apollo briefings

8/4/2019 Apollo Briefings

1/84

NATIONAL AERONAUTICS AND SPACE ADMlNlSTRATlnN W i ) ?-dlWnSHlrclGTON, I3 C. on546 TELS- wr l -0*?FOR RELEASE1 IMMEDIATE

Monday, April 14, 1969SATURN MISSOW DOCUMENTUniveigih. ofAlabama Research /nsiH1.h~ f %.nu & TDdinoloay Gm

PARTICIPANTS-- - :GEORGE H. HAW, Deputy Apollo Program Directat,NASA HeadquarteraCO-I, THUMB M c W I X N , Aersistant Miaaion DirectorWILLIAM J. O*M)MELL, Asslatant Public Affaf rs Off icer ,

OMSF, NASA


2/84

0DOWNJSU Good afternoon.Before we begin with our briefLng, 9[ would like

t o W e a couple oi announcements.F i r s t , there will be prlnted transcripts providedof the b r ie f in g . If you are interw~tad n receiving one ofthese transcripts, please address a government envelope withyour own addres s . You will f lnd th e envelopes in the lobby.The second announcement in that a briefing on t h e

NASA portion of President Nfxon's amended f i s c a l 1970 Budgetwill be h e l d tomorrow, Tuesday, A p r i l 15, at 5 :00 p e w , ,Eastern Standard T im e , at the NASA Headquarters Auditorfum,sixth floor, FQB 6 , 400 Maryland Avenue, Southwest,

To begin t h f s af erncron?~acttvlties we w i l l havethe Apollo 10 mission briefing by Mr. George Hage, who ist h e Apollo Mi~sionDirector, also Deputy Director of theApollo Program.

With Mr. Wge is Colonel Tom McMullen, AssistantMfs~ion irector.George.

L a d i e s and gentlemen, we will pmsent the Apullo 10mission briefing today in three parts, 1 will etart it outwith a discussion of t h e mission up t o t h e p o i n t of rendez-voun, Colonel McMullen will discuss the details o f therendezvous, And I will take t h e mission from t h a t point onback to recovery.

As Many of you know, Apollo 10 is proceeding welltowards a launch readiness on May 18. The launch tAmeplanned llle 1 l r49 a e m . , Eastern Standard T i m ,The flight madiness tea t W ~ B uccessfully com-

p l e t e d on echedule last Thursday, A p r i l 9 .We have twa majlor remaining l e v e n t ~prior to OUFlaunch readiness status, General Phillips' f l i g h t readi-ness review w i l l be conducted a t Kennedy on t h e 22nd of


3/84

this month. The final test, as fn previous mbssions, isthe countdown demonstration test that is scheduled to s t a r ton th e 27th QP t h i s month, with completion of th e f i r s t parti n m l v l n g th e flawing of all th e cryogenfc pmpellaate onthe 2nd of Map, foBloued by n crew partictpating part oft h e countdown demonstration test on th e 3rd of May.With those i n t r d u ~ t o r y o mm e l a t ~ , 1 would l f k eto have th e ibmt s l l d e , please,( S l id e )'fha Apollo 10 is camposed of the configurationitems shown on the left:Saturn launch vehicle SA505.Command service d a l e 106,

The spacecraft lunar moduLe adapte~ o, 13.And w e w f l l , be using t h e Colossus 2 and theLumfnasy program .Ln t h e guidance computers of th e tw o space-craft, respectively .This will be th e f i rs t launch from h u n c h Complex39-B,The crew assignments, Colonel Tom Stafford i s

t h e Commander, Commander ,John Young is th e & m n d ModulePflot, Commander Gene &man IZn the Lunar m u l e Pilot,The backup crews are listed there,Hext slide, please.

' (Slide)The srgaan&zatPonalstructure of th e f i s s i o n is,

as on previous mieelbonm, wPtb s ~ p g o r %rom Xaunch operations,t h e launch d fg ec t io n being under B, A, Petrone and Ms. &n-nef ly.


4/84

APOLLOAS-505LUNAR MISSION DEVELOPMENTF Mission

Vehicle SA-505 Mission Director G. H. HageModule CM-106 Launch Dl rector R k Petmnece Module SM-106 Flight Director 6.S. LunneyModule LM-4 Mission Engineer ( MA 0 1 G.P. Chandler Jr.Adapter S t A - 1 3Programs Colossus 11; Luminary 1 (Rev.69)Complex L C 39 B

( C DR )rdodule Pi lot CCMPE

Module Pi lo t CLMPS

CREW ASSlGWENTSPRIME- BACKUP SUPPORTTJ. Stafford L.G. Cooper J.H, EngleJ.W. Young D, F. Eisele C.M. ~ u k e.A, Cer nan E. D. M i cke l l R.E.' Evans


