Apollo 8 Mission 3 Day Report

8/8/2019 Apollo 8 Mission 3 Day Report

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N A T I O N A L A E R O N A U T I C S A N D S PA CE A D M I N I S T R A T I O N....................................................................................................................................................................................................................................................................................................................................................................................................................................................................................................................................................................................................................................................................................................................................................................................................................................................................................................................................................................................................................................................................................................................................................................................... . . . . . . . . . .................................................................. . . . . . . . . ....................................................................................................................................................... . . . . . . . . . ................................................................................................................................. . . . . . . . . . .................................................................................................................................................................................... . . . . . .. . . . . ................................... . . . . . ........ . . . . . . ........ . . . . . .. . . . . ............................................ . . . . . . . . . .. . . . . . . . . ....................... . . . . . . . . . . .. . . . . . . . . .. . . . . . . . . . .. . . . . . . . . .............. . . . . . . . . .......................

APOLLO 8 MISSION3-DAY REPORT

I$r"c' '

.............. (NASA-TM-X-70002) APOLLO 8 BISSXON: 3

........ D A Y BEPOBT (NASA) 17 p

. . . . . . . . . . . .. . . . . . . . . . DISTRIBUTION AND RE FEREN CING. . . . . . . . . . . .. . . . . . . . . . This paper is not suitoble fo r general distribution or referencing. It may be referenced

...................... only in other working correspondence and documents by porticipoting orgonizotions.

M A N N E D S P A C E C R A F T C E N T EHOUSTON .TEXASDECEMBER 1968............ . . . . . . . . . ....................... . . . . . . . . .................................. . . . . . . . . . ............. . . . . . . . . .. . . . . . . . . . ........................ . . . . . . . . .. . . . . . . . . . .. . . . . . . . . .. . . . . . . . . . ............ . . . . . . . . . ...........

874-724

Un c l a s00/99 16744


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MSC-PT-R-68-4 5rl

APOLLO 8 MISSION3 DAY REPORT

PREPARED BY

Apollo 8 Mission Eva lua t ion Team

APPROVED BY

George M . LowApollo Spacecraf t Program

NATIONAL AERONAUTICS AND SPACE ADMINISTRATIONMANNED SPACECRAFT CENTER

HOUSTON, TEXASDecember 1968


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SUMMARY

The Apollo 8 space vehicle w a s launched from Kennedy Space Center,F l o r i da , at 7:51:00 a.m. e . s . t . on December 21, 1968, a f t e r a s a t i s f a c -t o r y no-hold countdown. Following a nominal boost phase, t h e spac ecr aftand S-IVB combination w a s i n s e r t e d i n t o a pa rk i ng o rb i t o f 98 by 103 nau-t i c a l z i l e s . Af%er a post-insert ion checkoii t of spacecraf t sys t ems, thet ran s lun ar in j ec t io n maneuver was i n i t i a t e d a t 02: 0 :36 by r e i gn i t i ngt h e S-IVB engine, and th e nominal maneuver l a s t e d f o r 5 minutes and6 seconds.

The spa cec raf t s epara ted from th e S-IVB a t 03:20:55, follow ed by twosep ara t ion maneuvers using th e ser vic e module rea ct io n con t rol system.The f i r s t midcourse correct ion of 24.5 f't/sec w a s conducted a t 10:59:58.The t ra ns lun ar coast phase was devoted t o navigat ion s ig ht i ng s, two te le -vi si on transm iss ions , and various systems checks. The second midcourseco r rec t i on , cons i s t i ng o f 1.9 f' t /sec , was con ducted a t 60 :59 54.

The 246.5-second dur at io n lun ar o r b i t in se rt io n maneuver w a s per-formed a t 69:08:20, and t h e i n i t i a l l u na r o r b i t w a s 168.5 by 59.9 n. mi.A maneuver t o c i r c u l a r i ze t he o rb i t w a s conducted a t 73:35:06 and resu l t ei n a l u n a r o r b i t of 59.7 by 60.7 n. m i . The coast phase between maneuverw a s devoted t o o rb i t n avigat ion and ground t r ac k determinat ion.of te n re vol ut io ns were completed during th e 20 hours 11minutes spent i nl u n a r o r b i t .

