apollo 11 mission profile

8/4/2019 Apollo 11 Mission Profile

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STACKING - Bendix cranes l i f t the 294,900-pound f i r s t stage

of the Saturn 5 with ease. preparing to place it atop the mobile .auncher inThe h igh b%y of the VAB. Launch Support D i t '-?

is responsible for the stacking operations of a l l stages and t

spacecr'aft, in preparing i t for "roll ouP1 o the launch pad.

INTRODUCTION

I f you have been fortunate i n th is histor ic hour to watch the

events surrounding the pre-launch and launch of Apollo 11

unfold, either from a vantage point at the Kennedy Space

Center, o r along the banks of the Indian and Banana Rivers,o r from motel rooms along the Florida East Coast, then y o w

have been privileged to see f i rs t hand the greatest human

achievement i n the annals of mankind.

NASA and its team of aerospace contractors are now reaching

for just one of thei r goals -- landing a man o n the surface of

the moon and re tu rn ing h i m safely to earth. There are yet-

other space conquests in America's exploration of buter spacewhich w i l l cal l for even more determined sp i r i twh ich has been

the backbone of NASA's space program.

The pages of th i s booklet are designed to acquaint you wi th

facts of the Saturn 5, the Apollo soacecraft and t h LunarModule moonship, and to keep you informed of the day-to-

day scheduled missions as they are now planned, for the

durat ion of th is 8-day mission.

This booklet may also be a souvenir to r e m ~ n d ou for many

years to come that you were here dur ing the f l ight of Apollo 11,

the greatest adventure story since Christopher Columbus began

h i s peri lous voyage into the unknown.

ITHE BENDIX CORPORATION



ROLL OUT- The Bendix-operated 6 mil l ion pound CrawlerlTransporter

lumbers lowly to the pad carry ing its prec ious cargo, ApollolSaturn 5.

Known as one of the strongest, slowest, noisiest, strangest landvehicles i n the world, the giant tractor moves at less than one mile

per h o u r dur ing missions,

SATURNV - APOLLO 11

AS-5061CSM - 1071LM-5

MAJOR OBJECTIVES

1. Perform a manned lu na r landing and re tu rn to earth.

2. Per form selenological inspection and sampling, includ-

in g contingencyllunar bulk sample collection.

3. Obtain data to assess the capability and limitations of

the astronaut and his equipment i n the lu na r enviran-

ment, including: Iner ti al Measurement Unit (IMU)lu na r surface operations and l un ar surface EVA opera-

tions.

4. Obtain data o n characteris tics and mechanical behavior

of lunar surface.

5. Obtain data o n landing effects o n LM.

6. Determine position of LM o n the lu na r surface.

7. Obtain data on effects of il lu mi na ti on and contrast condi-

tions on crew visual perception.

8. Demonstrate procedures and hardware used to prevent

contamination of the earth 's biosphere.

9. Obtain photographic coverage dur in g lu na r landing and

lunar stay period.



APOLLO 'GAS STATION' - The Bendix Corporation's LaunchSupport Division High P ressure Gas Department an d the

Propellant Section combine to provide the world's largest

"gas station", of fe ri ng high and low pressure gasses andpropellant delivery for NASA's Apollo Program.

MISSION OBJECTIVES

10. Obtain television coverage dur in g lu na r stay period

11. Deploy the Early Apollo Scienti fic Experiments Package

(EASEP).

12. Demonstrate operational launch vehicle (LV) capabil-

i ty by injec ting a fu l ly loaded Apollo Spacecrafl (SC)

onto a specific ci rc um lu na r conic.

13. Demonstrate the adequacy of a l l SC systems and opera-

tional procedures for trans luna r and transearth fliqht.

14. Demonstrate the adequacy of deep space navigation

techniques and of guidance accuracy dur ing translunar

and transea rth midcourse corrections.

1 Demonstrate acceptable service propulsion system (SPS)

performance and SC guidance du ri ng the luna r orb it

inser tion boost and the transearth inj ec tion boost.

16. Demonstrate acceptable Lunar Module (LMI systems per-

formance dur ing the descent-to-hover boost.

17. Demonstrate acceptable LM systems performance during

the ascent and rendezvous mode.



