short range uav

CLOSE-RANGE / BATTLEFIELD

AIRCRAFT

T.JANAKIRAM2009603001

CHARACTERISTICS

• PLAYS A MULTITUDE ROLES(MILITARY, PARAMILITARY, CIVILIAN)

• LOW-ALTITUDE OPERATIONS

• RAPID RESPONSE TIME

• COMPLETELY MOBILE

SUB-TYPES OF CLOSE-RANGE UAVS

• Non-VTOL AIRCRAFT SYSTEMS

• VTOL SYSTEMS

OBSERVER

CHARACTERISTICS

ALL-UP-MASS 36KgWING SPAN 2.42mWING AREA 1.73m2

ENGINE POWER 5.25KWWING LOADING 184N/m2

SPAN LOADING 120N/mCRUISE SPEEED 125km/hrLOITER SPEED 110km/hrMISSION RADIUS 25kmENDURANCE 2 hrs

For the British Army, Phoenix provides intelligence direct to artillery forces, to command level, or to a Phoenix troop command post. The principal method of communication from the GCS to artillery on the ground is via the Battlefield Artillery Targeting System (BATES). The UAV can be launched within an hour of reaching its launch site. A second UAV can be launched within a further eight minutes and up to two UAVs can be controlled from the same ground station.

The BAE Systems Phoenix is an all-weather, day or night, real-time surveillance Unmanned Air Vehicle. It is a twin-boom UAV with a surveillance pod, from which the imagery is data linked to a ground control station (GCS).

Phoenix

The Elbit Systems Hermes 90 is an unmanned aerial vehicle (UAV) designed for tactical short-range missions using a heavy-fuel motor.Jane's claims that the Hermes 90 has its roots in the IAI I-View and later in the BAE Skylynx II. Ownership of rights were subsequently moved to Elbit Systems.[1]

The Hermes 90 has an operating range of about 15 hours and 100 km.[2]

In September 2009, the Hermes 90 made its maiden flight.[2]

Elbit Systems Hermes 90

ORBITER

RQ-7 Shadow 200

Characteristics: RQ-7B RQ-7B Length 11.2 ft Wing Span 14 ft Gross Weight 375 lb Payload Capacity 60 lb Fuel Capacity 73 lb Fuel Type MOGAS Engine Make UEL AR-741 Power 38 hp Data Link(s) LOS C2 Frequency S-band, UHF LOS Video C-band

Performance: Endurance 6 hr Max/Loiter Speeds 110/60 kt

Ceiling 15,000 ft Radius >68 nm Takeoff Means Catapult/ Rolling T/O Landing Means Rolling Landing/ Arresting Wire Sensor EO/IR Sensor Make Tamam POP 300

RQ-11 Raven (Pathfinder Raven)

Characteristics: RQ-11 RQ-11 Length 3.4 ft Wing Span 4.3 ft Gross Weight 4 lb Payload Capacity 1 lb Fuel Capacity n/a Fuel Type Battery Engine Make Power Data Link(s) C2 Frequency Video

Performance: Endurance 1.5 hr Max/Loiter Speeds Ceiling 14,000 ft Radius 6 nm Takeoff Means Hand launched Landing Means Stall Sensor EO Sensor Make

RQ-2 Pioneer

Puma (Aqua or Terra Puma)

Characteristics: Puma Puma Length 5.9 ft Wing Span 8.5 ft Gross Weight 14 lb Payload Capacity 2-4 lb Fuel Capacity n/a Fuel Type Battery Data Link(s) C2

Performance: Endurance 2.5 hr Max/Loiter Speeds Ceiling 10,000 ft Radius 6 nm Takeoff Means Hand launched Landing Means Stall Sensor EO & IR Sensor Make

RQ-15 Neptune

Neptune is designed for at-sea launch and recovery. Carried in a 72x30x20 inch case that transforms into a pneumatic launcher, it can be launched from small vessels and recovered in open water. It can carry IR or color video sensors, or can be used to drop small payloads. Its digital data link is designed to minimize multipath effects over water. First flight occurred in January 2002, and an initial production contract was awarded to in March 2002