A t o t a l

.The lunar orbi t coast phase involved numerous landing-si tehandmarks i g h t i n g s, unar photography , and prepa ra t ion f o r t ran sea r th in j ec t io n .The t ransearth inject ion maneuver, 203 seconds i n durat ion , was conducteda t 89 :l9 :16 using the service propulsion system.Dur ing bo th th e t rans luna r and t rans ear th coas t phases, pass ivethermal control maneuvers o f about one rev olu t io n per hour were eff ec te dwhen pos sib le t o maintain temperatures w ith in nominal l i m i t s . The trans-

ear th coas t per iod involved a number of s t ar /h oriz on na vigat io n s igh t in gsusing bo th t h e e ar th and moon horizons.co r rec t i on w a s a 4.8 ft/sec maneuver made at 103:59:53.The only transearth midcourse

Command module/service module separation w a s a t 146 :29 00 , and thespacec ra f t r eached t h e en t ry i n t e r f ace (400 000 f e e t ) a t 146:46:13.low ing normal deployment of a l l pa r a ch u te s , t h e s p a c e c r a f t la nd ed i n t h ePaci f ic Ocean a t 08O 08' N l a t i t u d e and 165' 02' W l ongi tude , as dete r -mined by t h e primary re covery shi p.146 hours 59 minutes 49 seconds, and t h e spacecraf 't and crew were re -covered by th e USS Yorktown after landing.

Fol-

The t o t a l f l i gh t du ra t ion was


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Almost without exception, spacecraft systems operated as in tended.A l l temperatures var ie d with in acceptable l imits a n d e s s e n t i a l l y e x h ib i t e dpr ed ic te d behavior. Consumables usage w a s always maintained a t a s a f el e v e l . Communications quality w a s except ional ly good, and l i v e t e l e v i s i o nw a s t r an smi t ted on s i x occas ions .fl ight-plan functions and achieved all photographic object ives .The crew s at is fa ct o r i ly performed a l l


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INTRODUCTION

The evaluat ion i n t h i s r e p o r t i s based on pre l iminary data , and th es t a t e d v al ue s are s u b je c t t o c hange i n l a t e r r e p o r t s . All times arer e f e re n c e d t o ra ng e z e r o, t h e i n t e g r a l s ec on d b e f o r e l i f t - o f f , w hich w a s12:51:00 G . m . t . , December 21, 1968.

A l l spacec ra f t sys tems per fo rmed s a t i s fa c t o r i l y throughout th ef l ig h t , and on ly th e more s ign i f i ca n t in fo rmat ion i s presented underappropriate systems headings.a l l y as intended and w i l l no t be d is c us se d u n t i l l a t e r r e p o r t s :d i s t r i b u t i o n , s e q u e n t i a l , d i sp l ay s and c o n t r o l s , ea r th landin g, and pyro-techn i cs . The i n i t i a l d i scuss ion of the crew medica l eva lua t ion w i l la pp ea r i n t h e ne xt o f f i c i a l r e p o r t .

The following systems performed essenti-power


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TRAJECTORY

Li f t -of f of th e Apollo 8 mission occurred a t 12:51:00.9 G . m . t .(07:51:00.9 a.m. e.s . t . ) on December 21, 1968, wi th subsequent o rb i t a li n s e r t i o n a t 00:11:38.f l igh t -pa th angle was 0.00 degrees , and a l t i t u de was 102.6 n. m i . Theres u l t a n t pa rki ng-o rbi t e lements a re g i ven i n t ab l e I.