A B I G JOB - Although i tw e igh s less th an a pound, th is sensor

is capable of in i t iat ing shut-down of the 1.5 mil l ion-pound- thrustengines of the S- I C , th e in i t ia l booster s tage o f NASA 's Sa tu rn 5.

The sensors is bu i l t by Th e Bendix Corporation Inst r um en ts and

Life Sup port Division, Dav enpo rt, Iowa.

PERTINENT DATA

Saturn V Launch Vehicle

SATURN V STAGE MRNUFACTUREl

MRNUFACTURER

NORTH AMERICAN-ROCKWELLt

?

PRE-LAUNCH LAJJNU Y F H I a E

GROSS WEIGHT 5 6.3MI.W

POUNDS

M I N I M VACUUM THRUST AT lUIDF

A 1 170.000 FT. AN0 70'F

NWINAL V A W W THRUST AT 6O.F

NOTE: M R L 6 T VALUES. WEIGHTS. RND BURN T I W ARE ALL APPPXINATIOHS.



COVERUP

-An iner tral guidance system of the type assignedto keeping the Saturn V r o c k t on course d urin g Apollo 11

moan shot. The unit is bu il t by Navigation and ControlDivis~on,Teterboro, N. J,

Lunar Module

Reaction Control

Descent Propulsion System (DPS)

TRW Corporation r o t o r pmv~der10,500 l b r . T h r u s t

To ta l We~ght- 30,531 lbs.



OUTLINE OF FLIGHT PROFiLE

Launch and Earth Parking Orbit Inse rti on - The Saturn VVehicle wi l l insert the S-IVBIIUlLiWCSM into a 100 NM

ci rc ul ar orbit at 11 minutes, 24 seconds after liftoff. TheS- I VB I I U and Spacecraft checkout wi l l be accomplished

dur ing the orbital coast phase.

Translunar Injection and Coast - The Launch Vehicle S-IVBstage w i l l be reign ited dur ing the second parking orbit, to

inject the S-IVB, LM and CSM into a tr an sl un ar trajectory.This nominal injection wi l l provide a "free re tu rn" to Earth

i f the inse rtion into luna r parking orbit cannot be accom-

plished.

The CSMwil l separate from the S-IVB, transpose, dock, and

initiate ejection of the LM. Midcourse corrections wi l l bemade, as required, ut i l iz ing the Manned Space Flight Network

(MSFN) for navigation.

Lunar Orbit Inse rt io n - Service Propulsion System (SPS) w i l l

in se rt the Spacecraft in to an initla1 orblt of 60 X 170 NM.

Following insert ion and systems checks and two revolutionsin this orbit , the orb it wi l l be circularized at@IM.

Lunar Module Descent and Landing - The Commander (CDR)

and LM Pilot (LMP) w i l l ente r t he LM and separate from theCSM using the S M - Reaction Control System (RCS). The LM

Descent Propulsion System (DPS) w ~ l le used for powered

descent to the lunar surface. The vert ical descent po rt ion of

the l anding phase w i l l star t at an al tltude of 150 feet. Restoeriods w i l l follow.

Flight Profile

Lunar Surface Operations - The staytime o n the luna r surfaceis planned at 21 hours, 33 minutes, and 21 seconds. Stay w i l l

include rest periods and EVA of 2 hours and 40 minutes at notov er 70 feet radius from the LM. Planned activities include

photography, TV, sample collection, LM inspection, assessmentof ast ronaut capabilities, and l imitations and experiment deploy-

ment.

Lunar Module Ascent - At the completion of the lunar surface

activities the LM-Ascent Propulsion System (APS) and the LM-

RCS w i I I be used to launch, rendezvous and dock to the CSM.The LM wi l l coast from insert ion to an elliptical orbit ( 9 X 45 NM)for one hour after which several maneuvers w i l l be made tobr ing the LM and CSM range to w i th in one nautical mile. Brak-

in g f rom this point w i l l be performed manually. Once docked to

the CSM the two LM Crewmen wi l l t ransfer to the CSMwith sam-

ples of lunar surface material. The CSM wi l l be separated from'

the LM using the SM-RCS.

Transearth Injection and Coast - The S P 5 w i l l be used to inj ec tthe CSM into the transeart htrajectory. Traosearth re tu rn time

wi l l be 63 hours, 51 minutes, 50'seconds. Dur ing th e trans-

earth coast Intermediate midcourse corrections w i l l be mede, i f

required, ut il iz in g the MSFN for navigation.

