55, with a range of2000 - 3000 km. The relationship between the "Kh-555" and the Kh-101, with evidentlysimilar characteristics, is unclear.

The Kh-65, also known as the Kh-SD, is reportedly a smaller version of the Kh-101. It issaid to be shorter and lighter [by some 600-800kg], with a much shorter range of onlyseveral hundred kilometres. It probably uses the same homing system as the Kh-101, butmay a Kh-65S anti-ship version may have an active radar seeker. The fact of theexistence of this program was first disclosed in data sheets released at the 1992 MoscowAir Show, at which time it appeared to be a tactical derivative of the Kh-55 Granat [AS-15 Kent] strategic cruise missile. More recently, it is described as the short range tacticalversion of the Kh-101.

Based on the reported association between the Kh-55 and the Kh-65, it is probably thecase that the Kh-101 is a derivative of the previous Kh-55.


Designation Kh-101 Kh-65 / Kh-SD

Year

Type ground attack standoffcruise missile

Kh-65 ground attackKh-65S anti-ship

Wingspan

Length

Diameter

Launch weight 2,200-2,400kg 1,400-1,800kg

Max. speed Mach 0.75 Mach 0.75

Ceiling

Maximum range 3,000-5,000 km ? 300-500 km

Propulsion solid booster + cruise turbofan

Guidance TERCOM + TV Seeker

Kh-65 TERCOM + TVSeekerKh-65S TERCOM +active radar seeker

Warheadimpact- and directimpact-fuzed highexplosive, 1000 kg

Service

R-1 / SS-1 SCUNNERThe R-1 / SS-1 SCUNNER was the first Russian ballistic missile system, incorporatingV2 parts and Alcohol and LOX propellants. The SS-1A is essentially unrelated to the SS-1b or SS-1c SCUD, which use storable liquid [RFNA and Hydrazine] propellants. Theterm "scunner" is a Scottish & Northern dialect word for an annoying person or thing, anuisance, an object of disgust or loathing. The first Russian launch of a V-2 fromKapustin Yar was conducted on 18 October 1947. The first R-1 test flight from KapustinYar was conducted on 10 October 1948.

SpecificationsTotal Mass 12,798 kg.

Empty Mass 4,066 kg.

Payload 483 kg.

Core Diameter 1.7 m.

Span 3.6 m.

Total Length 17.0 m.

Engines 1. RD-100

Propellants Lox/Alcohol

Liftoff Thrust 27,690 kgf.

Thrust (vac) 31,314 kgf.

Isp 233 sec.

Burn time 63 sec.

Isp(sl) 206 sec.

Diameter 1.7 m.

Range 270 km.

Maximum altitude 77 km.

Time of flight 5 minutes.

Max velocity at burnout 1465 m/s.

Accuracy 8 km in range, 4 km laterally.

R-2 / SS-2 SIBLINGThe ethyl alcohol used in the V-2 and R-1 was replaced by methyl alcohol in the R-2.The first launch of the R-2 missile was conducted from Kapustin Yar on 30 September1949.

SpecificationsTotal Mass 19,632 kg.

Empty Mass 4,592 kg.

Payload 508 kg.

Core Diameter 1.7 m.

Span 3.6 m.

Total Length 21.0 m.

Engines 1. RD-101

Propellants Lox/Alcohol

Liftoff Thrust 37,210 kgf.

Thrust (vac) 41,208 kgf.

Isp 237 sec.

Isp(sl) 214 sec.

Burn time 85 sec.

Range 550 km.

Maximum altitude 171 km.

Time of flight 7.5 minutes.

Max velocity at burnout 2175 m/s.

Accuracy 8 km in range, 4 km laterally.

R-11 / SS-1B SCUD-AR-300 9K72 Elbrus / SS-1C SCUD-BThe Scud is a mobile, Russian-made, short-range, tactical ballistic surface-to-surface(hence the nomenclature abbreviation SS) missile system. The SCUD-series guidedmissiles are single-stage, short-range ballistic missiles using storable liquid propellants.The Scud is derived from the World War II-era German V-2 rocket. Unlike the FROGseries of unguided missiles, the SCUDs have movable fins. Warheads can be HE,chemical, or nuclear, and the missile, launched vertically from a small platform, has arange of 300 km. Unsophisticated gyroscopes guided the missile only during poweredflight - which lasts about 80 seconds. Once the rocket motor shut down, the entire missilewith the warhead attached coasted unguided to the target area. Consequently, Scuds hadnotoriously poor accuracy, and the farther they flew, the more inaccurate they became.SCUD missiles are found in SSM (SCUD) brigades at front/army level. The SCUD seriesof missiles gave the Soviet front and army commanders an integral nuclear weaponscapability. Non-nuclear variants of the SCUD missiles have been exported to bothWarsaw Pact and non-Warsaw Pact nations.

The SCUD-A is also known as SS-1b. The SCUD-B replaced the JS-3-mountedSCUD-A, which had been in service since the mid-1950s.

The longer range SCUD B, also known as SS-1c, can be distinguished by the onemeter greater length of the missile and the presence of two air bottles on the sideof the superstructure in place of the single bottle used for the "SCUD A" missile.The SCUD B used unsymmetrical dimethylhydrazine (UDMH), a more powerful(and toxic) fuel than the kerosene used on the SCUD A, which required an engineredesign. They were transported originally on a heavy-tracked vehicle based onthe JS heavy-tank chassis. This vehicle serves also as an erector and launcher forthe missiles. The SCUD-B was introduced on the JS-3 tracked chassis in 1961 andappeared on the MAZ-543 wheeled chassis in 1965. The "SCUD B" missile hasappeared on a new transporter-erector-launcher based on the MAZ-543 (8x8)truck. The introduction of this new powerful cross-country wheeled vehicle gavethis missile system greater road mobility, reduces the number of support vehiclesrequired, and still preserves a great choice in selecting off-road firing positions.The same basic chassis also has been used for the transporter-erector-launcher forthe "SCALEBOARD" surface-to-surface guided missile. In the early 1980s, theSCUD-B was replaced by the SS-23, which has greatly improved range (500 km),increased accuracy, and reduced reaction and refire times.

The SCUD-C SS-1d achieved an initial operational capability with Soviet forcesaround 1965. It had a longer range, though lower accuracy, than the SCUD B, andwas deployed in smaller numbers. As of the late 1990s some remained in servicein Russian ground forces.

The SCUD-D SS-1e featured an improved guidance system, possiblyincorporating active radar terminal homing, and a wider choice of warheads than

its predecessors. This missile has a range of about 700 km. Initially operational inthe 1980s, it may not have been deployed by former Soviet ground forces.

At launch, a basic Scud contains about 3,500 kilograms (7,700 pounds) of IRFNA andabout 1,000 kilograms (2,200 pounds) of fuel. Most of the IRFNA and fuel is used withinthe first 80 seconds of flight when the missile is gaining enough speed to reach its target.When this speed is reached, the Scud is designed to shut off its engine by shutting off thepropellant tanks (a fuel tank and an oxidizer tank). The unused propellants—roughly 150kilograms (330 pounds) of RFNA and 50 kilograms (110 pounds) of fuel—remain onboard for the remainder of the flight.In the early 1970s, the Soviet Army sought a replacement for the 9K72 Elbrus (SS-1C`Scud B') system, which had a very slow reaction time [around 90 minutes to prepare andfire] and its poor accuracy when using conventional warheads. The replacement system,codename 9K714 Oka [SS-23 Spider], was developed by KB Mashinostroyenia (MachineIndustry Design Bureau) in Kolomna. This system was phased out in compliance with theINF Treaty in the late 1980s. Russia’s TBM inventory is limited to thousands of SS-1c/Scud B and SS-21/Scarab SRBMs as a result of the Intermediate Nuclear Force (INF)Treaty, which required the elimination of the FSU’s extensive stocks of MRBMs.

A second SCUD-followon effort began in the form of the SS-26, which apparentlyentered service by 1999. The SS-26 SRBM is expected to be both a replacement for theSS-1c/Scud B and an export. By the early 1990s, the `Scud' system was unquestionablyobsolete and many of the 9P117 launcher vehicles were retired due to age.

SpecificationsDIA SS-1b SS-1c SS-1d SS-1e

NATO Scud-A Scud-B Scud-C Scud-D

Bilateral

Service R-11 / R-175 R-300

OKB/Industry 8K14

Design Bureau Makeyev OKB MakeyevOKB

MakeyevOKB

Makeyev OKB

Approved ... ... ... ...

Years of R&D ... ... ... ...


... ... ... ...

First Flight Test ... ... ... ...

IOC ... ... ... ...

Deployment 1957 1965 1965 1980s

Date

Withdrawn 1978

Type of Warhead nuclearConventionalunitary blastChemicalwarhead

HE, CHEM(thickenedVX)

Conventionalunitary blastfuel-airexplosive40 runway-penetrator sub-munitions100 11-lb(5-kg) anti-personnelbomblets

Warheads 1 1 1 1

Yield ... 5-80 kiloton ... ...

Payload (t) 770-950 kg

Total length (m) 10.25 m 11.25 m 11.25 m 11.25 m


Missile Diameter(m)

0.88 m 0.88 m 0.88 m 0.88 m

Launch Weight(t)

6,300 kg

Fuel Weight (t)

Range(km) 130 km 300 km 575-600km 700 km



4,000 m 900 m 900 m 50 m

Reaction time 60 min

EngineDesignation

... ... ... ...

Design Bureau ... ... ... ...

EngineConfiguration

One engine One engine One engine One engine

Propellants LiquidStorable

LiquidStorable

LiquidStorable

LiquidStorable

Fuel Kerosene UDMH UDMH UDMH

Oxidizer nitric acid RFNA(Russian SG-02 Tonka 250)

RFNA(RussianSG-02Tonka 250)

RFNA(Russian SG-02 Tonka 250)

Main EnginesBurning time(sec.)

... ... ... ...

Main enginesThrust SeaLevel/Vacuum(Tonnes)

... ... ... ...

Main EnginesSpecific ImpulseSeaLevel/Vacuum(sec.)

... ... ... ...

SCUD-A

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SCUD-B/C

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R-5 / SS-3 SHYSTERThe R-5M missile the [western designation SS-3 Shyster], the first Soviet missile with anuclear delivery capacity, was a single-stage, medium-range, liquid propellant, road-transportable, ballistic missile. With a maximum range of 1200 km – sufficient enough toreach strategic targets in Europe – it was also considered to be the first Soviet strategicmissile.

The missile R-5M was based on the R-5 missile developed by by S.P. Korolev from theDepartment of the Research Institute of the Special Design Bureau. (OKB-NII) in theearly 50's. This predecessor was a single-stage missile with a separable reentry vehicle.According to Western assessments, the initial guidance system for the SS-3 was radio-inertial, which was retrofitted with an all-inertial system as more reliable componentsbecame available. The R-5M missile differed from its predecessor R-5 in that to increaseits reliability an auto-stabilizing command structure was installed. With a larger payload(1300 against 1000 kg) and dry weight (4390 against 4030 kg), the launching weight ofthe R-5M was more than twice that of the R-1 (28,610 against 13,430 kg). The enhanceddesign and efficiency in combination with an increase of the specific engine thrust from206 to 219 seconds allowed an increase in the maximum range almost five-fold relativeto the R-1. To maintain an acceptable target accuracy at this increased range, the R-5missile used a combined guidance/control system with autonomous inertial control pluslateral radio-correction. In-flight control of the missile was maintained with fouraerodynamic fins located on the aft bay, and four jet vanes located on the perimeter of thesingle combustion chamber of the engine. The accuracy of the R-5 was 1.5 kmdownrange and 1.25 km cross-range from the aim point, and exceeded substantially theaccuracy of the R-1 and R-2 missiles.

On 10 April 1954 the Soviet Government approved the development of the R-5M. Theflight tests of the R-5M were conducted at Kapustin Yar from January 1955 throughFebruary 1956. The flight test of the R-5M on 02 February 1956 represented the first fullscale testing of a nuclear missile, during which a nuclear warhead with a yield of 300 KTwas successfully detonated. The R&D flight test program was assessed by Westernintelligence to have begun in 1955, with initial operational capability reached in late1956.