A t o r b i t a l in s e r t i o n , v e l o c i t y w a s 25 567 f t / s e c ,

T rans l una r i n j ec t i on w i th t he S-IVB w a s i n i t i a t e d a t 02:50:36, andspacecraft /S-IVB se pa ra t io n occurred a t 03:20:55. Following a per iod ofsta t ion-keeping, a s m a l l re ac t io n con t ro l system maneuver w a s made t oi n c r e a s e t h e s e p a r a t i on d is t an c e f r o m t h e S-IVB. Because of S-IVB prox-i m i t y , an add i t i ona l t h ru s t i ng u s i ng t he r eac t i on con t ro l sy s t em w a s per-formed t o increase th e sep ara t ion dis t anc e. These maneuvers are summar-i z ed . .& t a b l e 11.

Only two midcourse co rrect io ns were req ui re d i n the t ra ns lun ar por-t i o n of f l i g h t , 24.5 f t / s e c a t approximately 11 hours and 1 .9 f t / s e c a tabout 6 1 hours .co r rec t i on w a s 63.4 n. m i .s t a g e s ; t h e i n i t i a l o r b i t , made w it h a maneuver of approximately 3000 ft/s e c , w a s 60 by 170 n. mi., and th e f i n a l lunar orbit , made with a maneuverof 134.8 f t / s ec , w as nea r l y c i r cu l a r at 60 n. m i .mainta ined for about 4-1/2 hours , and th e f in a l o r b i t f o r an a d d i t i o n a l

The per i cynth ion a l t i t u de re su l t in g from th e secondLunar o rb i t i n se r t i on was performed i n two

The i n i t i a l o r b i t w a s15-1/2 hours.

The t ra ns ea rth in je ct io n maneuver w a s performed a t 89 :19 :16, l a s t e dfor 303 seconds, and r e s u lt e d i n a v e l o c i t y change of approximately3500 f t / sec.midcourse co rr ec t io n was re qui red a t about 104 hours t o ach ieve t a rg e te dent ry condi t ions . Command module/service module separation w a s e f f e c t e da t 146:29 : OO .

The accu racy of t h i s maneuver w a s such tha t on ly a 5 f t / s e c

Ent ry in t e r face (400 000 f e e t a l t i t u d e ) o c cu rr ed a t 146 :46 :13, withLanding occurredsubsequent landing a t 146:59:49.36 221 f t / s e c and a f l ight -path angle of -6.5 degrees.at 08O 08' N and 1 6 5 O 02' W longi tude, based on recovery ship coordinates .

Event t imes for t h e mission ar e shown i n ta b le 111.

The entry condit ions were a ve l oc i t y o f


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CRYOGENICS

BATTERIES

The cryogenic s to rage system performed sa t i s f ac to r i ly throughoutt h e mission , and usage w a s s l i g h t l y l e s s t h a n pr e d ic t e d. A l l h e a t e r s wereoperated automatically and a l l fans were cycled manual ly t o preclu de t heac bus-voltage problem caused by th e ar ci ng motor sw itch not ed on Apollo 7 .Qua nt i ty balancing between t he resp ect iv e cryogenic tanks w a s s a t i s f a c t o r y .

COMMUNICATIONS

The ov er al l performance of th e spacecraft-to- network communicationsystem w a s nominal. The rece ived downlink c a r r i e r power, tele me tr y, andvoice performance c or re sp on de d t o p r e f l i g h t p r e d i c t i o n s .Communications system management, in cl ud in g antenna sw itc hin g du rin g

the miss ion w a s very good. Communications during pa ssi ve ther mal co nt ro lwere maintained by s eq ue nt ia ll y swi tchi ng between t h e fo ur omni antenn as,switching between d iam etr ica lly opposite omnis , or switching between thehigh-gain antenna and one or more omni antennas. A l l four omni antennasand t h e high-gain antenna were se le cte d per i odi cal ly ,with performancee q ua l t o or g r e a t e r th a n p r e f l i g h t p r e d i c t io n s .gain antenna were used successfully. A l l modes of t h e high -

The da ta qu al i t y of both high- and low-bit-ra te tele metr y w a s good.High-bit-rate telemetry w a s rece ived through th e 85-foot antennas a tslant ranges of up t o 160 000 n a u t i c a l m il es w h i le t h e s p a c e c r a f t w a str an sm it ti ng on omni antennas.The voice qua li ty , both normal and backup, received throughout t he

mission w a s excel lent . The MSFN s i t e s repo r ted rec ei pt of good-quali tytele metr y da ta during da ta sto rage equipment dumps.Communications were s a t is fa ct or y dur ing en tr y u n t i l b lackout a t146 : 6 :38. Air-to-ground voi ce con tac t w a s r e e s t a b l i s h e d a t approximately