5/84

MISSION OPERATIONS ORGANIZATION

Dl RECTOR OF LAUNCH DIRECTOR OF FLIGHTOPERATIONS: OPERATIONS:R g A a PETRONE -CmCm KRAFT

LAUNCH OPERATIONS FLIGHT DIRECTORS:MANAGER:

1 G , S 4 LUNNEYP C m DONNELLY G I 0 1 GRIFFIN

MmLr WINDLERM , P t FRANK

RADMm FmEa BAKUTIS

RADM . P . S , M~E ~ANUS

MbJ m GENt DM JONESPR1ME.RECOVERY SHIP:


6/84

The flight operations are under th e direction ofChris Kra f t at Houston, w i t h t h e s e four f l i g h t directors(f ndicating) under t h e direction of Glenn Lunney .The DOD recovery forces t h i s t h e involve Ta s kForce 130 and Task Force 140, with t h e prime recovery s h i pbeing th e USS Princeton, which is w landing pad helicopter,Next s l i d e , please.(Slide)Now, th e ground rules and guidelines for thies m i s s i o nare summarized here, One of the important ones is t o lay thksmianion out as c lose ly in a time l i n e sense as the G missionor t h e f i r s t lunar landing nfssion No, 11.We have f ive possibfe launch days across the sf ht-day per iod from t h e 18th through t h e 25th of May, I t w i l l betargeted to achPeve most favorable lighting an th e primeApallo G landing sites 2, 3, 4 and 5 .We progr-d the latter two days in t h e missionwi th some compromise Ln the lighting to give the additionalflexibility of going an a d d i t i o n a l two days, t h e 24th and

25th, in the event that some problem p r e v e n t s us from goingon our earlier planned date of th e 18th.There w i l l be a daylight launch and landing and re-covery.TLL -- translunar injection -- will be targeted fora free return circumlunar with a low po9nt or perigee w i t ht h e moon of 60 nautical miles and with an earth return par5-

gee of 28 nautdcal miles.We w i l l use a two-stage lunar orbit i n j e c t i o n aswe d5d on A p ~ l l o , 60 by 170 miles on the f i r s t orbit,circularizing after two orbfts to a 60 by 60 situation,Next s l i d e , please,(Sf de)


7/84

F CJ1SSIO# DESIGI 6ROU:ID' RULES AND 6UIDElI:IESE N T I R E MISSION TO FOLLOW THE G MISSEON TIMELINE A S CLOSELY

A S POSSIBLE5 POSSIBLE LAUNCH DAYS ACROSS 8 D AY PERIOD WITH 1,3.6,7,8TYE S P ACING

+ UUNCH W I L L BE TARGETED TO ACHIEVE MOST FAVORABLE LIGHTINGFOR PRIME G SITES 2,3,4, AND 5-1

Is H E IWO A D B l T l O N A l .LAUNCH D A Y S PAST THE NORMAL G MNDQW

AR E TARGETED TO THE LAST G $PIE - ACCEPTING HIGH SUNELEVATlONS A T SITE 5DAYLIGHT UUNCH AND LANDING

LUNAR PERIGEE 60N. MI.EAkTHf iETURN PERIGEE BN. I .

+ TWO STAGE LO1 TW O REVS IN 60 8 Y 170 C IR C U L A R IZ E TO 60 B Y 60


8/84

M P A D 4 9 9 1 5

APOLLO CAND IDATE LUNAR LAND ING SITES


9/84

This chart d e p f c t ~ he changes that occur in launchtime and the launch window as a function of the f i v e days,the 18th through th e 25th, in whlch we are prepared tolaunch. The earliest Launch opportunity, ous f previouslymentioned, is at T1:49 on the 18th, the last opportunitybeing at 4 :40 in the afternoon on th e afternoon of the 25th.The spread or eime with t h e s e windows is a funct ion

of the azfmuthal eonstmtnts launching out of Cape Kennedy.The landfng s i t e s , as 1 previously indicated, thatgo with each of t h e s e launch opportunbtfes are shown here,alla t h i s will be the expected lighting angle between t h e s u nand the local hotfaontal at each of t h o s e landjng s i tes when

the spacecraft -- when t h e -- arrives in its %ow orbitpass 50,000 f e e t over th e landing s i te selected for thatmission,A s you note, on th e Past opportunity we ham beenwilling t o accept a s l i g h t degradation or higher l i g h t i n gztngle in order to have t he f l e x i b i l i t y of going on t h a t day.Next s l i d e , please .{ S l i d e )Thks chart here 1 think in a schematic way d e p i c t sthe generic elements of t h e mission. And we have launchfrom ETR going into orbi t with th e opportunity for an S-IVBTLI burn -- I'm havfng a l i t t l e trouble w i t h this pointer --r ight there either on the second or t h i r d o r b i t .The fundamental dbfferencss that I wanted to high-

ldght fn showing t h e key events of the miss3on, aa rackedup here, are that the niosbon fs s l i g h t l y more than e i g h tdays in durat ion, assuming launch on the fArst opportunityst 11:49. One other point is that from the time of undockingon the fourth day until we bring t h e spacecraft back togetheris about e i g h t hours and ten minutes, Thi s compares with anundocked period of about ~ i xours on th e Apollo 9 miss ion ,