After reaching its IOC the R-5M missile received the index number 8K51 and wasintroduced into the Strategic Rocket Forces on 02 June1956. Between 1956 and 1957 atotal of 48 missiles were deployed, primarily at sites close to the western borders of theSoviet Union. A minimum operational SS-3 field site required only a large presurveyedclearing with soil stabilization or possibly a poured or prefabricated concrete apron. TheSS-3 is launched from the vertical position. Reaction time is approximately five hoursfrom the normal readiness condition. The allowable hold time in the most readyprelaunch condition (reaction time equal 15 min) is about one hour. In 1959 they wereput on alert for the first time, and it remained in service until 1967. No further

deployment was carried out due to the development of the more effective R-12 missilethat subsequently replaced the R-5M Missile.

SpecificationsDIA SS-3m

NATO Shyster

Bilateral R-5

Service R-5M

OKB/Industry 8K51 (8A62M)

Design Bureau (OKB-I), NII-88, (Acad. S. P.Korolev)

Approved 4/10/1954

Years of R&D



IOC 1956


First public display November 1957

Phase-out completed 1967


Warheads 1

Yield (Mt) 1x0.08 - 0.3 MT.

Payload (t) 1.350


Missile Diameter (m) 1,652

Diameter of Stabilizers (m) 3.452



Dry weight (t) 4,39

Range(km) 1200

CEP (m) (Russian Sources) 1500 m downrange and 1250 mcross range


Number of Stages 1

Booster guidance system Autonomous/inertial plus radio-control

Engine Designation RD-103M, 8D52

Design Bureau Acad. V. P. Glushko OKB-456

Years of R & D 1952-53

Propellant Liquid

Fuel 92% Ethyl Alcohol/water solution

Oxidizer Liquid Oxygen

Burning time (sec.) 115.4

Thrust Sea Level/Vacuum(Tonnes)

43.86 - 44 / 50.9892 - 51


Sea Level/Vacuum

219 -220 / 243 -248

Basing Mode Ground-Based

Launching Technique Hot Launch

Deployed boosters 0

Test Boosters

Warheads Deployed 0

Deployment Sites

Training Launchers

R-12 / SS-4 SANDALThe R-12 was the first Soviet strategic missile using storable propellants and acompletely autonomous inertial guidance system. With its capability to deliver amegaton-class nuclear warhead the rocket provided a capability to attack strategic targetsat medium ranges. This system constituted the bulk of the Soviet offensive missile threatto Western Europe. It was deployed at both soft launch pads and hard silos.

The Sandal is a single-stage rocket with a separable single reentry vehicle. In theintegrated fuel tanks the oxidizer was put ahead of the fuel tank, separated by anintermediate plate. During flight this allowed the oxidizer from the lower unit to be spentfirst thus improving in-flight stabilization. The propulsion system consists of four liquidpropellant rocket motors with a common turbopump unit. The flight control was carriedout with the help of four carbon jet vanes, located in the nozzles of the rocket motors.The autonomous guidance and control system used center of mass normal and lateralstabilization devices, a velocity control system and an computer-assisted automatic rangecontrol system.

Its development was accepted on 13 August 1955 by the Ministerial Council and carriedout by Yangel's OKB-586. The first tests were conducted at the test site in Kapustin Yarbetween 22 June 1957 through December 1958. The R-12 missile was introduced into theinventory on 04 March 1959 according to Russian sources, though Western intelligencebelieved that an initial operational capability was reached in late 1958.

Efforts to develop a railway based version of the R-12 missile were suspended.

The R-12 missile was surface-launched. However in September 1959 a series ofexperimental silo launches was conducted and subsequently in May 1960 thedevelopment of a new R-12 missile designated as R-12 U was begun. The R-12U wasdesigned to be used with both soft surface launchers and hardened silos. The silo-launchcomplex of the R-12U missile comprised four launchers and was designated as "Dvina."The testing phase of the missile and the launch complex lasted from December 1961through December, 1963.

The first public display of this system was in November 1960, and they were deployed toCuba in the Fall of 1962.

The first five regiments with surface-based R-12 missiles were put on alert on 15-16 May1960, while the first regiment of silo-based missiles was placed on alert on 01 January1963. Reaction time was assessed by the West at one to three hours in the normal soft sitereadiness condition, and five to fifteen minutes in the normal hard site readinesscondition. The allowable hold time in a highly alert condition (reaction time equals threeto five minutes ) is long--many hours for soft sites, and days for hard sites.

The R-12 and R-12U missiles reached their maximum operational launcher inventory of608 in 1964-1966. Some soft-site phase-out began in 1968, with some hard-site phase-outbeginning in 1972. In 1978 their phase out and replacement with mobile ground-launchedSS-20 "Pioneer" missiles began.

The Intermediate-Range and Shorter-Range Nuclear Forces [INF] Treaty was signed on08 December 1987 and entered into force on 01 June 1988. The fundamental purpose ofthe INF Treaty was to eliminate and ban US and former USSR (FSU) ground-launchedballistic and cruise missiles, as well as associated support equipment, with rangesbetween 500 and 5500 kilometers. SS-4 and SS-5 missiles and components wereeliminated at Lesnaya. The last of 149 Soviet SS-4 missiles was eliminated at theLesnaya Missile Elimination Facility on 22 May 1990.


NATO Sandal Sandal

Bilateral R-12 R-12U

Service R-12 R-12U (Dvina)

OKB/Industry 8K63 8K63U (Acad. M. K. Yangel)

Design Bureau OKB-586 OKB-586

Approved 8/13/1955 5/30/1960

Years of R&D


1957-1959 1961-1963

First Flight Test 6/22/57 12/30/1961

IOC 1959 1963



Warheads 1 1

Yield (Mt) 1-1.3 / 2-2.3 1-1.3 / 2-2.3

Payload (t) 1.3 -1.4 /1.63

1.3 -1.4 / 1.63

Total length (m) 22.1 - 22.77 22.1 - 22.77

Total length w/o 18.4 -18.6 18.6

Warhead (m)

Missile Diameter(m)

1.65 1.65

Launch Weight (t) 41.7 - 42.2 41.7 - 42.2

Fuel Weight (t) 37 37

Range (km) 2,080(2,000)

2,080 (1,800 - 2,000)


5,000 5,000

CEP (m) WesternSources

1500-3000 1500-3000

Basing mode Groundbased

Ground and silo based

Number of Stages 1Booster guidance system Inertial, autonomousEngine Designation RD-214Design Bureau Glushko, OKB-456Years of R & D 1955-1957Propellants Liquid StorableFuel Tm-185

92%hydrocarbon/keroseneOxidizer AK-27 I =73% HNO3 + 27%N204

(NTO), Nitrogen Tetroxideconcentrated in Nitric Acid

Burning time (sec.) 140Thrust Sea Level/Vacuum (Tonnes) 64.75 / 74.44 operational 72.00Specific Impulse Sea Level/Vacuum(sec.)

230 / 264

Canister length (m) N/ACanister Diameter (m) N/ALaunching Mode Hot LaunchedDeployed boosters 0Test BoostersWarheads Deployed 0Deployment Sites INF Treaty dataTraining LaunchersSpace Booster Variant SL-7 / B-1 Interkosmos booster

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R-14 / SS-5 SKEANThe R-14/SS-5 was a single-stage, storable liquid-propellant, intermediate range ballisticmissile. The design of the R-14 missile draw heavily on the previously developed P-12missile. As with the R-12, the Skean missile was a single stage missile with integral fueltanks though it was larger and twice the maximum range. According to Western estimatesit was capable of delivering a 3,500 lb reentry vehicle containing a nuclear weapon to amaximum operational range of 2,200 nm, and using an inertial guidance system with wasassessed as having a CEP of approximately 0.5 nm.

In comparison to the R-12 the increase of the propellant volume was reached through anincrease of the diameter of fuel tanks. Fabrication of tanks with aluminum panelsprocessed by a method of chemical contouring was used for the first time. The propulsionsystem of the R-14 consists of two identical blocks, each with a two-chamber combustionengine, a turbopump unit, gas generator and automatic control system, as well as a fourchambered control motor. The use of hypergolic [self igniting] asymmetricaldimethylhydrazine allowed an increased specific impulse. For the first time a gasgenerator [instead of hydrogen peroxide] was used to power the main propellantcomponents. The flight control still relied on jet vanes. Unlike the previous single-stagerockets, the R-14 used an efficient system of draining the propellant tanks to reducerequired propellant mass.

The R-14 marked the first use of a gyro-stabilized platform as part of the autonomousinertial guidance system, allowing fewer instrumental errors and improving accuracy.The R-14 also mounted three solid-propellant retrorockets to prevent accidental collisionof the booster with the nose cone after separation. Despite of its substantial longer range,the R-14 demonstrated the same accuracy as the R-12, though given its heavier payloadits nose cone was blunted. According to Western intelligence the Mod 1 reentry vehiclehad a ballistic coefficient of 1300 lb per sq ft.

The development of the R-14 was authorized on 02 July 1958. The authorizationprovided for the construction of a missile with an approximate range of 4,000 km,surpassing the R-12 by 2,000 km. The designer was M.K. Yangel of KB Yuzhnoye(OKB-586). The preliminary design was completed in December 1958. Flight tests of theR-14 began in July 1960 [Western sources suggest a first flight in June 1960] and werefinished between December 1960 and February 1961. On 24 April 1961 deployment ofthe R-14 missile began. According to Western intelligence the initial operationalcapability with the Mod 1 reentry vehicle and soft sites was achieved in late 1961.

In May I960 the development of the R-14U missile for silo and surface launchers began.The first flight test of the silo-launched R-14U was carried out on 12 January 1962, thesurface-launched version was first tested on 11 February 1962. Both were subsequentlyintroduced into the Strategic Missile Forces. The first regiment of surface-based R-14swas put on alert on 01 January 1962. According to Western intelligence an initial

operational capability with hard sites was achieved in early 1963, and the initialoperational capability with the Mod 2 reentry vehicle was achieved in mid-1963.

The SS-5 was deployed at both soft and hard launch sites. Soft-site reaction time in thenormal readiness condition is one to three hours. Hard-site reaction time in the normalreadiness condition is five to fifteen minutes. Allowable hold time (reaction time equalsthree to five minutes) was many hours for soft sites and many days for hard sites.Maximum operational launcher deployment was reached in 1964. Between 1965 and1969 the deployment of the R-14 and R-14U reached its peak with 97 launchers. Somephaseout of soft sites beginning in 1969 and some phase-out of hard sites beginning in1971. In the period between 1978 and 1983 they were replaced by SS-20 Pioneermissiles, and in 1984 they were totally withdrawn from service.

The Intermediate-Range and Shorter-Range Nuclear Forces [INF] Treaty was signed on08 December 1987 and entered into force on 01 June 1988. The fundamental purpose ofthe INF Treaty was to eliminate and ban US and former USSR (FSU) ground-launchedballistic and cruise missiles, as well as associated support equipment, with rangesbetween 500 and 5500 kilometers. SS-4 and SS-5 missiles and components wereeliminated at Lesnaya. Beginning in 1988 the six remaining non-deployed missiles weredismantled in compliance with the INF Treaty. The sixth and final SS-5 missile waseliminated at the Lesnaya Missile Elimination Facility on 09 August 1989.