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146:52 through th e Apollo Range Instrumenta tion Ai rc ra ft .town es ta bl is he d voice contact during parachute descent.la nd in g vo ice communications were momentarily in te rr u p te d when th e space-c r a f t w a s i n a s t a b l e I1 f l o t a t i o n a t t i t u d e , t h e r ec ov er y o p er a t io n w a ssa t s a c t o r i ly suppor ted .

The USS York-Although post-

A t o t a l o f s i x t e l ev i s io n t ransmiss ions were made dur ing th e f l i g h t .For t h e f i r s t t e l e c a s t , t h e t e le p ho t o l e ns (100 f o c a l length) vas usedt o view t h e ear th . Because of camera motion and th e high er tha n expectedl i g h t i n t e n s i t y o f t h e e a r t h , t h e p i c tu r e s w ere o f ve ry p oo r q u a l i t y .procedure for use of the f i l t e r s from t h e Hasse lblad camera w a s developedand subsequen t t e le ca s t s o f th e ea r th us ing the t e lepho to lens wi th a re df i l t e r were sa t i s f ac to ry . Excel lent views of th e luna r surfa ce were takeni n lunar o rb i t us ing the ex tra-wide-ang le l ens ( 9 mm foca l l eng th) ands u i t a b l e f i l t e r s .

A

INSTRUMENTATICN

The d at a sto ra ge equipment and instrum enta tion system performancew a s sa ti sf ac to ry throughout the mission, and only th re e measurementsf a i l e d .

The f u e l c e l l 2 rad ia to r -ou t le t t empera ture ind ica ted a temperature6 t o 1 2 degrees higher than expected.f u e l c e l l and r a d ia t o r w a s ve ri fi ed by o th er system measurements, t h u sin d i c a t i n g a f a i l e d se n so r .

Proper system performance of t h e

The r ad ia tor-out l e t temperature measurement i n t h e environmenta1con t ro l sys tem fa i led a t approximately 120 hours elapsed t i m e and wentt o fu l l - sca le read ing . Systems ana lys i s ve r i f i ed p roper rad ia t o r opera-t i o n .

The measurement o f po tab le water qu an tit y i n th e ECS ap pare ntlyf a i l e d a t approximately 145 hours e lapsed. t ime. Normal tank-pressuriza-t i o n and water production d at a ind ica ted th e measurement t o be question-a b l e .

GUIDANCE AND CONTROL

Performance of t h e guidance and c ont rol system w a s excel lent through-out the miss ion. A l l monitoring functions and navigation comparisonsr e q u i r e d d u rin g a s c e nt , e a r t h o r b i t , and t r a n s lu n a r i n j e c t i o n were nor-m a l , Platform alignments were performed during a l l coa st phases with


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good resu l t s .alignments , in di ca te performance with in one-sigma va ri at io ns . Acceler-ometer b i a s measurements made throughout t h e mission a l s o in d ic a te sta-b i l i t y w e l l w it h in one sigma. Onboard midcourse navigation techniqueswere thoro ughly ex er ci se d. Sta r-h ori zon measurements were made du rin gt r ans l una r and t r ansea r t h coas t , and prel im inary comparisons in di ca teclo se agreement wi th ground t ra ck ing . Onboard o r b i t a l naviga t ion w a sperformed i n lunar o r b i t wi th nominal r es u l t s .

Gyro b i a s d r i f t e s t i m a t e s , made from ev al ua ti n g suc ces siv e

S p ac e cr a ft a t t i t u d e c o n t r o l was s a t i s f a c t o r y u sin g b ot h t h e d i g i t a la u t o p i l o t and t he s t a b i l i z a t io n and con t ro l syst em. Serv ice propul sionmaneuvers were performed u sin g t h e d i g i t a l a u t op i l o t wi th nom inal resul ts .Entry guidance and navigat ion w a s e x c e l l e n t .Two guidance and con tro l system problems occ urred d uring th e mission.