Next s l i d e , p le as e,


10/84

L A U N C H WINDOW SUMMARYPAC I F I C I N J ECT I ON

L AUNCH TIME - EASTERN STANDARD IclLS LUNARLANDING S I T E


11/84

PRELIMINARY MUNCH WN D OW SUMMARY, JULY 16 - JULY 22,PACIFIC INJECTION

9 I 1 13 1 5 17 19 21Launch lime - hours ham midnight, e . s C.


12/84

MISSION 'SUMMARY MAY 18, 72" 1 .

lEl 105:18:26TOUCHDOWN 08:00:08

Y h


13/84

MISSION SUMMARY MAY 18, 72" - 1


14/84

TW!rSPOSITION,DOCKI IdG b EJECTION

* SPS


15/84

Now, after th e translunar InJection burn, t h espacecraft prepare for transposition and docking, Thefirst event that occurs i s the command module i n i t i a t e st h e deployment of the spacecraft LM vehic le panels whichare blown away pyrotechnically, The command module proceedsaway from the S- fVB, does a 180-degree maneuver, comes backin, docks w i t h the lunar module, and then the two of themback away from the S-IVB,

N e x t chart, please .(S l id e )This l a then a configuration of the t w o spacecraftin t h e dock configuration throughout the translunar phase of

t h e mission.Next slide, plema.

Now, after t h e two spacearaft have stuccessfullyaccomplished the transposition and docking and have separatedan acceptable d i s t a n c e away from the S- JVB, th e S-IVB willbe passivated and put i n t o a slingshot maneuver which fn ef-fect causes it to traverse a trajectory as shown here, whereint h e gravity f i e l d of th e moon is uned to force that v e h i c l einto a permanent aalar orbit,

Next ~ l i d e , lease.(Slide)The t h e variation that we antSclpate as a functionof launch day and th e time in the window when we launch,

t h i s being t h e beginning on a particular day and this theend ( i n d i c a t i n g ) , varies from a minimum of 75.2 hours to69,3 hours on the last day of t h e wf dow.That difference is largely a result of the f a c tthat the moon's orbit around the earth is not circular butelliptical, and therefore t h e distance is a variable depend-Lng on the day of t h e month that we launch.


16/84


17/84


18/84


19/84

SPENT S - I V BSTAGE

3-1 AS-SOSF/APOLLO-IO MISSION PROFILE


20/84

CIRCUMLUNAR F R E E RETURN


21/84

Next s l i d e , please,( S l i d e )

One intsreisting chart that 1 thought we would showtoday is a p l o t of the velocity of the two spacecraft afterthe translunar in jec t ion burn as it decreames, as we moveaway from the earth, until finally we reach t h e point wherethe moon's gravitational influence actually starts to speedthe combfnation back up again prior ta the time that we dot h e l u n a ~ rbit injection burn,

As you can Bee, that range of speed variea fromabout 25,000 miles per hour a t the time we leave the earthto a low of something in t h e order of something less than500 m i l e s per hour, and then f i n a l l y back up to somethinglike 8,000 miles per hour at time of Injection.

This mission profile is planned, as^ was Apollo 8 ,with four midcourse corrections going out , three coming back,And I mentioned previously that we w i l l use t h e two-stepin j ec t i on into th e final circular orbit around the moon.Our expected time of duration in lunar orbit i nslightly more than 61 hours.Next s l i d e , p lease .( S l i d e )I have already covered t h e two-stage lunar orbi tinsertion discussion, Both of the burns involved are fixedattitude burns, in that the vehic le is Lined up with a par-t icular orientat ion to f nert ia l space, and then burned untilt h e required veloci ty As attained,After the final midcourse maneuver as the spocecraftis coming in towards th e moon, t h e vehscfe is rotated as shownhere in a d i r e c t i o n such that when the insert5on burn is made

th e service propulsion engine causes a retrograde or slowingdown of t h e vehic le to glace it in t h i s orbit,

Again on the side away from the earth the circular-izing maneuver is made to f i n d the place to get to t h e 60nautical mile orbit .Next s l i d e , please.