NATO Skean Skean

Bilateral R-14 R-14U

Service R-14 R-14U (Chusovaya)

OKB/Industry 8K65 8K65U

Design Bureau OKB-586 OKB-586 (Acad. M. K.Yangel)

Approved 7/2/1958 5/30/1960

Years of R&D 1958 - 1960 1960 -1962


1960 -1961 1961 -1962

First Flight Test 7/6/1960 2/11/62 (1/12/1962)

IOC 1962 1962



Warheads 1 1

Yield (Mt) 1.0 or 2.0 -2.3 1 x 2.3

Payload (t) 1.300 -1.500 or2.155

1.300 -1.500 or 2.155

Total length (m) 24.3 - 24.4 24.3 -24.4

Total length w/o

Warhead (m)

21.62 21.62

Missile Diameter(m)

2.4 2.4

Launch Weight (t) 86.3 - 87 86.3

Fuel Weight (t) 79.2 79.2

Range (km) 4500 or 3200 -3700

4500 -3700

CEP (m)

(Russian Sources)

1250 -1900 1250

CEP (m)

(WesternSources)

900-1900 900-1900

Basing mode Ground Based Ground and Silo BasedNumber of Stages 1Booster guidance system Inertial, autonomousEngine Designation RD-216m (8D514,M)Configuration Cluster of two enginesDesign Bureau Acad. V. P. Glushko OKB-456Years R & D 1958-1960Propellants Liquid StorableFuel UDMHOxidizer AK-27 I = IRFNA =73% HN03 + 27%

N204 (NTO) in N02Burning time (sec.) 130 -131Thrust Sea Level/Vacuum (Tonnes) 151.4991/171.075 -177.9Total thrustSpecific Impulse Sea Level/Vacuum(sec.)

246-248 / 290-291.3

Canister length (m) N/A

Canister length w/o front meters N/A

Canister diameter (m) N/AHardnessLaunching Technique Hot launchedDeployed boosters 0Test BoostersWarheads Deployed 0Deployment Sites INF Treaty InformationTraining LaunchersSpace Booster Variant SL-8/C-1 Kosmos, Kosmos-3M


First flight test June 1960

R&D flight testing probably completed February 15, 1961

Initial operational capability with Mod 1 reentry vehicle Late 1961

Hard site tests began Mid 1962

New series of flight tests began July 12, 1962

Deployment to Cuba began 1962

Initial operational capability with hard sites Early 1963

Initial operational capability with Mod 2 reentry vehicles Mid 1963

Maximum operational launcher inventory 1964

First public display. November 7, 1964

Phase-out of soft sites began 1969

Phase-out of hard sites began 1971



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TR-1SS-12 SCALEBOARDSS-12M SCALEBOARD BSS-22The SS-12 SCALEBOARD uses the same MAZ-543 (8x 8) chassis as the SCUD-B. Theprimary recognition difference is the environmental protective container that completelyencloses the SCALEBOARD missile. The missile is a liquid-fuel, single-stage systemsimilar to the SCUD, but with greater range (900 km), accuracy, and size of warhead.Like the SCUD, the SCALEBOARD is designed to be fired from a pre-sited position,then moved to another prearranged position. The MAZ-543 has centralized tire pressurecontrol.

The SCALEBOARD is a front and theater-level weapon system that gives the Sovietcommander a nuclear capability. The SCALEBOARD appeared deployed only withSoviet forces. The mid-range missile can be stationed in the western part of the USSRand still be able to hit important targets in Central Europe.

The SS-12 SCALEBOARD, in service since the mid-1960s, was replaced beginning in1979 with a new missile that had the same range (900 km) with improved accuracy.Initially considered to be a new missile, designated the SS-22, the SS-12MSCALEBOARD B [also known as the SS-12B and the SS-12 mod 2] was subsequentlyassessed as an improved version of the earlier Scaleboard. By the early 1980s the Sovietswere replacing older shorter-range Scaleboard missiles with SS-22s, and were developingthe new SS-23 as a follow-on to the Scud missiles. The SS-22 missile had the range tocover a substantial portion of NATO Europe even from its deployment areas within theSoviet Union.

The Intermediate-Range and Shorter-Range Nuclear Forces [INF] Treaty was signed on08 December 1987 and entered into force on 01 June 1988. The fundamental purpose ofthe INF Treaty was to eliminate and ban US and former USSR (FSU) ground-launchedballistic and cruise missiles, as well as associated support equipment, with rangesbetween 500 and 5500 kilometers. SS-12 and SS-23 transporter-erector-launcher (TEL)vehicles were eliminated at Stan'kovo. The first Soviet SS-12 missile was eliminated atthe Saryozek Missile Elimination Facility on 01 August l988. The last of 718 Soviet SS-12 missiles was eliminated at the Saryozek Missile Elimination Facility on 25 July 1989.

In February 1997 a top Cuban military defector, Alvaro Prendez, alleged that Cuba wasdeveloping biological weapons were to be delivered by five Soviet-made SS-22 missilesthat were deployed near the central city of Santa Clara. Prendez and other defectors hadheard rumors that the missiles were shipped from Russia to Cuba as late as 1991. Cuba isnot known to have any SS-22 missiles, and these claims appear unfounded.

SpecificationsUSA Code Name SS-12

Nato Code Name: Scaleboard

Russian Designation: 9M76

ContractorsNadiradze OKB (design bureau)Votkinsk (missile)Barricade factory, Volgograd, Russia, (TEL)

Stages: 1

Fuel: Liquid

Inservice: 1969

weight 9,700 kg

length 12.4 m

diameter 1.01 m

Range: 800 km - Mod 1900 Km - Mod 2

Guidance inertial

Circular Error Probable(CEP)

0.4 nm / 0.75 km - Mod 10.2 nm / 0.37 km - Mod 2

Warhead 500-kiloton nuclear

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RT-15 / RT-2PSS-14 SCAMP / SCAPEGOATThe RT-15 / SS-14 medium-range ballistic missile was a two-stage, tandem, solid-propellant missile capable of delivering a nominal reentry vehicle of the 1,200-lb class toa range of about 1,600 nm. Missile gross weight was about 35,800 lb. that was derivedfrom the two upper stages of the SS-13 ICBM. It had an inertial guidance system that wasestimated by Western intelligence to have a CEP (at 1500 nm) of about 0.5 nm.

The RT-15 [designated the RT-2P according to some sources] was the first Sovietattempt to develop a mobile intermediate range missile. The development of the RT-15missile was approved on 04 April 1961 and was included in the program of developingthe RT-2 / SS-13 missile on whose second and third stages it was based. The missile wasintended to be sea and ground launched and had a maximum range of 2000-2500 kms.The designer of the ground-launched RT-15 (8K96) was P.A. Tyurin from KB Arsenal.

Two-stage solid fuel missile was deployed on a transport-launching rack, which wasplaced on the mobile launcher. The launcher was built on the basis of a heavy tank. TheSS-14 transporter-erector-launcher was first observed in May 1965, and designatedSCAMP by NATO. The SS-14 system was first observed in a Moscow parade inNovember 1967. the missile inside the container was later seen separately and codenamed SCAPEGOAT in 1968. Subsequent analysis demonstated that the SCAPEGOATmissile was carried by the SCAMP launcher.

In 1968 it was recommended for series production and experimental operation afterpassing successful tests. Nevertheless the Ministry of Defense refused to accept thedeployment of this missile and the program was completely stopped in 1970 after 10experimental launches were conducted in the years 1969 and 1970. The last flight testobserved by Western intelligence was in March 1970, and the program was assumed byWestern intelligence to have been cancelled. Less than 30 SS-14s were deployed, all informer Soviet Asia.

No permanent facilities other than a benchmark would be necessary at an SS-14 launchsite. Preparation of such a site would therefore be minimal. Access to launch sites wouldbe by means of semi-improved or unimproved roads in extremely rough terrain orpossibly no roads at all in fairly smooth terrain. Reaction time in the normal readinesscondition (condition after arrival at site) would be 20 to 30 minutes. Hold time at peakreadiness (reaction time of two to ten minutes) would be about a day.

SpecificationsDIA SS-X-14 (SS-14)

NATO* Scamp/ Scapegoat

Bilateral

Service RT-15

OKB/Industry 8K96

Design Bureau KB Arsenal (Tyurin-OKB) TsKB-7

Approved 4/4/1961



First Flight Test 9/__/1965

IOC Not operational 3/__/1970

Deployment Date Not deployed 3/__/1970


Warheads 1

Yield (Mt) 1

Payload (t) 0.535





Range (km) 2500-2,950

CEP (m) (Russian Sources) 0.9 km

CEP (m) (Western* Sources) 600-2000

Number of Stages 2

Canister length (m) 12,7

Canister length w/o front meters(m)

Canister diameter (m) 2,1


Length (m) 4.74 6.77Body diameter (m) 1.49 1.01Fueled weight (t)Dry weight (t)Solid Motor Designation 15D27 15D2 or 15D92Design BureauR & D YearsPropellants Solid SolidFuel N/A N/AOxidizer N/A N/ABurning time (sec.) 60 45Thrust Sea Level/Vacuum(Tonnes)


42

237/263

22

271

Basing Mode Ground MobileHardnessLaunching Technique HotDeployed boosters 0Test BoostersWarheads Deployed 0Deployment SitesTraining LaunchersSpace Booster Variant N/A

RT-25 MRBMThe RT-25 was intended to be based on the first and third stages of the RT-2. Itsmaximum range was supposed to be 4000-4500 kms. The governmental order issued on04 April1961 providing for the development missiles based on solid fuel led to plans todevelop this missile. The designated design bureau was Korolev's OKB-1, and the projectreceived the industrial index 8K98 But its development never got beyond the initial stageas the Ministry of Defense suspended further development.

Specifications

DIA

NATO

Bilateral

Service RT-25

OKB/Industry 8K97

Design Bureau OKB-1/Mashinosteroeniya

Approved 4/4/1961



First Flight Test No flight tests conducted

IOC Not operational



Warheads 1

Yield (Mt)

Payload (t)

Total length (m) 15-16


Missile Diameter (m) 2-1.84

Launch Weight (t) 40-42

Range (km) 4000-5000

CEP (m) ?

Number of Stages 2

Canister length (m)

Canister length w/o

front meters (m)



1st stage 2nd stage

Length (m) 8.7 3.83

Body diameter (m) 2.0-1.84 1.01


Dry weight (t)


15D23 15D25

Design Bureau

Years R & D

Propellants Solid motor Solid motor

Fuel N/A N/A

Oxidizer N/A N/A

Burning time (sec.) 75

Thrust SeaLevel/Vacuum(Tonnes)

91


Basing Mode mobile, silo concept

Hardness

Launching Technique Hot launch

Deployed boosters 0

Test Boosters

Warheads Deployed 0

Deployment Sites

Training Launchers

Space Booster Variant N/A

RT-21M / SS-20 SABERThe RT-21M / SS-20 is a solid-fuel, two-stage, theater-based ballistic missile based onthe first and second stages of the SS-16. The SS-20 was probably intended to replace oraugment the SS-4s and SS-5s deployed in the Soviet Eastern European theater, thusproviding approximately three times the number of warheads of the older force.

The two-stage solid-fuel "Pioneer" with single-nozzle sustainers is derived from the firstand second stages of the SS-16 ICBM. The cylindrical casings of the sustainer stages aremade from composite materials. The solid propellant charge is rigidly fastened to thesustainer body.

The guidance/control system with its onboard digital computer and a gyro-stabilizedplatform with floating gyros enables the missile to be horizontally positioned and ensuresoptimal target accuracy. Flight control during the first stage flight is achieved throughaerodynamic and jet vanes. During the second stage low temperature gas is injected intothe diverging part of the sustainer nozzle.

The missile was deployed in a transport-launch canister, which was installed on a road-mobile launcher. The launcher was equipped with systems needed to ensure constantcombat readiness, preparation and firing. The missile could be launched from a slidingroof garage at regimental bases or from field deployed sites. Before ignition the launcherwas suspended on a hydraulic support, then the container was set upright in a verticalposition. Before ignition of the first sustainer stage the missile was popped out of thecontainer with the help of a solid propellant gas generator the missile and the first stagesustainer was started. The control of launch was conducted from a mobile control center.The SS-20 also has the capability to be reloaded and refired.

The developer of a complex was the Moscow institute of Thermal Technology which washeaded by A.D. Nadiradzye. The flight-design tests were conducted from 21 September1975 through 09 January 1976 at the Kapustin Yar test site. Deployment of the SS-20began on 11 March 1976, and the first regiment equipped with the Pioneer missiles wasset under airborne alert on 30 August 1976.