The f i r s t involved abnormal s h i f t s i n t h e computer readout of t he op t ic st runnion angle . Severa l t imes during per iods of no op t i cs a c t iv i t y , t h eread-out sh if te d from 0 t o 45 degrees.w a s re st or ed wi th a normal op t ic s zeroing procedure, and no op t ic s u t i l i z a-t i o n c a p a b i l it y w a s l o s t .or ato ry by inducing a malfunction i n th e read c i r c u i t of the opt ics coup-l i n g da ta u n i t .

In each case , t h e cor r ec t read ingThe symptoms have been du pli ca ted i n th e lab-

REACTION CONTROL SYSTEMS

A l l co da nd and ser vic e module re ac t io n co nt r ol system parameterswere normal throughout t h e mission.The t hermal cont r o l sys tem in th e se rv ic e module r eac t ion co nt r o l

system maintained package tem peratu res w it hi n nominal l i m i t s . All regu-l a t e d pressures w e r e normal and propellant usage w a s within acceptablel i m i t s d ur in g t h e f l i g h t . A t o t a l of 654 pounds of pr o pe ll an t were usedduring the mission w i t h 94 pounds used i n luna r o r b i t .

SERVICE PROPULSION SYSTEM

Four maneuvers were accompl ished using t h e s er vic e propulsion system,the longest being the 246.5-second lunar or b i t i n se r t io n maneuver, andsystem operat ion w a s s a t i s f a c t o r y . All maneuvers were no-ullage s t a r t s .

A momentary drop i n chamber p re ss ur e w a s expe r ienced ea r l y i n t hef i r s t se r v ic e propu lsion maneuver which w a s a t t r i b u t e d t o t h e pre sen ceof a s m a l l helium bubbl e i n t he ox i d i ze r f eed l i ne . This bubble i s


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t hough t t o have r e su l t ed from an inadequate engine-oxidizer bleed duringpr ef l i g ht ser vic ing . The chamber pre ssu re w a s sa t i s f ac t o ry t h roughou tt h e r em ai nder o f t h e t h e burn and f o r t h e t h r ee subsequent maneuvers.

Feed-l ine temperatures were more favor able than a nt ic ip at ed andremained reasonably steady wi th in th e i r upper and lower re d l i ne l i m i t s .A s a r e su l t , no heater operat ion w a s requi red .

ENVIRONMENTAL CONTROL SYSTEM

Performance of t h e environmental co nt ro l system w a s s a t i s f a c t o r y .The r a d i a t o r s s a t i s f a c t o r i l y r e j e c te d t h e s p a c e c r a f t h e a t l o ad s d u ri ngt h e t ranslunar and t ransear th coas t s , maintaining water/glycol temper-atu re s below th e evaporator turn-on le ve l . The evaporators were t h e r e f o r et u r n e d o f f d u ri ng t h i s t i m e . The primary evaporator w a s used i n t he aut o-mat ic mode during lun ar o r b i t . Evaporator dryout occurre d se ve ra l t imes ;however, t h e dryout d id not impose any r e st r a in ts on th e mission. Evapo-ra tor d ryout occurred on Apollo 7 at low he at loa ds and w a s a n t i c i p a t e dt o occur on Apollo 8 under similar l oad condi t ions . The evaporator w a sr e se rv i ced a t t h e end o f t h e f i r s t o r b i t and o p er a te d s a t i s f a c t o r i l y u n t i levapora tor d ryout recurred dur ing th e fou r th or b i t . The evapora tor w a saga i n r e se rv i ced and o p e r a t e d s a t i s f a c t o r i l y f o r t h e remainder of lun aro rb i t a l f l i g h t . P rimary evapora tor d ryout occurred aga in dur ing en t ry ;however, th e crew ac t i va te d t h e secondary coola nt loop, which operate dproperly throughout ent ry and maintained normal cabin temperatures near6 1 O F. and t h e suit -heat -exchanger out le t -gas temperatures near 4 4 O F.The fa ns , which were not needed dur ing t h e missio n, were no isy when ac ti -va ted on th e occas ion t o c i rc u la t e the cab in a tmosphere fo r a v a l i d c a b i ntemperature reading.