22/84

24VELOCITY(FTISEC)

(1031

LWI._,UO O 40 80 120 160 2 00 24 0

DlSTA l l C E FEO dl EARTI! CERTEI : (STATUTE PA!) (103)


23/84

MPAD 4 9 8 8 5

MISSION PROF I LE

INJECT ION INTOf RANSLUNARTRAJECTORY

10 = M IDCOURSE CORRECTION


24/84

LUNAR ORBIT. INSERTION

o L O l ( 1 ) r d O x 170 WITH P L A N E C H A N G Eo L01(2)40 x 60 IN PLANE

0 I X E D ATTITUDE BURNS


25/84


26/84

(Slide)Now, in order to acquaint you a l l with some of the

acronyms tha t we use quite broadly on the program, I havelisted some of the key ones in the next nffde, L e t me takejust a moment here to go through them b r i e f l y t o g i v e youP chance t o mad them.

I think most of you are familiar with MSFM, t h eManned Spaceflight Network.L W Paeans we have lost'canmnfcation w i t h t h e spat+craft because i t bas gone behind the moon,~a s when we acquire it again.DPS 'is deercent propulsion system of the lunar moduleAPS Is the a s c e n t propulsfon system of t h e lunarmodule,DOX In the descent orbit insertion that t h e l unarmodule makes An Ats move down towards the 50,000-foot a l t i t udeCSI I s one of t h e rendezvous maneuvers called con-centrPc aequenca i n i t i a t i on , which Colonel McMullen wi11 d i s -cuss in more d e t a i l , as will he discuss CIIH: or constant

d i f Psrential he igh t maneuvers,TPE fs approaching t h e ffnal phase of t h e rendezvout h e ~o-called erminal phase i n i t f ation.PC here is used as plane change, since there i~ al-ways some small remidual plane charige required to br fng the

two spacecraft back together in the same i n e r t i a l plane.Next slide, please,Now, t h i s chart emphasfees two paints, We have workvery bard on th e F mission to m a k e the time line from the timethe spacecraft go into the f i r s t lunar orbit untfl they comeback out on t h e i r way home am r close as we can to the lunar

landing G missfon. And, as you will see, the f irat 30-somehours of the s e two missions are planned t o be i d en t i c a l .


27/84

KEY

MSFN - MANNED SPACEFLIGHT NETWORKLO S -LOSS OF MSFN SIGNALAOS -ACQUlSIT1ON OF MSFN, SIGNAlQFS - DESCENT PROPULSE CYM SYSTEMA P S - ASCENT PROPULS 1ON SYSTEMDOI - DESCENT ORB1 INSERT1 ONCS1 -CONCENTRlC SEQUENCE INITIATIONCDH - CONSTANT D FFERENTlAL HEIGHTTPI -TERMINAL PHASE INlTIATIONPC - PLANE CHANGE


28/84

FIG FnlSSlONS LWR ACTIVITY COlrrrPARtSON

1 POII m r r + - m ~ k

1ERIOD .M I M A R K TRKPHOTOGRAPHY

LWAR ASCEMTLUNAR SURFACELUNAR ASCENT

TO LMT E I


29/84

" F I S S I O N LUNAR ACTIV IN

GET FROM KC-4

CS n fVT lmW3CKNU4 1Y-r IcsnKS tSh TO t MINI-LOI-1SPS LM

* i03T-3AtL -RCS

PD I

COAST60 ?4 MI.I] PERICYNTHIAN-

'OX 60 E i Lrt ' i ~AT

HOUSE A70 N.RImn.nr. CIRC. TREST PERIODI 8 HOURSE X50AT CHECK-OUT


30/84

F MlSSlON LUNAR AC T l V l N(CONCLUDED1

4 WS UJYD h!! iR1 IF REV STZIP P a T O


31/84

1 would also point out that we have arranged thismission such that the rendezvous for th e two miasions areas cl08e to i d e n t i c a l as we can maha them.The ones unique feature in the F mission is that wehave a p h a ~ i n g urn earlier and special only tothe F missionwhich earlier in th e funnr o r b i t t i m e line sets up conditionsso that r rendezvous can be conducted here rather than here(ind2eating) in the time line under the same conditions oflighting and other parameters re la t ive t o that orbital geo-m e t r y exercise.In the cars of the G mfsnion, of course, lrpe have

t h i s block of time set out for the descent , the lunar surfacea c t i v i t f e s , and return back t o lunar orb i t ,Re haw transposed that w i t h this block of time on

the F miesion ( indicat ing) and w i l l use this 50 provide addi-tional photography and landmark txack5ng of certain selectedkey landmarks on t h e lunar surface,

One other point . 1 apologize for an error on thischart. We should have started our time bar here at Wf-1Instead of t h e last midcoume maneuver, and then t h a t pZusthe fact that we l e f t out a little block of time here ( fndi-eating)-- It turns out that th e time in orbft f r o m LO1 untilTEI is' actually a little over 61 hours, So there i s an errorin tha t time scale.