According to western data, the rocket was tested in three different Mods. The SS-20Mod1&3 carried a single warhead whereas the SS-20 Mod2 carried a MIRV warhead.The Mod2 equipped with three warheads with a yield of 150 KT each became thestandard missile. In this version the warheads are placed on a post-boost vehicle.

On 10 August 1979 the tests of the modernized "Pioneer"-UTTKh (15Zh53) began on theKapustin Yar test site. They continued through 14 August 1980, and on 17 December1980 the missile designated as SS-20 Mod3 was deployed. This variant had the samepropulsion system as earlier versions, but it due to upgrading of a command structure andinstrumentation-service unit it was possible to improve accuracy (CEP) from 550 to 450

meters, to increase maximum range by 10 %, and to increase the area covered by thewarheads.

According to some Western assessments, with a new single, lightweight warhead, or withthe addition of a third stage (or both), the SS-20 has the potential to be converted to anICBM with limited capability against the continental United States.

Between 1978 throught 1986 a total of 441 launch complexes for the "Pioneer" missileswere deployed. The SS-20 was one of the missile systems eliminated under the terms ofthe INF Treaty, which took effect in June 1988. Prior to the INF drawdown, the SS-20force comprised 48 bases that housed the regularly deployed force of 405 missiles andlaunchers.

The Intermediate-Range and Shorter-Range Nuclear Forces [INF] Treaty was signed on08 December 1987 and entered into force on 01 June 1988. The fundamental purpose ofthe INF Treaty was to eliminate and ban US and former USSR (FSU) ground-launchedballistic and cruise missiles, as well as associated support equipment, with rangesbetween 500 and 5500 kilometers. The first Soviet SS-20 missile and canister wereeliminated under INF Treaty at the Kapustin Yar Missile Test Complex on 22 July 1988.The first Soviet SS-20 missiles were eliminated by launching at the Chita and Kanskmissile sites on 25 August 1988. The last of 654 SS-20 missiles was eliminated at theKapustin Yar Missile Test Complex on 12 May l991. And the last of 499 SS-20 launcherswas eliminated at the Sarny Launcher Elimination Facility on 28 May 1991.


DIA SS-20 SS-20 SS-20/SS-X-28

NATO Saber Saber Saber

Bilateral RSD-10 RSD-10 RSD-10

Service RSD-10/Pioneer

RSD-10/Pioneer-UTTX

RSD-10/Pioneer-3

OKB/Industry 15Zh45 (Temp-2C)

15Zh53 (Temp-2C)

15Zh53 (Temp-2C)

DesignBureau

MoscowInstitute ofThermalTechnology



Approved 3/4/1968 7/19/1977 8/14/1980

Years of R&D


1974-76 1974-1976 1979-1980

First FlightTest

9/21/74 9/21/74 8/10/1979

IOC 1976 1976 1980

DeploymentDate

3/11/1976 3/11/1976 12/17/1980

Type ofWarhead

Single MIRV Single or MIRV

Warheads 1 3 1/3

Yield (Mt) 1.0 0.15 ?

Payload (t) 1.5-1.74 1.5-1.74 ?

Total length(m)

16.49 16.5 17.0

Total lengthw/o warhead(m)

14.9 14.9 14.9

MissileDiameter (m)

1.79 1.79 1.79

LaunchWeight (t)

37 37 37

Fuel Weight(t)

Range (km) 600-5000 600-5000 600-5500/7500

CEP (m)

RussianSources

0.550 0.550 0.450

CEP (m)

WesternSources

150-450 400-430` ?

Number of Stages 2


Canister length w/o front (m)



1st stage 2nd stage 2nd Stage

Length (m) 8.58 4.4-4.6 4.4-4.6


Fueled weight (t) 26.7 8.63 8.63

Dry weight (t)


Design Bureau

Years R & D

Propellants Solid Solid Solid

Fuel N/A N/A N/A

Oxidizer N/A N/A N/A

Burning time (sec.) 63

Thrust SeaLevel/Vacuum(Tonnes)

Special Impulse(sec.)

Basing Mode Ground mobile

Hardness

Launching Technique Mortar Launch

Deployed boosters 0

Test Boosters

Warheads Deployed 0

Deployment Sites INF Treaty data

Training Launchers

Space Booster Variant N/A

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SS-23 SPIDERIn the early 1970s, the Soviet Army sought a replacement for the 9K72 Elbrus (SS-1C`Scud B') system, which had a very slow reaction time [around 90 minutes to prepare andfire] and its poor accuracy when using conventional warheads. The replacement system,codename 9K714 Oka, was developed by KB Mashinostroyenia (Machine IndustryDesign Bureau) in Kolomna. The new 9K714 system featured a reaction time of under 30minutes and used the low-maintenance solid-fuel 9M714 missile. The 300 km range ofthe R-300 (`Scud') was surpassed by the 400 km range of the 9M714/R-400.

In the early 1970s the Warsaw Pact had only a limited ability to strike North AtlanticTreaty Organization (NATO) air bases in Europe. However, by the mid-1980s Sovietforces could strike NATO airfields in all types of weather using tactical ballistic missiles(TBMS) such as the SS-21 and the SS-23. NATO had only limited defense against theseweapons, some of which were accurate to within 100 meters. The SS-23 has a range of310 miles, with speeds of 6,800 miles per hour or Mach 9 that can access most locationsin a given theater of war.

The Intermediate-Range and Shorter-Range Nuclear Forces [INF] Treaty was signed on08 December 1987 and entered into force on 01 June 1988. The fundamental purpose ofthe INF Treaty was to eliminate and ban US and former USSR (FSU) ground-launchedballistic and cruise missiles, as well as associated support equipment, with rangesbetween 500 and 5500 kilometers. SS-12 and SS-23 transporter-erector-launcher (TEL)vehicles were eliminated at Stan'kovo.

On 21 July 1988, US Army Colonel Edward H. Cabaniss led an American INF inspectionteam to Petropavlovsk in Kazakhstan, approximately 2,000 kilometers east of Moscow.Petropavlovsk was the location of the V.I. Lenin Heavy Machine Building Plant, wherethe American team conducted a closeout inspection of the former SS-23 missile launcherproduction facility. The last of 239 SS-23 missiles was destroyed at the Saryozek MissileElimination Facility on 27 October 1989. The final SS-23 launcher was eliminated thesame day at the Stan'kovo Elimination Facility.The Soviet Union had negotiated separate diplomatic agreements with bothCzechoslovakia and the German Democratic Republic, where Soviet INF missile unitshad been based. In the case of the INF Treaty, the Soviet-declared data was not agreed toby each side, and it was not included in the Treaty. Later it turned out that the Soviets hadfalsified some of their INF data. In April of 1990 the Soviets admitted that they hadcovertly provided SS-23 missiles banned by the INF Treaty to three East Europeannations. At least 120 Soviet-controlled SS-23s covertly deployed in Eastern Europe,which the US INF negotiator termed "deceit and mendacity" during the negotiations. InFebruary 1990 President Bush sent Congress a report stating that the Soviet SS-23deployment did constitute "bad faith." But he didn't say whether it was a violation of theINF Treaty. The State Department was embarrassed by the discovery later that someSoviet-declared INF data was false, because the State Department had repeatedlyvouched for its accuracy in public when advocating the Treaty.

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Iskander / SS-26The road-mobile SS-X-26 is the second attempt to replace the `Scud', since the firstattempt, the Oka SS-23 SPIDER, was eliminated under the Intermediate Nuclear Forces(INF) Treaty. The operational requirements for the SS-26 are probably similar to those ofthe original SS-23. One of the major questions concerning the program is the missile'srange, which is almost certainly less than the 500 km range limit established by the INFTreaty. The SS-26 may include a longer range (greater than 400 km) variant for theRussian forces, and a shorter range (less than 300 km) variant for export.The new TEL is probably based on the new BAZ-6909 family of trucks, first publiclydisplayed at a commercial transport show in Moscow in August 1995. Two missiles arecarried on each launcher, though the delay between firing each round is unclear. The newTEL is apparently based on the the 9P71 Oka TEL, though the new SS- X-26 TEL hasbeen designed with the INF Treaty in mind, with several external changes that clearlydifferentiate the two vehicles to prevent treaty compliance problems. The nose of thevehicle has been extended forward, the chassis lengthened, and the access doorarrangement has been changes. The tactical parameters of the two vehicles are probablysimilar.In 1996 Russian television reports depicted the first launch of the SS-X-26, which is adirect evolution of the SS-23 Oka. It appears probable that new features will beincorporated into the design. The SS-X-26 appears to have several different conventionalwarheads, including a cluster munition warhead, a fuel-air explosive enhanced-blastwarhead, a tactical earth penetrator for bunker busting and an electro- magnetic pulsedevice for anti-radar missions. Given the relatively small warhead, improved terminalprecision is a major system requirement, which could be achieved by active terminalsensor such as a millimetre wave radar, satellite terminal guidance using GLOSNASS, animproved inertial platform, or some combination of these approaches.

As of 1999 it appeared that this system had entered operational service with the RussianArmy.

The launch installation has two missiles with a range of 280 kilometers. Each missile hasa 480 kilogram warhead consisting of 54 elements. The system can be used against smalland large targets. The Iskander missile can easily overcome air defense systems. It'salmost impossible to prevent a launch of an Iskander missile because of the system'smobility. Targets can be found not only by satellite and aircraft but also by aconventional intelligence center and by a soldier who directs artillery fire. Targets canalso be found from photos, which will be put into a computer by means of a scanner. Theself-direction device functions even in fog or darkness. Only the Iskander system canaccomplish such tasks. The United States has tried to reconsider the missile technologycontrol regime and here arises the question whether this may be an obstacle for the sale ofthe new missile abroad. Such missile systems as Iskander have a special place in theworld weapons market. Even a small amount of such missiles drastically changes thebalance of force in conflicts.

According to Nikolay Guschin, chief and senior designer of the Machinebuilding DesignOffice, the complex is meant ' for covertly preparing and launching effective missilestrikes at small-size targets of particular importance. A specificity of this complex is thehigh level of automation in the pre-launch preparations little time required to make itready, and the high precision of shooting.Research carried out by specialists from the leading Russian military science centers hasshown that the lskander-E missile complex is 5 to 8 times better than its foreignanalogues in terms of the "effectiveness-cost" criterion. As for its tactical and technicalcharacteristics, it also poses a great improvement on the existing Russian tactical missilecomplexes. Capable of accomplishing tasks connected with the use of non-nuclearwarheads, it's the world's first complex equipped with two-missile launch installation.Weighing 3800 kilos each, controlled throughout the trajectory of their flight, equippedwith various systems of correction and self-targeting, its missiles are capable ofovercoming the enemy's anti-missile defences and hitting targets at a distance of 280kilometers.According to military experts, the lskander-E missile complex will serve as "determentweapon" in local conflicts, and as strategic arms for the countries with limited territory.Its great range of shooting making it possible to use it from the depth of one's ownpositions, and the brief time it can stay in its launch position make the complex virtuallyinvulnerable to ordinary weapons.The composition of the complex makes it possible to ensure the full cycle of its use incombat, including its combat control, information base, technical servicing and thetraining of its crews, without the involvement of additional remedies.

SpecificationsDIA Code Name SS-26

Nato Code Name: ?

Russian Designation: Iskander

Design Bureau: KBM Engineering

Inservice: 1999

Range: 300 Km

Stages: 1

Warhead: 480Kg - unitary or 10 Submutitions

Weight: 3,800 Kg

Fuel: Solid

Guidance: GPS/GLONASS/Inertial/ Possibly IRTerminal Homing

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SS-NX-13 [KY-9] SLBMThe SS-NX-13 submarine-launched ballistic missile is a short-range, two-stage, storableliquid-propellant missile apparently designed for an anti-ship role. It is capable ofdelivering a reentry vehicle in the 2500-lb class, containing a warhead with a yield of 2.0to 3.5 MT, to a minimum operational range of 80 nm or a maximum operational range of360 nm. The missile flies a lofted trajectory, and is unique in that it has an impact-pointcorrection capability of up to 30 nm through use of a restartable second-stage. Themissile uses an inertial guidance system aided by an onboard passive ELINT targetsensor. In a pure ballistic mode the SS-NX-13 is capable of a CEP of about 0.3 nm, andagainst cooperative targets, i.e., a target emanating radio-frequency transmissions, theSS-NX-13 is capable of a CEP of 0.1 to 0.2 nm.