CREW PROVISIONS

A l l crew equipment operated s a t i s fa c to r i l y during th e mission. Exces-si v e noise on th e Lunar Module Pi lo t ' s e lect rocardiogram w a s co r rec t edwhen harnesses were swapped.f rayed bu t usab le .

The as t ro nau t s ' boo t s were r epor t e d t o be


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FLIGHT CREM

The Apollo 8 mission w a s accompl ished es se n t i a l l y i n accordance wi thth e nominal f l i g h t plan, wi th th e fol lowing minor except ion s.The S-IVB sepa ra t i on rate f rom the spacecraf t w a s l e s s t han p red i c t ed ,

and the crew spent a l onger time i n keep ing th e S-IVB i n s igh t and even-t u a l l y us ed a n add i t ion a l r eac t ion cont ro l syst em maneuver t o in cre asesepara t ion d i s t ance .Because of t h e h eavy work l o a d i n l u n a r o r b i t , t h e o r b i t a l a c t i v i t i e s

af t e r th e e igh th revolu t ion were sharp ly reduced t o a l low the crew t o g e tsome r e s t . N o r m a l ac t i v i t i e s were resumed i n p repa ra ti on fo r t he t r ans -e a r t h i n j e c t i o n , a f t e r which the f l i g h t p l an w a s aga in modif i ed t o a l lowfo r add i t i ona l c rew re s t . A t about 100 hours t h e m i ss ion r e t u rned t o t h enominal f l i g h t plan w i t h only minor resched uling of r e s t and m e a l pe r i ods .

Desp ite the long duty ho ur s, crew performance w a s good throughoutt h e mission, and many valua ble ob serva t ions of th e lun ar s ur fa ce and i t senvironment were made.Entry and landing were performed i n dar kness , with no apparent prob-lems. The sp ac ec ra ft assumed a s t a b l e I1 (apex down) f l o t a t io n a t t i t ud e

upon landing approximately 5200 yards from USS Yorktown, and t h e crewsuccessfu l ly re turned t h e v e h i cl e t o t h e u p ri g ht f l o t a t i o n p o s i t i o n . Adec isio n had previou sly been made t o delay t h e deployment o f swimmersun t i l . day l igh t ; t he re fo r e , crew t ra ns fe r t o th e prime recovery sh ip byhel icopter occurred about 80 minutes a f t e r l and ing .


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MISSION SUPPORT PERFORMANCE

FLIGHT CONTROL

Fl i gh t con t ro l suppo r t w a s exce l l en t dur ing the Apol lo 8 mission.

NETWORK

Network performance w a s exce l len t fo r t h i s m i s si on . A l l communica-t i o n s , ra ck in g , command, tele me try , and t h e real-time computation func-t i o n s s up po rt ed t h e m is si on s a t i s f a c t o r i l y wi th no s i g n i f i c a n t loss ofd a t a at any t i m e .

RECOVERY

Recovery of t h e Apollo 8 spacecraft and crew w a s su cc es sf ul ly com-p l e t ed i n t h e Pac i f i c Ocean by t he p rim e r ecove ry sh i p , t h e USS Yorktown.The major recovery events on December 27, 1968, a r e l i s t e d i n t h e follow-i n g t a b l e .