With those comment^, I would like t o ask Tom McMulleto lead you through t h e steps in th e rendezvous maneuvers,HcMULXIEN: Thank you, George.Can we go to th e next slide, pleme,

Aa I go through the discussion here, I would liket o emphasize th e point that Mr, Hage has already ma d e -- t h egreat d e a l of ef fort that has gone into making t h e maneuversat lunar distance during this m i s s i o n similar t o those w ew i l l actually be performing on lunar landing m i s s i o n next time


32/84

L e t me explain a l i t t l e bit t h e s l i d e before wealso get into dfscussing maneuvers themselves,You can see we have t w o plots of the spacecraft,

this one down here Bnd t h i s one up here. The one on the r i g h t -hand s i d e is wha t you would see if you were s tanding o f f some-where in space and looking a r t the moon w i t h t h e two spacecraftgoing around, So you can imagine yoursel f somewhere out inspace, say on t h e earth, with good eyes, and have ability tosee this amount of detail.The scale, of course, is n o t quite true, in that t h eorbits are shown qufte a b i t higher or larger w i t h respect tothe size of the moon,We have the maon div ided i n t b d f i f e r e n t colors here.

The ~ o l i d h m a when both t h e spacecraft and t h e lunar surfaceare in darkness. The next two pke-shaped areas show when thespacecraft is illuminated by the sun ?mt the surface atill isdark. And, of course, on the upper right-hand s i d e , boththe spacecmft and t h e lunar surf ace are f 1 uminated,Over on the lower left hem we have a p l o t which

shows th e relative motion of the two v e h i c l e s t o each other,and on t h i s one you can imagine that you are s i t t i n g an topof t h e command and service module and watching t h e LlYl maneuverabout you,

Okay. So now I think we are ready t o go ahead andd iscu ss the f i r s t maneuver, and it is the separation maneuver.It 5s qufte similar to the separation maneuver we mad e onthe Apollo 9 missSon just completed, I t consists of w smallradial burn by the command and service module usfng the servicereaction control system, This is two-and-a-half fee t persecond. And it g ives the command and service module a smallincrement of downward ve loc l t y ,

Thfa does not change the period of th e command andservice module, so the lunar module and command and servicemodule are s t i l l going around the moon and will complete oneorbit in th e same l ength of t i m e . However, it does providen maximum of about 1.8 nautical miles between the tw o anda b u t a half a m i l e in h e ig h t .

bad here w e see t h a t although the burn is made by .the command and service module, it would appear to the commandand service module as though the lunar module were goPng upand behind it,


33/84

(SAME FOR- SURFACE DARKNESS

SC DARKNESS

F-t 1.8 N. MI.MOTION 1\ / 1- - -MOTION OF LM RELATIVE TO CSMMOON

MPAD 4978 S

2.5 FPS D O W N

CSM SEPARATIONMANEUVER


34/84

And after this small burn, the tw o ve hic l e s w i l lseparate, and as the lunar module d r i f t s up and behind thecommand and service module, certain checks w i f 1 be made tobe sure we want to proceed.

And if we decide not to proceed, we Just withoutany further burns ccontfnue on around thiL maneuver line hereu n t i l the two are back together, and a very emall burn, andthey would again be back in t h e same orbit.However, if the systems look good, th e rendezvousappears to be working satisfactorily, at this point then wewill perform our descent orbit insert ion burn.Next ~ l i d e , lease .

The descent orbit insertion burn is a maneuver tha tis performed by the lunar module descent propulsion system.It starts up with the racket engine throt t ldd up to 10 percent for about 15 seconds, and t h e n t h e throttle i~ advancedto 40 per cent for the remainder of the burn, which is aboutanother 11 seconds.A t the end of t h i s burn, t h e two vehicles w i l l bein the orbits as s h m hers with the lunar module descending

downward closer to the lunar surf ace and th e command andservice module continufng on around t h i s f a i r l y cf.xcularorbit.

One of the other po5nts I should have mentionedis we show on these charts th e point at which the MannedSpaceflight Network will acquire and lose s i g h t of the Lunarm o d u l e as it goes behind the moon.

Also, on the relative motion plot here now, we seethe separation burn is thia small d o t t e d l ine r i g h t here toa d i f f e r e n t scale than we saw prerviouslg. And then w e alsosee the descant orbit -- t h e res u l t s of the descent orbitinaert ion -- as the lunar module n w moves down, passesdirectly underneath the command and service module by about20 nautical milesw dif ference , and then proceeds on downw h e r e it reaches a di s t ance of 52 nautical ma l e a b e h w thecommand and service module.


35/84

N. Mi.

DESCENT ORBIT INSERTION(SAME O N F AND G )

I LM BELOWAND AHEAD

' \FiLM BELOWj -b/20 N. MI.52 N. MI.