SS-N-3 SEPALSSC-1a SHADDOCKThe "SHADDOCK/SEPAL" missile is an interesting example of the limits of Westernintelligence during the early years of the Cold War, since NATO applied theSHADDOCK designation to six different and unrelated missiles, yet the virtuallyidentical S-35 and P-35 missiles were given two different codenames -- SEPAL andSHADDOCK, respectively.

The SS-N-3 is a family of turbojet-powered, cruise missiles with three variants[confusingly, the Western nomenclature designates the initial P-5 variant with the highestnumber -- SS-N-3c].

The P-5 [SS-N-3c Shaddock], an inertially-guided missile, is launched from Echo II,Whiskey Conversion, and Juliett submarines and flies to a maximum range of 250 nm ata speed of . It is the oldest of the three SS-N-3 missiles and is almost identical to theSoviet Army SSC-1a (Shaddock). The P-5 cruise missile was designed in the 1950's bythe Chelomey design bureau. The P-5 had a special system of two unfolding wings"ARK-5", which allowed it to be launched from the relatively low diameter cylindricalsubmarine launcher. P-5 had a range of 500 km at an altitude of 100-400 meters and aspeed of 345 m/s [Mach 0.9]. The later P-7 variant had a range of 1000 km. Thesecharacteristics allowed the P-5 to effectively penetrate the US coastal air defense systemof the early 1960's. The circular error probable at full range was 3,000m, which wascompensated by the 930 Kg "RDS-4" nuclear warhead. As with the US Navy's Regulus,to fire the SS-N-3c the submarine platform had to surface for launch, deploy and activatea tracking radar, and remain on the surface linked to the high altitude cruise missile inflight via datalink, providing guidance commands based on the submarine radar'stracking data.

The P-6 [SS-N-3a Shaddock] is a more accurate cruise missile later developed fortargeting US Aircraft carriers. This radar-homing missile is launched from Echo II andJuliett submarines and flies to a maximum range of 220 nm at a cruise speed of Mach 1.2.A 2200-lb conventional or nuclear warhead is estimated for the SS-N-3a. In its antishipversion, the Echo depended on prior cueing by a radar-equipped maritime patrol aircraftand terminal homing by a radar seeker on the SS-N-3 itself. The high altitude, relativelyslow SS-N-3 was vulnerable to air defenses in flight, and its radar seeker was vulnerableto jamming and deception measures.

The P-35 SS-N-3b (SEPAL), also a radar-homing missile, is launched from Kynda andKresta I class guided-missile cruisers and generally flies to a range of 150 nm at a speedof Mach 1.2. It is estimated to carry a 2200-lb warhead.

The S-35 SSC-1a "SHADDOCK" missile is transported in and launched from a longcylindrical container mounted on an eight-wheel vehicle of distinctive appearance. For

launching, the crew 'lowers the four hydraulic stabilization jacks, removes thehemispherical end covers to the top-mounted tables, clamps down the blast shields overthe windows, and elevates the container to the proper launch angle. The SSC-lb coastaldefense version can be distinguished by the longer driver's cab on the transport-launchvehicle.


Entered Service

Total length 10.20 meters [SS-N-3a/b]11.75 meters [SS-N-3c]

Diameter 0.98 meter

Wingspan 5.00 meters

Weight 5,400 kg

Warhead 1000 kg conventional high explosive or350 kiloton nuclear warhead

Propulsion 2 solid-fuel boosters1 turbo-jet sustainer

Maximum Speed Mach 0.9


450 km [SS-N-3a/b]750 km [SS-N-3c]

Guidance mode inertial with mid-course guidance through data linkfrom launch platform

Single-shot hitprobability

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P-1 Strela Shchuka-ASS-N-1 ScrubberThe SS-N-1 Scrubber [in British usage, a "scrubber" is young lady of dubious integrity]was a cruise missile with a nuclear warhead. With the Russian service designation P-1[also sometimes referred to as the Strela or Shchuka-A], it was deployed on the Kildin-class and Kanin-class destroyers [Soviet designation Large Rocket Ships]. Between 1966and 1977 these ships were modernized and redesignated Large Anti-Submarine Ship(Bol'shoy Protivolodochny Korabl' – BPK) in the face of the obsolescence of the SS-N-1Scrubber.


Entered Service 1957

Total length 7.6 meters

Diameter 0.9 meter

Wingspan 4.6 meters

Weight 3,100 kg

Warhead nuclear warhead

Propulsion liquid rocket

Maximum Speed

Maximum effectiverange 40 km

Guidance mode inertial


P-70 Ametiste 4K-66SS-N-7 StarbrightThe SS-N-7 is a subsonic, solid-propellant, cruise, anti-ship missile launched from asubmerged Soviet submarine. It was a scaled down P-5 [SSN-3 Shaddock] designed toarm Project 670A class [Charlie class] submarines. It is believed to be capable ofcarrying a payload of 1170-lb a distance of about 30 nm. It was intended to replace thehigh altitude, relatively slow SS-N-3, which was vulnerable to air defenses in flight andused a radar seeker that was vulnerable to jamming and deception measures. The shorterrange of the SS-N-7 compared to the SS-N-3 reduced the flight time of the missile andeliminated the need for mid-course guidance. This eliminated the need for a guidanceradar on the submarine, which allowed a fire and forget submerged launch.


Entered Service


Diameter

Wingspan

Weight 3,375 kg


Propulsion solid rocket engine


Maximum effectiverange 50-65 km

Guidance mode inertial with terminal homing


P-120 Malakhit 4K-85SSN-9 SirenThe P-50 Malachit was developed as a "universal" anti-ship missiles for submarines andsurface ships. It was intended to replace the high altitude, relatively slow SS-N-3, whichwas vulnerable to air defenses in flight and used a radar seeker that was vulnerable tojamming and deception measures. Intended to replace P-50 missile, development of theP-120 Malakhit [industrial code 4K-85] started 1963. The shorter range of the SS-N-9compared to the SS-N-3 reduced the flight time of the missile and eliminated the need formid-course guidance. This eliminated the need for a guidance radar on the submarine,which allowed a fire and forget submerged launch. It was initially deployed on surfaceships and subsequently on the Charlie-II submarines. It has been superceded by thelonger-range SS-N-22 Sunburn.




Diameter

Wingspan

Weight 3,000 kg


Propulsion solid-fuel booster and sustainer[liquid-fuel rocket engine according to some sources]

Maximum Speed Mach 0.8 [Mach 1.4 according to some sources]


Guidance mode inertial terminal homing


P-350 Bazalt 4K-77P-500 Bazalt 4K-80SS-N-12 SandboxSS-N-12 Sandbox is a Russian supersonic speed cruise missile with a range of 550 kmcarrying a payload of 1,000 kg. The P-350 Bazalt [industrial code 4K-77] was thesuccessor to the P-35 Bazalt, which was started in 1963 and subsequently cancelled. Itevolved into the P-500 Bazalt [industrial code 4K-80] which was the production versionof the original P-350 Bazalt. Developed to replace the SS-N-3 Shaddock anti- shipmissile, it was initially deployed on Kiev-class aircraft carriers in the mid-1970s. TheSlava-class cruisers carry an advanced version with an improved sophisticated guidancesystem, an autopilot that can be programmed for mid-course maneuvers, and an enhancedengine. The P-700 Granat [SSN-19 Shipwreck] was developed as a more successfulturbojet alternative to the SSN-12 Sandbox, from which it was derived.




Diameter 0.90 meters

Wingspan 2.60 meters

Weight 5,000 kg

Warhead 1,000 kg high-explosive or350 kiloton nuclear

Propulsion liquid-fueled rocket[turbojet according to some sources]



Guidance modemid-course missile guidance radar on lamuchplatformactive or passive terminal homing

Circular ErrorProbable (CEP) 300-700 m

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P-700 3M-45 GranatSS-N-19 SHIPWRECKThe P-700 Granat [SSN-19 Shipwreck] was developed as a more successful turbojetalternative to the SSN-12 Sandbox, from which it was derived. Developed in the 1970's,the Shipwreck's initial employment was on the battle cruiser Kirov (later renamedAdmiral Ushakov). The Shipwreck was subsequently deployed on the nuclear poweredcruiser Peter the Great. It is also deployed on submarines, which can launch the missilewhile submerged.


Entered Service

Total length 10 meters

Diameter 0.85 meters

Wingspan

Weight 7,000 kg


Propulsion 2 solid-fuel boosters1 turbojet sustainer engine

Maximum Speed supersonic


Guidance mode inertial with command update, active radar/IR andanti-radar homing


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Project 651 / JuliettProject 651 (NATO designation - Juliett) was ordered by the Soviet Navy in the late1950s to provide a nuclear strike capability against the US homeland, particularly EastCoast cities. The Juliett had four nuclear armed cruise missiles on board, and ten torpedotubes with up to 22 torpedoes. The time required for the first missile launch was about 4.5minutes, with the second after 10 seconds. The missiles were launched from the surface,while the submarine was moving at a speed of up to 4 knots. Initially armed with the P-5[SS-N-3c Shaddock] inertially-guided missile, it was subsequently equipped with moreaccurate cruise missiles [the P-6 SS-N-3a Shaddock, and the later P-500 4K-80 BazaltSS-N-12 SANDBOX] which were deployed on these submarines for targeting Americanaircraft carriers.

The Juliett is about 4 times larger than WWII submarines. The Project 651 is of double-hull construction with an exceptionally large reserve buoyancy. The hull itself containedeight compartments: I. forward torpedo room, II. living accommodations and forwardbatteries, III. Missile control room and batteries, IV. submarine control room, V. livingaccommodations and two banks of batteries, VI. Diesels and generators, VII. electricmotors and VIII. after torpedo room. The submarine's hull is covered by two inch thickblack tiles made of specially profiled sonar/ sound absorbing hard rubber. The silver zincbatteries allow travel submerged with a maximum speed of 17,5 kn. for 1.5 hours, with amaximum underwater range of 810 miles. Another advancement was a low magneticsignature austenitic steel hull. A special 10m2 target guidance radar was built into theforward edge of the sail structure, which opens by rotating. The boats were eventuallyfitted with the Kasatka satellite downlink for targeting information.

It was originally planned to build 35 of these submarines to augment nuclear-poweredProject 675 (ECHO II) class submarines which with 8 missile launchers were an enlargednuclear version of the Juliett. In fact only 16 submarines were actually built from 1962 to1968, most of them by Krasnoye Sormovo shipyard in Gorky. The Juliett's were in activeservice through the 80's with the last one decommissioned in 1994.

SpecificationsDisplacement (tons): 3,174 Tons Surfaced

3,636 Tons with additional fuel4,137 Tons Submerged

Speed (kts): 19 knots Surfaced14 knots Dived

Operating Depth 775 ft maximum Safe Depth1,200 ft crush depth

Dimensions (m): 297 ft (90 M) long32.8 ft (10 M) beam

23 ft (7 M) draft

Propulsion 2 Main Diesel (3500 hp each)2 Electric Motors (3000 hp each)300 Tons Silver Zinc Batteries2 Shafts/Propellers2 Electric "Silent Run" (150 hp)1 Diesel Generator (3000 hp)

Endurance:

90 days9000 miles at 8kn Surfaced18,000 miles at 7kn max. with additional fuel810 miles submerged at 2,74 kn.