G . m . t . , hr:min(December 27)1 5 : 115: 315 : 915 116:4818:181 7: 0

EventF i r s t v i s u a l s i g h t i n g of s p a c e c r a f t by H a w a i i

Rescue 1Radar contact by USS YorktownF i r s t s i g h ti n g of CM f l as hi ng l i g h t by YorktownLandingF l o t at i o n c o l l a r i n s t a l l e d and i n f l a t e dAstronauts onboard recovery shipCM onboard recovery ship

Both S-band and VHF contac ts were e s t ab l i sh ed wi th t h e recovery for ceV i sua l con t act w it h t h e f l a sh i ng l i g h t and vo ice con tac t w it h t he f l i g h tcrew ceased at landin g, in di ca t i ng th a t t h e command module went i n t o as t ab l e - I1 pos i t i on be fo re up r i gh t ing .w i t h one bag r epo r t ed t o be onl y pa r t i a l l y i n f l a t ed .h e l i c o p t e r w a s d i r e c t l y o ve r t h e s p a ce c r af t as e a r l y as 16:08 G . m . t . , itw a s decided previously t o w a i t u n t i l day l igh t before deploy ing swimmers.

The uprighting bags were i n f l a t e d ,Although a recovery


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The per t inen t loca t ion da ta for t h e recovery opera t ion are l i s t e dbelow:

P red i c ted t a rge t coord ina tes

Retr ieval coordinates

08' 08", 1 6 5 O 02'w

08 0 7 . 5 ~ ~6 5 O 0 1 . 2 ~Sh ip pos i t i on a t landing"Estimated range t o space craf t a t l and ing 5200 yards0 8 O 09.3N, 165' 02.1N

*As determined aboard t h e recovery sh ip.

~~


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- .rl bD6 a,&' e hc c d

cd0

- 0 0 m M m ~. . . . . .. . . . . . . . . . . . . .o o t n m m \ c o mL n ; t - ; r L n V \ O M. . . . . . . . . . . . . .w mncur l l nm u \d l n

. .. . . .. . . .o \ Mc o o

rl

c0.rliJua,'13c-.-I rl cu

c0.dt-,ldkldm

r i c u Mc0TI-Pua,kk0 u - Pa,mk0a.rlz


16/17

TABLE 111.- APOLLO 8 SEQUENCE OF EVENTS

14

Event T i m e , hr:min:secILaunch phaseRange zero (12: 1:OO G . m . t . )L i f t o ffS-IC cen ter engine cu to ffS-IC outboard engin e cu to ffS-IC/S-II separationS-I1 engine ig ni t io nI n te r s t age j e t t sonLaunch escape tower j e t t i s o nS-I1 engine cu tof fS-II/S-IVB separationS-IVB engine i g n it i o nS-IVB eng ine c u t o f fI n s e r t o n

Orbi t a l phaseT rans l una r i n j ec t i on i gn i t i onT rans lunar i n j ec t i on cu t o f fS-IVB/Command module s ep a ra t io nSep ara tion maneuver 1Sep ara tion maneuver 2Midcourse correct ion 1 i g n i t i o nMidcourse correct ion 1 cu t o f fMidcourse correct ion 2Lunar o rb i t i nser t ion 1 i g n i t i o nLunar o rb i t i nser t ion 1 c u t o f fLunar o rb i t i nser t ion 2 i g n i t i o nLunar o rb i t i nser t ion 2 c u t o f fT ransea r t h i n j ec t i on i gn i t i onT ransea r t h i n j ec t i on cu t o f fMidcourse correct ion 3 i g n i t i o nMidcourse correct ion 3 cu t o f f

00 :00 :oo00:02 0600:02:34 I00:02:3400:02 500:03:0500:03:0900 :08: 400 0 : 500 08: 5

1

00:11:2500:11:35

02:50:3602 55 4203: 0 5503:40:0004: 5:0010 59 811: 0 :0160 59:5469:08:2069 2 :2773: 5:0673: 5 1689 19 1689 22 :3910 59104 00 7


17/17

.

TABLE 111.- APOLLO 8 SEQUENCE OF EVENTS - ConcludedJhen t

CSM/SM se pa ra t io nE n t ry i n t e r f ace (400 000 f t . )Begin blackoutEnd BlackoutDrogue deploymentMain parachute deploymentLanding

- T i m e , hr:min:sec I146 29 0146 6 3146 46 38146: 1: 44146 54 6146 55 20146 59:49

Apollo 8 Mission 3 Day Report

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