50,000 FT ABOVE\LANDING S l TE RADIUS

MOON


36/84

Qkay. In the course sf the burn It 5s hoped tobring t h e lunar module down $0 a point t h a t 1s 50,000 feetor about e i g h t nautical m i l e s above %he landing site,

Okay, Next chart, please.

Here we have a pic t ure , a serPes of pictures, oft h e lunar modu l e as it passes over th e lunar surface. Andproceeding from l e f t t a right. as we start out, we see t h a tthe lunar module fa moving with the engine s i d e facing forwardand t h e astronauts looking down towards t h e lunar surface. Andabout minus 600 seconds they will yaw the v e h i c l e around sothey look out of the front of t h e vehicle facing up. And thisis t o permit several t h i n g s , one t o be aimilar to the way itis going to be handled on the lunar landing mission, butprimarily to permit us to i n i t i a t e a Handing radar checkout.

As you know, this is one system t ha t we haven't.real ly had a good check on to date on a spacecraft f l f ghttest, And this checkout will begin with the vehic le in thisattitude, and as we get down to the minus 400 seconds orpericynthion , or t h e closest point of passage to t h e lunarsurface, the vehicle will pLtch around to where its vert fca laxis is 10 degrees inclined from the l oca l ver t i ca l , andat this time we should be g e t t i n g a lock on from all Pourtrackem of the landing radar,

The landing radar tests will continue as the vehic lecontinues and makes another small attitude change here,p i t c h down 10 degrees, so this vertical ax%s is now alignedwith the local vertical.

As they pass on amurtd, they will also pass a p o i n twhen3 the astronauts' l i n e of s i g h t to t h e landing site isparal le l to the rays of t h e sun as it canes I n , so they willhave some opportunity to measure t h e surface washout.And then as they p a s s on over t h e landing s i t e ,they will pitch the ve hic l e over so they will be looking

vertically down and have s chance to get some good b o t h optitcal and photographic tracks of the landing s i t e .


37/84

HEAR LUNAR SURFACE ACT I V I TY


38/84

0 The next maneuver t h j will be making r3llbe t h e phasdng b u n which Mr. H a g e mentioned a moment ago,Can we go to t h e next cfiart, please?(S l ide )As he anent$oned, the pxposecsf the phasing burn

is t h e point that we initkate t h e phasing burn-- I'm sorry.A l i t t l e b f t before w e would have done $his phasing burnwe would haw started th e pcme~ escent on the lunar landing,In this case, however, we just f l y over the landing s i t e ,and we get 20 this p o b t , and we periarma a phasing burnwhich Is to get usr back i n t o position-with espect to t h ecommand and ss-ce module to perfom rendezvous identicalwith what we w i 1 1 be doing on t h e lunar landing mission,

So the phasing burn is again performed w i t h thedescent propulsion system. 1% is a porslgrsrde maneuver toincrease velocity, hence Ancrease the aposynthion distancespecifically w i t h th e po%nt ip mind of increasing the per iodof the orbit so that th e id which is now fn front of andbelow the CSM can wind up in a position behind and b l m t h eCSY.

I

We see tha t the descent propulsion system is againt h r o t t l e d to 10 per cent, this t i a e for about 26 seconds,and then th e thrott le is advanced t o t h e fixed throttlewhich is about 92,5 per cent thrust for the remainder ofthe burn, whicb is about another 15 seconds.The agocynthion distance or he i g ht I s 194 nauticalmkles above th e lunar surface, Andl then as the vehiclecoasts back d m , St w 2 l l f i n d itself behind the commandand service m o d u l e at t h i s point. The lunar module will.

be staged such tha t t h e dsscent's%agewdll be cast off andwill wind up ~ 5 t hhe ascent stage, and, of course, t h eascent propulsion system rancovered for our next burn,

(Slide)The next burn is n-vbat similar ta w h a t wew i l l be doing on the lanay Isadgng mission, How e v e r , in

this erase we m e , 0% course, in o r b i t already, as opposed


39/84

PHAS I NG MPAQ 4984 5( DEPARTG TIMELINE) N. MI. APOLUNE

tMOON

193 FPSDPS-FULL THROTTLE


40/84

MSFN -. I

213 FPS \1NSERTION

(RETROGRADE] APS

t ( z ?ME ON F AND G)MOON


41/84

t o lifting off th e lunar nurface, and we have or problemof subtracting out velocity as opposed to we will beadding at this point on th e lunar landing,We will need to subtract off some of t h e veloc l tythat we added previously in order t o have our apolune orapocpnthion height of 45 nautical miles. So this is thepolnt w e are talking about up here 45 nautical m i l e s above

t h e lunar surface,As a brief recap over here on t h e relative motion

p l o t , you can see the phasing maneuver took place way up,and we pass behind as we pass through the . , . distanceabove th e CSM and drop behind and again b e l o w , so we areat t h i e point here where again we are ready to subtractout nome veloclty and move ourselves up to a p o i n t 15 nauti-ca l miles be l ow the command and service m d u l e circular orbi t .