Crew 12 Officers, 16 NCO, 54 Crew

Armament:4 P-5 (P-6 or P-500) Guided Cruise Missiles6 Bow torpedo tubes - 21" (533 MM)4 Stern torpedo tubes - 16" (400 MM)

Electronics RadarSonar


# number

Name

Shipyard

Fleet

LaidDown

Launched

Comm.

Stricken

Notes

1

K-156 KS 11/16

/196007/31/1962

12/10/1963

1991-95

1987 redesignated to B-156

2

K-85 KS -------

-------------

12/30/1964

1991-95

3

K-70 KS -------

-------------

12/31/1964

1991-95

redesignated to B-270

4K-24 KS 10/15

/196103/11/1965

10/31/1965

1994?

redesignated to B-124 1994 soldto Finland as floating restaurant

5K-77 KS -------

-------------

10/31/1965

1991-

95

6K-81 KS 11/20

/196308/07/1964

12/14/1965

1994

1994 sold to Finland as floatingrestaurant

7

K-68 KS -------

-------------

12/28/1965

1991-95

8

K-63 KS -------

-------------

06/12/1966

1991-95

9

K-58 KS -------

-------------

09/23/1966

1991-95

10

K-73 KS -------

-------------

12/15/1966

1991-95

11

K-67 KS -------

-------------

09/30/1967

1991-95

12

K-78 KS -------

-------------

11/01/1967

1991-95

redesignated to B-478

13

K-203 KS -------

-------------

12/02/1967

1991-95

14

K-304 KS -------

-------------

08/21/1968

1991-95

15

K-318 KS -------

-------------

09/29/1968

1991-95

16

K-120 KS -------

-------------

12/26/1968

1991-95

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Project 659 / Echo IProject 675 / Echo IIThe Project 659 [Echo I] nuclear-powered cruise-missile submarines were designed tolaunch the land-attack version SS-N-3c Shaddock. They carried 6 Shaddock missiles inerectable launch tubes mounted in pairs above the pressure hull on both sides of the sail.The Echo I boats, which used a reactor and propulsion system similar to the Hotel SSBNand November SSN classes, were converted to attack submarines in the early 1970s. Atleast one and possibly two were decommissioned in the mid-1980s, while the remainingthree or four units were decommissioned in 1990.

The Project 675 [Echo II] nuclear-powered cruise-missile submarines were modified tocarry the Front series of radars [also featured on the Juliet-class SSG] that enabled themto launch the anti-shipping version of the Shaddock. These were primarily anti-carrierweapons, intended originally as a response to nuclear strikes against the Soviet Union bycarrier-based aircraft like the A-3 Skywarrior. As such, their SS-N-3s came in bothnuclear and conventional versions. A total of eight missiles were carried, two more thanon the Echo-I, and the hull was lengthed five meters to accomodate the extra pair oflaunchers. According to Western estimates about 20 minutes was required to launch alleight missiles. To fire its missiles the submarine surfaced, deployed and activated atracking radar, and remained on the surface linked to the high altitude cruise missile inflight via datalink, providing guidance commands based on the submarine radar'stracking data. The submarine itself was highly vulnerable to attack while on the surfaceoperating its radar. A total of 29 Echo IIs were constructed between 1962 and 1968, ofwhich perhaps 10 were converted to carry the improved SS-N-12 by the mid-1980s. Allhad been de-commissioned by the mid-1990s.

At least four Echo submarines have suffered serious accidents. In August 1980 a fire inan Echo II off Japan killed at least nine crewmembers. On 26 June 1989 a fire erupted inof the the two reactor compartments on an Echo II submarine of the Northern Fleet. Thereactor had to be shut down, and the submarine surfaced to return to Murmansk underauxiliary diesel power. Several crew members were injured, but none were killed in theincident. There is some confusion over the numbering of the damaged submarines.According to one reasobably authoritative account, the Navy has four damagedsubmarines, of which three are in the Far East, in the Pavlovski Bay (project 675, serialNo. 175 and 541 and project 671, serial No. 610) and one - in the North (project 675,serial No. 533). The cores of submarines No. 541 and 533 are planned to be discharged.These numbers are at variance with those reported by other sources, and certainly reflectat least in part the annoying Russian habit of re-designating their ships.

SpecificationsProject 659 / Echo I Project 675 / Echo II

Displacement (tons): 4,500 tons surfaced5,500 tons submerged

5,000 tons surfaced6,000 tons submerged

Speed (kts): 20 kts surfaced25 kts submerged

20 kts surfaced23 kts submerged

Dimensions (m): 110.0 meters long9.0 meters beam7.5 meters draft

115.0 meters long9.0 meters beam7.5 meters draft

Propulsion 2 pressurized-waternuclear reactorssteam turbines; 25,000shp2 shafts 5-bladedpropellers

2 pressurized-waternuclear reactorssteam turbines; 30,000shp2 shafts 5-bladedpropellers

Endurance:

Crew about 75 about 90

Armament:

6 - SS-N-36 21-in (533-mm)torpedo tubes (fwd)4 16-in (406-mm)torpedo tubes (aft)

8 - SS-N-3 or8 - SS-N-126 21-in (533-mm)torpedo tubes (fwd)4 16-in (406-mm)torpedo tubes (aft)

Electronics RadarFront Door or FrontPiece targetingSnoop Tray SurfaceSearchSonarHerkulesFez

RadarSnoop Tray SurfaceSearchSonarFenikslow-frequency


NO.

NameShipyard Laid

DownLaunched

Comm.

Stricken

Notes

Project 659, NATO code "Echo I"

K-45

KM 12/28/1957

05/12/1959

09/18/1960

1990

06/1961 operational1965-69 project 659T convertedto SSN under SALT-1

K-59

KM ----------

----------

12/10/1961

1990

1965-69 project 659T convertedto SSN under SALT-1

K-66

KM ----------

----------

12/10/1961

1990

1965-69 project 659T convertedto SSN under SALT-1'04/23/1980 fire (mutiny?)in reserve

K-122

KM ----------

----------

04/13/1962

1981

1965-69 project 659T convertedto SSN under SALT-1'08/21/1981 reactoraccident,stricken

K-259

KM ----------

----------

12/**/1962

1990

NO. possibly K-1511965-69 project 659T convertedto SSN under SALT-1

Project 675, NATO code "Echo II"

K-1

SV ----------

----------

1962-68

----------

1987 project 675MK converted(satellite targeting)

K-7

KM ----------

----------

1962-68

----------

1968 redesignated to K-127

K-10

KM ----------

----------

1962-68

1982

lead ship built at KM1980 collided with Chinesesubmarine

K-22

Krasnovardeets

SV ----------

----------

1962-68

----------


K-23

KM ----------

----------

1962-68

----------

K-28

SV ----------

----------

1962-68

----------

redesignated to K-428

K-31

KM ----------

----------

1962-68

----------

04/29/1969 redesignated to K-43101/13/1986 reactor accident,inreserve

K-34

Kefal KM ----------

----------

1962-68

----------


K-35

SV ----------

----------

1962-68

----------


K-47

SV ----------

----------

1962-68

----------

09/26/1976 fire

K-48

KM ----------

----------

1962-68

----------

project 675K converted (SLEP)

K-56

SV ----------

----------

1962-68

----------

06/13/1973 collided withresearch ship

K-57

KM ----------

----------

1962-68

----------


K-74

SV ----------

----------

1962-68

----------

K-86

SV ----------

----------

1962-68

----------

diver tranport converted

K-90

KM ----------

----------

1962-68

----------

K-94

KM ----------

----------

1962-68

----------

K-104

SV ----------

----------

1962-68

----------


K-108

KM ----------

----------

1962-68

----------

K-116

KM ----------

----------

1962-68

----------

08/19/1978 reactor accident

K-125

SV ----------

----------

1962-68

----------

K-128

KM ----------

----------

1962-68

----------

K-135

KM ----------

----------

1962-68

----------

K-166

SV ----------

----------

1962-68

----------

lead ship built at SV

K-172

KM ----------

----------

1962-68

----------

K-175

KM ----------

----------

1962-68

----------

K-184

KM ----------

----------

1962-68

----------

K-189

KM ----------

----------

1962-68

----------

hull NO. possibly K-131

K-192

SV ----------

----------

1962-68

----------

06/25/1989 reactor accident,inreservein storage at Polyarny

http://www.fas.org/nuke/guide/russia/theater/echo-2_DNST8205653.JPG

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http://www.fas.org/nuke/guide/russia/theater/pl659.jpg

Project 670 Skat / Charlie IProject 670M Skat-M / Charlie IIThe CHARLIE was originally planned as a small, "mass-production" submarine thatwould be the lower-cost complement to the more expensive PAPA design, which clearlycould not be built in sufficient numbers [in fact, only a single PAPA was built]. TheCharlie SSGN was the first Soviet submarine to deploy submerged launch antishipmissiles. In common with American submarines, and unique among Soviet combatnuclear submarines, the Charlie class had a single reactor and a single propeller shaft --all other Soviet submarine classes feature two reactors and two propellers. With only asingle reactor (VM-4 type water-cooled), the Charlie-class was limited to a top speed of24 knots, which was insufficient to keep pace with a 30-knot carrier battle group.

The Charlie seemed to eliminate many of the problems inherent in the Echo design andconcept of operations. It used targeting data from the first Soviet ocean surveillancesatellites, which were intended to substitute for the vulnerable and range-limited maritimesurveillance aircraft. In practice, the space-based ocean surveillance system did not liveup to initial expectations, and the Charlie remained dependent on surveillance for targetacquisition support. Although the shorter range of the SS-N-7 compared to the SS-N-3required a closer approach to the target, it also reduced the flight time of the missile andeliminated the need for mid-course guidance. This eliminated the need for a guidanceradar on the submarine, which allowed a fire and forget submerged launch.

The Charlie-I was originally designed to carry the SS-N-9 anti-shipping cruise missile,which had been planned for the PAPA class. When the SS-N-9 missile was not ready intime for the Charlie-I class, the SS-N-7 [a modified version of the SS-N-2 Styx], wassubstituted. A total of 11 or 12 Charlie I submarines, carrying 8 SS-N-7s ofapproximately 30 mile range, were built between 1967 and 1972 at a rate of about two ayear. The Charlie II provided the SS-N-9 armament originally planned for the Charlie Iclass, along with an improved fire control system. Six Charlie II submarines, each with 8SS-N-9s of 60 mile range, followed between 1972 and 1980. The slower construction rateof the Charlie II suggested that the design was deemed less than satisfactory. Indeed, theCharlie SSGNs were by far the smallest class of the second generation of Soviet nuclearsubmarines which, also included 49 Victor SSNs and 76 Yankee/Delta SSBNs. Allsubmarines of both classes had been discarded by 1994. Contrary to some expectations,there was no Charlie III class.

K429 (a Charlie I class submarine) sank on 23 June 1983 in the Savannaya Bay in theBering Sea. The boat was raised and returned to service. Unluckily, she sank againalongside the jetty on 13 September 1985. The incident led to the loss 16 lives and theimprisonment of the submarine commander. In January 1988 the Soviets leased a CharlieI to India, where she served until January 1991 as the Chakra. Some reports suggesting athat a second Charlie-class unit would be leased to India [possibly to be named theChitra] were erroneous.