Entry and Recovery - P r i o r to atmosphere ent ry the Command

Module w i l l be separated from the Service Module using the SM-RCS The drogue parachute deployment sequence w i l l start at

a n altitude of 23,300 feet, the three main parachutes at 10,500

feet altltude. The nom~na lange from the ent ry interface at

400,(MO feet alt~tudeo touchdown will be 1285 nautical milesEarth touchdown wi l l be i n the Mid-Pacific.



LUNAR LANDING MISSION PROFILE '



MAJOR SCHEDULE AND COUNTDOWN EVENTS

T - 4 months, 2 weeks Erected Launch Vehicle S-IC,

S-11, SIVB, and I U

T - 3 months, 1week Erected Spacecraft CSM-107 and

and LM-5 - 'I. . 2:T - 2 months lnstalled SIC and LV 0 r d n a k e ' '

and LES and Transferred SV to

Pad A

T - 1month, 2 weeksConducted SV - Flight ReadinessTest - FRT

T - 1month Hypergolic Loading and RP-, . -21

loading of SV

T - 3 weeks

Countdown

T - 114 hours

Begin Countdown Demonstration

Test - Wet and Dry % '* s

Begin Countdown

T - 106 hours, 30 min. Monitor GH2 Facility and Provide GN2and GHe for Duration of Test

T - 93 hours

T - 89 hours

T - 85 hours

Begin Space Vehicle Ordnance Opera-t ions

Begin Launch Vehicle Ordnance Op-

erations

Provide SCAPE Support



APQLLO TRACKING - B e n C i men operate the Devil's Ashpit

station o n tiny volcanic-extinct Ascension Island , 5,mmiles

downrange from Cape Kennedy. Th is is one of the 12 sfations

maintained and operated fo r NASA's Goddard Space Fl ight Center

by th e Bendix Field Engineering Corporation.

Countdown

T - 25 hours

T - 24 hours

T - 22 hours

T - 20 hours

T - 15 hours, 45 min.





T - l l hours


Validate Astronaut Vans

Inspect MSS for Travel Configura-

t ion

Activate First In du st ri al Water Engine

and Bri ng Up to Speed

l stall and Soap Plywood Surface atPad

Start and Stabilize Crawler Transporter

Secure Hammerhead Crane fo r Launch

Pressurize and Leak Check GH2 Cross

Country Lines

Propel CIT to Top of Ramp

Propel CIT to Mate MSS

Jack CIT to Mate MSS

lns ta ll and Soap Plywood Surface at

MSS ParksiteRelease Weather Balloon

Jack MSS up to Clearance Height

T - 10 hours, 15 min. Propel MSS to Parksite

T - 9 hours, 45 min. Provide Generator Support at CCFUn ti l End of Miss ion

T - 9 hours, 30 min. Verify 11 Scott Air Packs in the ECS

Room and 23 i n he Blast Room



countdown

T - 9 hours


T - 8 hours

T - 7 hours



T - 6 hours




T - l hou r

T- 7 min.

*T - 3 min.

*T - 2 min., 47 sec.

*T - 1min., 37 sec.

Begin Bui l t - in Hold of 6 hoursSlide Wire Preps Complete and

Ready to Support

Begin LV Propellant Loading

Begin LV Cryogenic Loading

Clear Route for Astro Van Activate

2nd and 3rd Industr ia l Water Engines

MSS Mated at Parksite

MSS is Hard Down o n Mounts

Release Weather Balloon

MSS Parksite Clear of Personnel

Prime Crew Enter Astro Van at MSO

B dg.

Crew Ingress at C-39 Pad A

Support RP-1 Fuel Level Pdjust merito n LV

Verify GO for Launch

Terminate LV Liquid Oxygen and

Hydrogen Replenishment

pressurize S-IVB LOX Tank

pressurize S-IC, S-l I and S-IVB

Fuel Tanks

Countdown.

'T - 1 min., 22 sec. Pressurize S-I I Liquid HydrogenTank

"T - 1min., 12 sec.

T - 1 min.

'T - 40 sec.