XPV-2 Mako

ScanEagle

SPRITE

CHARACTERISTICS

• BOTH GCS AND A/C HAS BACK-UP SYSTEMS

• TWO INDEPENDENT POWER-PLANTS

•A/C CAN HOVER ON ONE ENGINE

•MODULAR CONSTRUCTION OF GCS AND A/C ENABLES EASE OF BUILD AND MAINTAINENCE

• IT HAS NEUTRAL STABILITY

• RELIES ON AFCS FOR +VE SPATIAL STABILITY

•LOW DETECTABLE SIGNATURES

RMAX

  ItemRMAX

Type II GRMAXType II

Performance

Maximum Payload* 28kg 31kg

Chemical Capacity* 21kg 24kg

Flight Duration 60 minutes

MaximumTakeoff Weight*

94 kg

Practical Range150 m

(visual observation range)

Control System YACS-G YACS

Body

Type L17-1 L17-2

Main Rotor Diameter 3,115 mm

Tail Rotor Diameter 545 mm

Overall Length3,630 mm

(rotors included)

Overall Width 720 mm

Overall Height 1.080 mm

Engine

TypeWater-cooled, 2-stroke,

horizontally opposed 2-cylinder

Displacement 246 cc

MaximumOutput/Maximum Torque

21PSÅ ^ 2.6kgm

Starting System Cell Motor

FuelRegular gasoline mixedwith 2-stroke engine oil

ROTOR DIA-3.13MPAYLOAD - SPRAY EQPT AND FLUID

•FLY EFFICIENTLY AT LOW SPEEDS OVER LOCAL FIELDS.•21/2 MASS OF SPRITE

EADS - Scorpio 30

A lightweight helicopter designed for urban operations by military and paramilitary organisations. Scorpio 30 is the larger version of the type and was first released to the market in 2002. Low volume sales have been recorded for the French Army and undisclosed South American customers. One system was acquired by the UK Ministry of Defence for use in the former joint UAV experimentation programme.

Range Class: Close range  

Airframe Helicopter  

Span 2.20 m  

Length 2.00 m  

Max take-off weight 38.00 kg  

Payload Weight 15.00 kg  

Cruise speed 27.00 kts  

Endurance 2hrs  

COMPARISON OF CLOSE-RANGE UAV

WING LOADING: RL must be able to leave the ramp top and sustain flight at airspeed lower than the a/c using runway. This means RL should have low wing loading..typically 1/10th of HALE &1/2 of medium-range a/c.

Phoenix has the highest wing loading ,followed by Scan Eagle and so on.

PROPELLER EFFICIENCY :RL is vulnerable to air disturbances at air speed

slightly above the stalling speed. Side gust causes lateral roll, side-slip and ground impact. Up-gust causes nose-up in turn resulting in lift and drag increase leading to stall.So propeller must accelerate rapidly to high speed to provide max thrust. Leads to use of variable-pitch prop. Due to RL we us fixed-pitch prop thus resulting in poor efficiency

LANDING EQUIPMENT:PHOENIX AND OBSERVER HAS TO CARRY

PARACHUTE AND AIRBAG TO REDUCE THE IMPACT LOADS ON TOUCH-DOWN.Scan eagle use sky-hook

CONCLUSION OF AUTHOR IS VTOL IS BETTER SUITED FOR SHORT-RANGE/BATTLE FIELD SCENARIO THAN RL HTOL SYSTEMS BECAUSE:

1. VTOL IS LESS VULNERABLE TO ENEMY ATTACK IN AIR AND LESS VULNERABLE ON GROUND DUE TO MORE MOBILE WITH FAR LESS GROUND EQUIPMENT AND PERSONNEL DEPLOYED.

2. VTOL COST LESS IN OPERATION THROUGH LESS COST OF PERSONNEL.

3. LOWER RESPONSE TO AIR TURBULANCE4. VERSATILITY TO HOVER AND LOW SPEED FLIGHT

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