SpecificationsProject 670 / Charlie I Project 670M / Charlie II

Displacement (tons): 4,000 surfaced5,000 submerged

4,500 surfaced5,400 submerged

Speed (kts): 23 knots dived16 kts surfaced



Propulsion 1 VM-5 pressurized-water nuclear reactor1 steam turbine 20,000 shp1 5-bladed propeller

Endurance:

Crew about 100

Armament:

8 SS-N-7 Starbright6 21-in (533-mm)torpedo tubes (fwd)12 torpedoes or12 SS-N-15 Starfish

8 SS-N-9 Siren6 21-in (533-mm)torpedo tubes (fwd)12 torpedoes or12 SS-N-15 Starfish

Electronics RadarSnoop Tray Surface SearchSonarShark Teeth bow-mountedperiscopes


NO. Name

Shipyard Laid

DownLaunched

Comm. Stricken

Notes

Project 670A("Skat" type), NATO code "Charlie I"

K-43

KS ----------

----------

1968 ----------

01/1988-01/1991 project 06709,to India (Chakra)1991 in reserve

K-87

KS ----------

----------

1969 ----------

1972 redesignated to K-2121992 in reserve

K- KS --------- ------- 1969 ------ 1993 in reserve

25 - --- ----

K-121

KS ----------

----------

1969 ----------

1993 in reserve

K-313

KS ----------

----------

1970 ----------

12/1985 primary coolant leak,probably in reserve

K-308

KS ----------

----------

09/20/1970

----------

1993 in reserve

K-320

KS ----------

----------

09/15/1971

----------

01/18/1970 reactor accidentunder construction1994 in reserve

K-303

KS ----------

----------

1971 ----------

1995 in reserve

K-325

KS ----------

----------

1971 ----------

1995 in reserve

K-429

KS ----------

----------

1972 1987 06/24/1983 sunk (laterrecovered)09/13/1985 sunk again

K-201

KS ----------

----------

12/26/1972

----------

1994 in reserve

Project 670M("Skat-M" type), NATO code "Charlie II"

K-452

Berkut

KS ----------

1973 1974 ----------

1989 namedproject P-670 converted1994 in reserve

K-458

KS ----------

1975 1976 ----------

1992 in reserve

K-479

KS ----------

1977 1978 ----------

1993 in reservein storage in Nerpa navalshipyard

K-503

KS ----------

1978 1979 ----------

1994 in reserve

K-508

KS ----------

1979 1980 ----------

1994 in reserve

K-209

KS ----------

1980 1982 ----------

1994 in reserve

http://www.fas.org/nuke/guide/russia/theater/charlie-1-DNSC8903178.JPG




http://www.fas.org/nuke/guide/russia/theater/charlie-1-DNSN8205959.JPG

http://www.fas.org/nuke/guide/russia/theater/charlie-DNST8204650.JPG

http://www.fas.org/nuke/guide/russia/theater/pl670a.jpg

Project 661 Anchar / PapaA predecessor to the famous ALFA-class attack submarine, the Project 661 Anchar[Papa] was designed as an extremely fast anti-shipping cruise missile submarine. ThePapa design included 10 SS-N-9 missiles in individual tubes forward of the sail, betweenthe inner (pressure) hull and the outer hull. The US Navy was surprised in 1970 by thedeployment of the Alfa-class attack submarine, whose 45 knot speed and 2000-2500 footoperating depth greatly surpased previous Soviet or American submarines. The Alfa useda high power density, liquid metal reactor plant which greatly increased her power-to-weight and volume ratios. It also featured a titanium pressure hull which reduced the hullweight needed for extreme operating depths. The Papa SSGN appeared to incorporatesimilar design technologies for the antiship cruise missile mission. The K-162 was theworld's fastest submarine, reportedly reaching a record speed of 44.7 knots on trials[causing signficant damage to topside equipment in the process]. The high speed of thedesign came at the price of excessive noisy and high construction costs. The Alfa did notenter production until the late 1970s, with only six units built, while only a single PAPAwas ever deployed. Instead, the Soviets focused on building the more traditionalsubmarines.

SpecificationsDisplacement (tons): 5,200 surfaced

7,000 submerged

Speed (kts): 44.7 knots dived

Operating Depth 400 meters


Propulsion 2 VM-5m pressurized-water nuclear reactors, 177.4MWt2 steam turbines; ??,000 shp2 ?-bladed propellers

Endurance:

Crew 82

Armament: 10 - SS-N-9torpedo tubes

Electronics RadarSonar2 periscopes


NO.

Name

Shipyard Laid

DownLaunched

Comm. Stricken

Notes

K-162

SV 12/28/1963

12/21/1968

12/31/1969

----------

redesignated to K-22209/30/1980 reactoraccident1988 in reservein storage inSeverodvinsk

http://www.fas.org/nuke/guide/russia/theater/papa-DNSN8600737.JPG

http://www.fas.org/nuke/guide/russia/theater/pl661.jpg

Project 949 Granit / Oscar IProject 949A Antey / Oscar IIThe Oscar-class nuclear-powered cruise missile attack submarine, which displaces morethan 18,000 tons when under water, is one of Russia's largest and most capablesubmarines. As with earlier cruise-missile submarine, the Oscar was designed primarilyto attack American aircraft carrier battle groups.

As with other Russian submarines, the Oscar features a double hull -- and inner pressurehull and an outer hydrodynamic hull, with eight inches of rubber between them to mufflesounds. American submarines have a single pressure hull, with additional hydrodynamicfairings, such as the cap that encloses the bow sonar dome. The 3.5 meter separationbetween the inner and outter hulls on the Oscar provides significant reserve buoyancy,and improved survivability against conventional torpedoes. These large submarines aresaid to be slow to dive and maneuver, though they are credited with a submerged speedof about 30 knots - sufficient to keep pace with their targets. The improved Oscar II isabout 10 meters longer than the Oscar I, possibly making room for a quieter propulsionsystem, and feature upgraded electronic systems. The Oscar II is also characterized by asubstantially enlarged fin, which should improve underwater manueverability, as well asthe substitution of the Oscar-I's four-bladed propeller with a [presumably] quiter seven-blade propeller.

The Oscars are rather poorly characterized in the open literature, with substantialdiscrepancies in reported submerged displacement [the upper estimates are probablycloser to the mark] and maximum submerged speed [reportedly classified intelligenceestimates have tended upward over time. Considerable confusion also exists as to thenames of some units. During the Cold War essentially no information was publiclyavailable concerning the names of Soviet submarines, and with the end of the Cold Warthe Russian Navy has exibited an annoying tendency to rename ships [a very un-American practice]. And unlike the American practice, in which hull numbers aregenerally assigned in a consecutive numerical sequence which corresponds to thechronological sequence of construction, the pennant numbers assigned Russiansubmarines [eg, K-141] do not conform to an apparent set pattern.

The submarine is equipped with two dozen SS-N-19 missiles with a range of 550-kilometers -- three times as many anti-ship cruise missiles as earlier Charlie and Echo IIclass submarines. The missiles, which are launched while the submarine is submerged,are fired from tubes fixed at an angle of approximately 40 degrees. The tubes, arranged intwo rows of twelve each, are covered by six hatches on each side of the sail, with eachhatch covering a pair of tubes. The launchers are placed between the inner pressure hulland the outer hydrodynamic hull. The torpedo tubes fire both torpedoes and shorter rangeanti-ship missiles, and a combination of some two dozen weapons are carried.

The Project 949A submarines have a total of at least ten separate compartments, whichcan be sealed off from each other in the event of accidents. The compartments arenumbered sequentially from fore to aft, with the two separate reactor compartmentsnumbered V and V-bis [which is accounts for the fact that there are ten compartments,though the numbers only run through nine].

I - Torpedo roomII - Control RoomIII - Combat stations and radio roomIV - Living QuartersV and V-bis - ReactorsVI - propulsion engineeringVII - main propulsion turbinesVIII - main propulsion turbinesIX - electric motors

Access hatches are believed to be located in the 4th and 9th compartments. In commonwith the larger Typhoon-class ballistic missile submarine, the Oscar-class boats arereported to have an emergency crew escape capsule located in the sail.

In the 1980s the Rubin Design Bureau was responsible for developing a number of thirdgeneration nuclear submarines with cruise missiles, including Projects 949 ("Granit","Oscar I") and 949A ("Antey", "Oscar II"). The Bureau took the lead in using navalcruise missiles, designing the first cruise missile nuclear submarine -- Project 659 ("EchoI"), then Project 675 ("Echo II") and related modifications.

To manage the impact of its resource problems, the Russian Navy, in the early 1990’s,made a series of hard choices aimed at preserving its core submarine force capabilities.These included early retirements of older and less capable units, strict controls onoperating tempo, and focused maintenance on its best submarines. The first Oscar I unitswere decommissioned in 1996, though the Russian Navy continued to invest in newconstruction. In the late 1990s it completed several new submarines of the larger thirdgeneration Oscar II SSGN.

Considering the importance of the Oscar II submarines for the Russian Navy, the level ofconfusion concerning the designations and status of the units of this class verges on theastonishing. There is almost complete disagreement among all authoritative sourcesconcerning the correlation between pennant number, name, construction sequence andcurrent status. Allowing for the unavoidable uncertainties inherent in assigning"commissioning" dates, most sources are in general agreement as to the unit chronologyand pennant number chronological sequence of the first ten units, through K-141 Kursk.There is however, rather general disagreement among sources as to the names associatedwith these units, and the status of particular units.

All sources agree that at least eleven of the Oscar II submarines were built between 1985and 1999 at the Sevmash yard in Severodvinsk. The status of a twelfth Oscar-II issomewhat uncertain, as some sources suggest it was comissioned in late 1999, while mostagree that outfitting was suspended after it was launched [sometime in the 1998-1999

timeframe]. Some Western sources suggest that construction was suspended on athirteenth unit, and that as many as 15 units of the Oscar II class were planned, butRussian sources maintain that the Oscar-II class was never intended to consist of morethan twelve vessels.

A fourth-generation follow-on to the Oscar was planned, but reduced defense spendingforced the cancellation of the project.

Sources generally agree that at least two and possibly as many as three of the initial nineOscar II units were inactivated in the late 1990s, and as of mid-2000 were laid upawaiting disposal. Considerable confusion surrounds the identity of the third and fourthunits -- Krasnoyarsk] was reportedly deactivated in 1998, but sources differ as to whetherthis name was assigned to K-119 or K-173.

The active Northern Fleet units are homeported at the Zapadnaya Litsa base (BolshayaLopatka). The disposition of units between the Northern and Pacific Fleets is uncertain.As of September 1997 Bellona placed six units in the Northern Fleet, four in the Pacific.As of September 2000 the warships1.com analysis also placed 4 units in the Pacific Fleet,and the remaining 6 in the Northern Fleet. However, World Navies Today reports that tenactive units [as of late 2000] are evenly divided between the two fleets [but the unit listseems rather unreliable, casting doubt on this assessment]. The two sources appear todisagree on the location of K-119 Voronezh.

On 26 January 1998 a moored nuclear-powered Oscar II submarine suffered a coolingsystem accident. During routine tests aboard a cooling system pipe broke, releasingammonia and nitrogen gas into the compartment. A total of 5 crew members wereinjured, one of whom, a Captain of the 3rd Rank, died two days later. The Oscar IIsubmarine was reportedly the K-512 St.Georgy Pobeditel [formerly named Tomsk]. Thiseleventh unit of the 'Oscar II' SSGN class had been launched in July 1995 despiteirregular materiel and component delivery problems.

In 1994 an Oscar submarine conducted operations off the East Coast of the United States.In July 1997 when the Oscar II submarine K-442 Chelyabinsk [aka Pskov] shadowedseveral US aircraft carriers off Washington state. The Tomsk transitted to the Pacificunder ice after being commissioned on 28 February 1997, and arrived at Petropavlovsk-Kamchatskiy on 24 September 1998. This brought the Pacific Fleet class inventory toseven, with four others in the Northern Fleet. In February 1999 an Oscar-class submarinewas observed monitoring a NATO exercise off the coast of Norway. In August 1999NATO sonar detected the presence in Western Atlantic waters of a Russian Oscar classsubmarine belonging to the northern fleet, based in the Arctic ports. In the mid-1999 anOscar II-class submarine sailed from northern Russia to the Mediterranean, the firstRussian SSGN patrol in the Mediterranean in a decade. It then sailed on to areas off theeastern United States. In early September 1999 the crew of the Jose Maria Pastor, afishing trawler registered in Almeria [southeastern Spain] reportedly snagged an Oscarsubmarine in its nets. The incident occured some 27 miles (50 kilometers) from the Tarifacoast (Cadiz Province), and continued for over half an hour before the submarine broke

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free. Another Oscar II deployed from the Russian Far East, sailing to the area aroundHawaii before arriving in waters off San Diego by October 1999. It reportedly spent aweek following the aircraft carrier USS John C. Stennis and the amphibious landing shipEssex.