Pressurize S-IC LOX Tank

Pad I nd us tr ia l Water On

Flame Deflection Cooling WaterOn

T - 9 sec.

T - 2 sec.

Ig ni ti on Sequence Start

A l l 5 Engines Runn ing

"May not be exact time - actual countdown not available atth is time.



FIRST DAYWednesday

T - 9 sec. l g n i t i o n C om m an d

T - 0

T t 2 m in., 14 sec.

T t 2 m i n . , 40 sec.

T t 2 m in . , 41 sec.

T t 2 m i n . , 42 sec.

T t 8 m in . , 50 sec.

T t 8 m in ., 51 sec.

T + 11m i n . , 2 1 sec.

L i f t o f f

IS - I C I n b o a r d E n g i n e C u t o f f (1 )

S- I C O u t b o a r d E n g i n e C u t o f f ( 4 )

S - IC IS - I I Separa t i on

S - l l ( 2nd S tage) l gn i t i on

Je t t is on La un ch Escape Tower (LET)

S- I En g ine C u to f f (51

S - I I I S - I V B S e p a ra tio n

S- IVB (3 rd S tage) 1st l g n i t i o n

S - I V B V e l o c i ty C u t o f f - O r b i t

I n s e r t i o n - 1 00 N M

T t 2 h r s . , 44 m i n . , 18 sec. S - I V B 2 nd l g n i t i o n o n 2 n d R e v o l u t i o n

T t 2 h r s . , 49 rnin., 3 9 sec. S - I V B C u t o f f - T r a n s l u n a r I n j e d i o n

(TLI )

T t 3 h r s . , 1 2 m i n . C S M S e p a ra tio n f r o m S - I V B I IU I L M - 5

a n d T ~ a n ~ p o ~ i t i o n

T t 3 h r s . , 2 2 m i n . D ock C S M w i t h L M

T t 4 h r s . , 10 m i n . E jec t LM f r o m S- I V B

T t 4 h r s . , 39 m i n . , 37 sec. Evasive M a n e u v e r - SPS l g n i t i o n o f

C S M I L M

FIRST DAY

T + 4 h r s . , 49 m i n .

T t 7 h r s .

T t 1 1 h r s , 1 6 m i n .

T + 19 h rs .

SECOND DAY

Th u r s d a y

T + 26 hrs . , 3 m i n .

T + 43 h rs .

S- I V B 3 r d l g n i t i o n - S l i n g s h o t

M a n e u v e r - O r b i t S - IV B I I U A r o u n d

S u n

39,Wc N M f ro m E ar th

M i d c o u r s e C o r r e c t i o n Ma n e u v e r N o . 1

(MCC #1)of CSMILM-5

SF,00'! N M fr o m Ea r th

M C C % 2 ( i f r e q u i re d )

150 ,DM NM f r o m E a r th

T H I R D D A Y

F r i d a y

T + 53 h rs . , 55 m in .M C C 8 ( i f r e q u i re d )

T t 5 6 h r s . , 17 mi n . L u n a r M o d u l e P i l o t (L M P) - t n t r a -V e h i c u l a r T r a n s f e r ( IV T ) t o LM

Commander (CDR) - Trans fe r Equ ip -

m e n t to L M P i n L M

T + 5 7 h r s . , 5 m i n . CDR - I V T t o L M

T + 5 8 h r s . L MP a n d C DR r e t u r n to C S M 180,000

N M f r o m E a r t h

T + 70 h r s . , 55 m i n . M C C W ( i f r e q u i r e d )



FOURTH DAY

S a t u r d a y

G O-N O-G O f o r L u n a r O r b i t I n s e r t i o n

-#I1011)T + 73 h r s .

T t 75 h r s , 55 m i n , 03 sec. 'Loll M N M X 170NM

O r b i t B u r n T ime - 6 m i n . , 5 sec.

T t 80 h r s . , 10 m i n L u n a r R e v o lu t io n # 3

T + 80 h r s . , 12 m i n , 01 sec. LO12 m N M X @ N M O r b i t B u r n T i m e -

14 sec

T + 81 h r s . , 48 m i n .

T t 83 h r s . , 48 m i n LM P - R e t u r n s to C S M

L u n a r R e v o l u t io n $5

LM P - I V T t o L M

T + 84 h r s . , 07 m i n .