Th i s burn will be perfomned by the ascent propulsionsystem which i s an unthrottleable engine, 213 foot per second~ u b t r a c t i o n f velocity.May we have the next s l i d e , please.(Slide)The n e x t maneuver is, h e concentric sequence i n i t i -ation, and, a9 pointed out earlier, it occurs at a helghtabove the lunar surface of 45 nautical m i l e s , so we arenow 15 m i l e s below t h e command and service module orbit.And t h i s is an addition of velocity so as to raise t h eapocynthion from*its 50,000 feet original d is tan ce up toagain 45 nautical m i l e s so we are now in circular orbitbelow the command and service module.Thin is done by the lunar module RCS, and it 1s anmall burn, about 50 feet pes second.Okay. The next burn that we w i l l discuss-- Iguess I should point out over here on this relat ive motionp l o t that now t h i s circular orbit will appear as a s tra ightline as we maintaln our 15 nautical mile distance b e l o w

t h e CSM.


42/84

CONCENTRIC SEQUENCE IN IT IAT ION

MSFN 1

.l I \ MSFNI t ~ o stMOON


43/84

As you all HEamow, there m q be some requireareatfor a pl- change, andl t h e only time you can change fromone $1- to another is when you are passing through t h epoint along t h e l i n e at which throase two pla- coincide.So in order to force that point to occur do= here at ourcomtrtnt differentPa'L heigh t maneuver, we make a s m a l lplane change here if required, and nominally it w5ll bezero, but, at any rate, %t could be some some value, to forcet h e plane t h a t t h e lunar W u l e is %n to cross the plane oft h e command and service saodule at tMs point,

y We can go to th e next s lAde ,(S l ide)W e will d i s c u s s th e constant d i f f e r e n t i a l height

bum, And this is nominally about s i x feet per second andagain performed by the lunar module reaction control system.And this can provide any plane change %sin required toens- t ha t th e final. rendezvous maneuvers are co-planer --that is, th e two vehicles are in t h e same plane -- and alsofor any height adjustment required,

And again w e are back over hem on the re la t ivearot2on plot w i t h an expanded scale, and you can see how asm press on around the trajectory course, tbe terminal phasei n i t i a t e point , that we are a constant height below t h eorbit of the. C SM ,

Okay. Then we can see on thfs s l i d e and as w e .get around to t h i s point we are about-- Oplr elevation anglePram t h e lunar module up to the command and s e~v i c e oduleis about 26 degrees, We will prform a burn essentkallyalong that l i n e of sight. A n d tbas will raise the heightof thg lunar madule's orbit around t h e lunar surf- to 60m i l e s , which will let us coincide d t h the orbit of thecommand and service module.

A d , of c m e , w f n g on-board systems, any eorrec-t ions t h a t are r eq ed r ed l -18 be ma d e at t h e s e midcaumecorrection poiits as the mndmv01~1p m s s e s ,And then the f i r s t 6%the serfgs of three brakingmaneuvers a l m t sfmultanmusly afll be p e r f o w at this


44/84

CONSTANT DFFERENTIAL HEIGHTAND TERMINAL PHASE(SAME ON F AND G)NDEZVOUS ANDSTATIONKEEP

TPI (MIDPOINT

30 N. MI.d m

MINI1 L con(NEAR ZERO)MI.+ - \ \P : 36 MIN CPH


45/84

point for tatal d e l t a V used during the braking process of30 t o 32 feet per second, and again k t w i l l be performedusAng the lunar module reaction control system,

So we have the lunar mudule being the active space-craft during the rendezvous.Of aourse, the purpose of the brak5ng maneuver ist o circularize th e lunar moduleps orbit in exactly tire sameorbit m t h e command and service module,And then a t t h i e point we will go ahead and dockthe tmo vehic les , this time I believe wing the command and

service M u l e aa t h e active apacecrsrft.Okay. Then, at that polnt , w e will go ahead andtransfer the crew back from t h e lunar module into the commandand servkce mnsdule,Can we go t o the next chart, please,(Slide)And here w e see the LM b e i n g jettisoned after the

c r e w has transferred back. And this 90 E i~ about 90 degreeseast Jongitude on the lunar surface.

And then aa t h e two vehicles come around, the commanand sewice module will m&e a amall burn to separate th e twoabout two feet pez- second, and it is about 45 degrees offfrom the lunar module.