K-141 Kursk

On or about 12 August 2000, the tenth unit of the Oscar-II class, the K-141 Kursk, sankabout 100 miles from the Russian port of Murmansk. At the time the boat wasparticipating in the fleet's major summer exercises, involving about 30 other vessels. TheKursk apparently sank quickly, and did not launch distress buoys. The submarine was notcarrying any nuclear weapons at the time, and there was apparently no immediate dangerof radiation leaks. Considerable confusion surrounded initial reports, though apparentlythe Kursk shut down its two nuclear reactors after it was crippled. Although RussianNavy commander Adm. Vladimir Kuroyodev stated that there were "signs of a big andserious collision," subsequent reports cast doubt that the sub was damaged in a collision.The US Department of Defense stated that there was " no indication that a US vessel wasinvolved in this accident." By 15 August it was generally believed that the Kursk hadbeen damaged by an explosion on board, probably in the torpedo room.

Initial reports suggested that at least some of the crew were alive and communicatingthrough rhythmic tapping on the hull. Rescue submarines that rushed to the Kurskreportedly found it damaged but resting upright on the seabed, at a depth variouslyreported as between 350 feet and 500 feet of water. Subsequent reports suggested that thesubmarine was listing, perhaps as much as sixty degrees. According to initial reports, asof Monday 14 August 2000 at least one rescue craft, the Kolokol, was said to be feedingpower and oxygen to the Kursk. Communication links with the boat's captain, GennadyLyachin, were reportedly restored after a day of radio silence. However, subsequentreports indicated that these initial reports were incorrect, and overly optimistic. AdmiralKuroyedov initially expressed doubts about the possiblity of rescuing the crew, stating"the chances for a positive outcome are not very high." The Russians had two India-classrescue submarines, each of which carried a pair of small rescue submarines which couldreach a depth of 2,275 feet. However, these submarines and their rescue capabilities wereapparently discarded by the Russians in 1995 as a cost-savings measure.

Rescue efforts centered on attempts to attach equipment to provide oxygen and restoreelectric power to the submarine. As of 15 August a first attempt to lower a diving bell tothe submarine had failed, and a second attempt was launched soon thereafter. The twoattempts on Tuesday to reach the Kursk were frustrated by of poor underwater visibilityand 12-foot high waves. Rescue workers failed in efforts to maneuver a robotic remotedlyoperated vehicle onto an emergency hatch on the submarine.

By Wednesday, while Russian experts were still optimistic about the rescue operation,Russian President Putin termed the situation with wrecked sub "critical". The weatherhad worsened in the Barents Sea, while the Bester capsule with divers aboard was usedfor the first time Rrescue ships tried twice more to lower a diving bell to dock with the

Kursk, but each time the operations had to be aborted because of rough seas, strongcurrents, and poor underwater visibility. Rescue efforts continued despite the fact that oneof the three rescue capsules used to reach the stranded sub was damaged in the storm.The Russian military consulted NATO experts on submarine rescue, and Russia askedBritain and Norway to help the rescue effort. Britain sent three aircraft with crew andequipment, and the first plane loaded with a British rescue vessel landed in Norway lateWednesday [Moscow time]. The British mini-submarine may be transported to Russia bySaturday.

On Thursday 17 August it was reported that US surveillance ships in the area at the timeof the accident heard two explosions on 12 August, the second much stronger than thefirst. The Russian navy was reported to be studying video footage showing massivedamage to the first and second compartments in the submarine's bow. A Navy spokesmansaid the video showed extensive damage from the top to the back fin. The periscope wasalso still up, indicating the ship sank so fast the crew did not have time to react. Russia'sDeputy Prime Minister Ilya Klebanov said films taken of the Kursk indicated extensivedamage to the ship's bow that he said was caused by a collision with an unknown object.

By Friday it was reported that the submarine was lying at an angle of no more than 20degrees from vertical, rather than the 60 degress previously reported, and at a depth of alittle more than 100 meters. The depth and the angle are were said to be well within theoperating limits of th British LR5 rescue craft.

It was initially estimated that the air on the K-141 Kursk submarine would run out byFriday 18 August 2000. As of Friday it was officially estimated it could last another fivedays. Contrary to most news reports, the problem was not a lack of oxygen for the crewto breath in, but rather the buildup of the carbon dioxide that they would breath out. Overtime, this carbon dioxide would build up to a level that would kill any crew memberswho survived the initial accident. The oxygen limit is about 0.1 atm and the Carbondioxide limit is time dependent, but somewhere between 0.03 and 0.06 atm. Respirationproduces (roughly) 1 molecule of carbon dioxide for each molecule of oxygen consumed.This suggests that, starting with 0.21 atm of oxygen, the oxygen partial pressure will stillbe 0.15 atm even when 0.06 atm of carbon dioxide is present. [see the NOAA DivingManual for details].

While some Russian Navy officials maintained that some crew members remained aliveand were sending an SOS message by banging against the submarine's hull, otherofficials said there had been no communication and that the crew might already be dead.

On 21 August Chief of staff of the Russian Northern Fleet Mikhail Motsak pronouncedthe Kursk flooded and its whole crew dead. Admiral Motsak said a Norwegian-led teamof divers was videotaping the interior of the rear compartment after successfully breakingin through damaged escape hatches.On 01 September 2000 an agreement was reached on the technical and organizationalaspects of the international effort to lift to the surface the bodies of the crewmen of theKursk. The Norwegian Stolt Offshore company received blueprints representatives of the

http://uwsports.ycg.com/reference_library/noaa/section_03/subsection_01_03.html

http://uwsports.ycg.com/reference_library/noaa/section_03/subsection_01_03.html

naval design center which designed the sunken submarine that showed where deep waterfrogmen may enter the boat. A team of international and Russian divers planned to cutholes in the Kursk’s hull to pull out the remains of the 118 seamen who died. Theoperation was scheduled to begin in October 2000.There was no chance of quickly salvaging the Kursk submarine, since September is themonth when storms start raging in the Barents Sea, which would make such impossible.At best the salvaging operation could be carried in 2001. Neither the Russian submarinebase at Vidyaevo, nor any western base have hoists capable of salvaging such a largevessel the Kursk submarine, or even moving it to a shallow place closer to the coast. Itwould take several months only to build such a device. Another priority on the agenda isthe salvaging of the submarine and taking it to shallow waters. The Norwegian StalledOffshore Company has given its consent to participate in the salvage effort.

On 06 September 2000 Russian President Vladimir Putin was reported to have said thatthe 118 sailors aboard the submarine Kursk probably died quickly after it sank, and thatthey never sent any signals from the distressed sub after it went down. At the time of theaccident, conflicting reports from some Russian naval officials indicated that survivorswere tapping on the ship's hull. But Putin said that the signals came from "a mechanicaldevice on board" that went off automatically.

There are several versions of the reasons for the disaster. According to Vice-premier IlyaKlebanov, the first version is that of an underwater collision with a foreign vessel. IlyaKlebanov who heads the commission to investigate the case described as the secondversion a possibility that the submarine hit a German mine left over from the time of theSecond World War. The third version, the Vice-premier believed, could be an emergencysituation in the submarine's torpedo compartment. According to Ilya Klebanov, themajority of the crew died during the first seconds of the disaster.

Specifications949 (Oscar-I) 949A (Oscar-II)

Displacement (tons): 12,500 surfaced 13,400 - 14,700 surfaced

http://www.fas.org/nuke/guide/russia/theater/949-kursk1.gif

http://www.fas.org/nuke/guide/russia/theater/949-maps.htm

15,500 - 22,500submerged

16,400 - 24,000submerged

Speed (kts): 32 knots dived16 kts surfaced

32 knots dived16 kts surfaced

Dimensions (m): 143.0 meters long18.2 meters beam (20.1with stabilizers)9.0 meters draft


Propulsion 2 VM-5 190 MWt pressurized-water nuclear reactors(OK-650b)2 steam turbines - 90,000 shp

Propulsion 2 4-bladed propellers 2 7-bladed propellers

Endurance: 50 days

Diving depth: 300-600 meters [byvarious estimates]

Crew : 94 total

Armament: 24 - SS-N-19 / P-700 Granit

24 - torpedoes/tube-launched weapons

4 - 533 mm tubes - SS-N-15 Starfish / 82-Pmissiles or torpedoes4 - 650 mm tubes - SS-N-16 Stallion / 85-Pmissiles or torpedoes

Electronics RadarSnoop Pair or Snoop Half Surface SearchRim Hat intercept arraySonarShark Gill (MGK-503) hull mountedShark Rib flank arrayMouse Roar MG-519 Hull mountedPelamida towed array2 periscopes


NO.

NameShipyard

Fleet Laid

DownLaunched

Comm.

Stricken

Notes

Project 949 ("Granit" type), NATO code "Oscar I"

1 K-525

Arkhangelsk

SY402

NOR

1978 04/**/1980

1982 1996 12/30/80 named"MinskyKomsomolets"1991 renamed1996 deactivated2000 to be dismantledat Sevmash

2 K-206

Murmansk SY402

NOR

1980? 12/**/1982

1983 1996 1991 named1996 deactivated2000 to be dismantledat Sevmash

Project 949A ("Antey" type), NATO code "Oscar II"

1 K-148

Orenburg SY402

NOR

----------

08/**/1985

07/**/198612/**/1986

??1998

ex-Krasnodar [name asof 1995]ex-Vologda2000 probably active2000 laid up awaitingdisposal ??

2 K-132

Irkutsk SY402

PAC

----------

**/**/198603/**/1986

**/**/198701/**/1987

?1998

(name also reported as"Belgorod")2000 in reserve2000 laid up awaitingdisposal ?

3 K-119

Voronezh SY402

NORPAC ?

----------

**/**/198612/**/1987

**/**/198812/**/1988

(name also reported as"Krasnoyarsk""Tambov" or"Chel'yabinsk")2000 active

4 K-173

Krasnoyarsk

SY402

NOR

----------

**/**/198701/**/1989

**/**/198812/**/1989

?1997-8

(name also reported as"Veronesh")(name mis-reported as"Chelyabinsk")1997-8 deactivated2000 laid up awaitingdisposal ?

5 K-410

Smolensk SY402

NOR

----------

**/**/198812/**/1989

**/**/199012/**/1990

2000 active

http://www.fas.org/nuke/guide/russia/facility/slbm/severodvinsk.htm


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http://www.fas.org/nuke/guide/russia/agency/mf-pacific.htm














6 K-442

Chelyabinsk

SY402

PAC

----------

**/**/198901/**/1990

12/29/199001/**/1991

(name also reported as"Pskov")(name mis-reported as"Tomsk")2000 active

7 K-456

Viliuczinsk SY402

PAC

----------

**/**/199012/**/1991

**/**/199111/**/1992

(ex-"Kasatka",possibly "Tambov")09/**/1993 to PacificFleet2000 active

8 K-266

Orel SY402

NOR

----------

01/**/199205/22/1992

12/**/199201/**/1993

(ex-"Severodvinsk")2000 active

9 K-186

Omsk SY402

NOR

----------

05/08/1993

10/27/199312/15/1993

(possibly renamed"PetropavloskKamchatsky")2000 active

10

K-141

Kursk SY402

NOR

1992 05/**/1994

10/**/199412/30/199401/20/1995

8/12/2000

11

K-512

St.GeorgyPobeditel

SY402

PAC

----------

07/18/199507/18/1996

02/28/199712/31/1997

(ex-"Tomsk")08/1997 operational01/26/1998 coolingsystem accident2000 active

12

K-530

Belgorod SY402

----------

05/**/199808/**/1999

???? (name also reported as"Pskov")2000 constructionsuspended??

13

K-139

Pskov? SY402

???? ???? ----------

[?? constructionsuspended ??]

14

K-___

SY402

???? ----------

----------

[?? cancelled ??]

1 K- SY ???? ------- ------- [?? cancelled ??]
































5 ___

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russian nuclear forces

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