T + 94 h r s . , 26 m i n .

T + $4 h r s . , 5 0 m in . C D R - I C T t 0 L M

FIFTH DAYS u n d a y

T + 97 h r s . , 30 m i n . GO-NO-GO for Undock ing

T + 97 h r s . , 58 m i n . L u m r R e v o l u t i o n #12

T + 98 h r s , 18 m i n . U n d oc k L M f r o m C S M

T + 98 h r s . , 43 m i n L M S e p a r a ti o n f r o m C S M

T + 99 h r s . , 42 m i n . , 27 sec. D e s ce n t O r b i t I n s e r t i o n (D O!) B u r nTime - 35 sec.

T + 100 h r s . , 38 min. , 57 sec. P D I

T + 100 h r s . , 5 0 m in . , 5D sec. T o uc hd o w n o n M o o n

FIFTH DAY

T + 100 h r s . , 54 m i n . GO-NO-GO for 7 min . S tay

T + 101 h r s . , 01 m i n . GO-NO-GO f o r 1L u n a r R e v o lu t i o nof C S M

T + 101 h r s . , 52 m i n . L u n a r R e v o lu t i o n #14 f o r C S M

T + 102 h r s . , 10 min . GO-NO-GO fo r L u n a r Stay - LMT + 108 h r s . , 32 m i n . B e g i n p r e p a r a t i o n s fo r Egress

T + 109 h r s . , 50 m i n . L u n a r R e v o lu t io n #18 f o r C S M

T + 110 h r s . , 30 min . CDR - S t a r t E x t r a v e h i c u l a r A c t i v i t y

(EVA)

T + 110 h r s . , 40 m i n . CDR - ln i t i a l EV A w i t h L MP A s s is -

t a n ce a n d M o n i t o r i n g S e qu en ce cCamera - TV

T + 110 h r s . , 55 m i n . C o n t i n g e n c y S a m ple C o l l e c t i o n

T + I l l h r s . , 08 m i n . CDR - Rest a n d Pho tog raph LMP - EVA

T t 111 h r s . , 30 m i n . N D e p lo y m e n t q o l a r W i n d C o m p o n e n t

(SWC) Deployment B u l k Sample Col-l e c t i o n EVA an d E n v i r o n m e n t Evalua-

t i o n

T + 111 h r s . . 42 m i n . P e r f o r m L M I n s p e c t io n

T + I l l h r s . , 45 m i n . L u n a r R e v o lu t io n #19

T + 112 h r s . E a r l y Apo l lo Sc ien t i f i c Equ ipmen t Pack-age IEASEP) Deployment

T + 112 h r s . , 08 m i n . D o c u m e n t e d S a m p le C o l l e c t i o n



FIFTH DAY

T + 112 h r s . , 40 m i n . LMP - E VA Te rm i na t i on

T + 112 h r s . , 45 m i n .

T + 113 h r s .

T + 113 h r s . . 43 m i n .

T + 114 h r s . , 21 m i n .

CDR - Rock an d Tra ns fer Sample Re-

t u r n C o n t a i n e r (SRC)

CDR - E V A Te rm i na t i on

(To ta l EVA -2

h r s . , 40 m i n )

L u n a r R e v o l u tio n #a C S M

J e t t is o n S u r p l u s E q u ip m e n t E at a n d

Rest

S I X T H D A Y

M o n d a y

T + 122 h r s . , 28 m i n . , I1 sec. L W A S - L i f t o f f - A s c e n t P r o p u l s i o n

(A P S ) S ys t em - B u r n T im e - 400 sec.

T + lT2 h r s . , 35 m in ., 25 sec. O r b i t I n s e r t i o n o f L W A S

T + 123 h r s . , 26 min . , 27 sec. LM-RCS-Coe l l i p t i c Sequence

I n i t i a t i o n M a n e u v e r-

( C S I ) B u r nTime - 46 sec.

T + 123 hrs . , 25 min . , 27 sec. C S M Ba ck up C S I B u r n

T + 124 h r s . , 24 min . , 25 sec. LM-RCS Cons tan t De l ta A l t i t ude

M a n e u v e r (C DH ) B u r n T im e - 2.8 SeC.

T + 124 h r s . , 27 m i n . , 25 sec. C S M B a ck up - CDH B u r n

T + 124 h r s . , 02 m i n . , 46 sec. L M-R CS T e r m i n a l P h a s e i n i t i a t i o n

M a n e u ve r (T PI) B u r n T im e - 23.3

T + 125 h rs . , 17 m i n . , 46 sec. LM- RCS-M CC #1

S I X T H D A Y

T + 125 h r s . , 32 m i n . , 46 sec. LM-RCS-MCC #2

T + 125 h r s . , 42 min . , 22 sec. LM -R CS B r a k i n g M a n e u v e r s B u r nTime - 1.5 sec., Range - 1.0 N M

T + 125 h r s . , 44 m i n . , 05 sec. LM-RCS B r a k i n ~ M a n e u v e r s u r nT i m e - 9.6 sec . , Range- .5 N M

T + 125 h r s . , 45 m i n . , 14 sec. LM -R CS B r a k i n g M a n e u v e r s B u r n

Time - 9.0 sec., Range - . 2 N MT + 125 h r s . , 47 m i n . , 02 sec. LM-RCS B r a k i n g M a n e u v e r s B u r n

T i me- 4.3

sec.,

Range- .08

N M

T + 125 h r s . , 48 min . , 03 sec. LM-RCS B r a k i n g M a n e u v e r s B u r nT i me - 4.2 sec. , Range - 0.3 N M I

T + 126 h r s . L M A c tlv e D o c k in g w i t h C S M

T + 126 h r s . , 48 m i n . CDR - I V T t o C S M

T + 127 h r s .

T + 128 h r s .

LM P - I V T to C S M

Jet t i son LM-AS

T + 129 h r s . , 32 mi n . L u n a r R e v o l u tio n #28

T + 131 h r s . , 28 min . , 43 sec. T r a n se a r th I n s e r t i o n (T EI) B u r n T im e

S PS - 2 min . , 20 sec ., L u n a r Revo lu -t i o n #29

SEVENTH DAYTuesday

M C C #5 ( i f r e q u i r e d )+ 148 h r s . , 32 mi n .



EIGHTH DAYWednesday

T + 172 h r s . , 58 m in . MCC #6 ( i f req u i red )E a r th i n s e r t i o n (E l ) - 22 h r s .

N I NT H DA Y

T h u r s d a y

T + 1 92 h r s . , 0 6 m in . MCC #7 ( i f r e q u i r e d )

E I 3 h r s .

T t 194 h r s . , 57 m i n . C M i S M S e p a ra tio n

T t 195 hrs . , 06 m i n . , 27 sec. E a r t h I n s e r t i o n - A l t i t u d e - 4n0,%0 ft.

T + 195 hrs . ,0 6 m i n . , 5 3 sec . E n t e r , S -B a n d B l a ckb u t

T t 195 h r s . , 07 min , , 5 1 sec. A s t r o n a u t s E xp e r ie n ce P ea k G Force

T + 195 h r s . , 07 m i n . , 5 3 se c . Ex i t . S -Band B lackout

T + 195 h r s . , 15 rn in. D ro g u e C h u t e s De p l o ym e n t 2 3,3 00

feet a l t i tude

T t 195 h r s . , 15 m in . , 49 sec. D r o g u e C h u t e s D i sc o n n ec t a n d 3 M a i nParachu tes Dep loy a t 10,500 eet a l t i -

t u d e

T t 195 hrs., 20 m i n . , 42 sec. S p l a sh d o wn - Pa c i f i c Ocean

FOOT STEPS ON THE MOON - Apol lo 11a s t r o n a u t s w i l l c a r r y

t h i s se l f - co n t a i n e d s e i s m i c s t a t i o n a s p a r t o f th e Ear ly Apol lo

Scientific E x p e r i m e n t a l Package (EASEPI, to be placed o n th e

moon. W h e n opera t i ng , t h e se i sm o m e t e r m ay t r a n s m i t to

e a r t h l i s t e n e r s t h e s o u n d o f t h e a s t r o n a u t ' s footsteps.

Ron Redick, o f t h e B e n d i x C o r p o r a t ~ o n ' sAerospace Systems

D i v i s i o n , A n n Arbor . M i c h ~ g a n , s i m u l a t e s t h e moon deploy-

m e n t .

apollo 11 mission profile

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