A s we p a s s on around on the zero degmes longitude,which is, of course-- The e a r t h 1s d i r e c t l y down this dls-tance. The a s c e n t propulsion nystem will again be l i t toperform rm APS burn t o depletion,

Thin is performed on th e abort guidance system,All the other maneuverg we have Been have been performedon th e primary aviation guidance system on the LM,On this 6n0, in order t o get the check on t h eactual switchfng. . . We are adding approximately 3,800 fee


46/84

MPAD i\-64 d

F MISSION LM JETTISONTO APS DEPLETION BURN

APS BURN TO ..DEPELTI ON


47/84

per second t o the ascent stage, and P t will pass on out ofthe lunar sphere of f f uence and go i n t o an orbit about t h esun, no longer entering into our problem.That's a b u t all I have to say on t h e a s c e n tmaneuvers. Mr. Aage will be back to brief you on the restof the mission,MGE: A t this point Colonel McMullen has broughtus up through th e busy five days t h a t we had on Apollo 9.Subsequent to completing th e rendezvous and t h e ascent burnand the LM ascent stage unmanned, the crew will spend severalorb i t s doing landmark sighting. L e t me descr5be what t h a t is.N e x t slide, please.

One of th e niost precise ways that we have of loeat-ing not only in la t i tude and longitude but e l evat ion spec i f i clandmarks such as a l i p of a crater or a small protuberanceon the surface of th e moon is to view t ha t landmark with theoptical tracking system aboard the command module and at d f s -creta points along the orb i t about every 15 degrees or sorecord into the computer the precise angles that th e opticalsystem had t o be set at in order to view that landmark r i g h tin the crons-haim of th e telescope.

With that angular information and th e Manned Space-f l i g h t Network tracking information of what the o r b i t oft h e command and service module was during that specAf5c passover a landmark, k t is fairly straightfornard by conventionalsurveying trigonometry to prec ise ly so lve for the altitudeand th e latitude and longitude of t h a t specjf ic landmark.

As I mentioned, th e crew will spend several orbttsconducting those kind of exercltses, camplemented by addi-t i o n a l photography.Next s l i d e , p lease .(Slide)


48/84


49/84

Now, the transearth injection is very simflar t othat that we had on Apallo 8 , Our time in orbit is aboutdouble what we had on A p o Z l o 8. We are targetfng fox thesame general l a n d i n g area 165 degrees went longitude, whkchis an area west and south of Hawaii.

We are not attempting t o control the latitude aswe d i d not on previous flights,Our nomnal entry angle is as shown, and I will dis-

cuss that in a l i t t l e mo r e detail,We will use whatever res idual propulsive capacitywe have in the aervAce module t o reduce the return timefrom t h e moon.And all of the transearth knject ion burns and themidcourse burns will be done with a fixed att i tude of the

command service module.Next slide, please.

M o w , this is th e configuration which you are a l lfamiliar with of t h e veh ic l e coming home from the m w n , antennadeployed as shown,I thought I would comment jus t briefly here on adiagram that I think g&ves you a pretty mod representationof what happens if you don't have capability of making mid-course corrections.Each and any one of these propulsion burns wind

up w i t h some reb5dual errors t o that that waa specificallyplanned, If one permits those errors t o propagate withoutcorrection, then we f ind that we have a d iv e r g in g cone onthat trajectory, 50 we set certain miss ion rules to permitt h a t to grow within acceptable limits, and then we make a mid-course correction and bring t h e vehic le back on trajectoryand track it and watch for evidence of errors i n t h a t mid-course correction, untf finally we f i n d th e vah&cleon anacceptable path lead ing to t h e f i n a l separation of thecommand module and enter ing knto the narrow entry corridor.


50/84

M P A D 4 9 9 0 S

TRANSEARTH INJECTIONNOMINALLY EXECUTED - 61 .5 HR AFTER LOI-1TARGETED LANDING LONG I TUDE = 165OWLANDING LATITUDE NOT D IRECTLY CONTROLLED

TARGETED E N T R Y PATH ANGLE 5 -6.5r

R E T U R N T I M E ASAP WHEN A V AVA I L A B L ERETURN INCLINATION (40F I X E D ATT ITUDE BURN


51/84


52/84


53/84

You may remember on ApoLlo 8 the transearth in ject ionburn was so precise that we could have, f f we had elected t o ,essentially l e t the vehicle come home without any furthermaneuvers, We did d e c i d e to make a small t r i m burn nbont half-way home.

Next chart, please,

Thfs chart %I-s you some f ee l for the variatfonin total mission time in hours, where 192 here representse i g h t calendar days, And, as you can see, it is a l i t t l eover e%ght calendar days if we launch right at the beginningof the first launch window on the 18th.

The time of t h e mission can vary f r o m this limitof 187 hours up to this lAm5t whfch is something in excessof 197 houra, or, fa other words, a p o s s i b l e variation of asmuch as ten hours depending on whfch day and which part oft h e launch window we get on.

Next s l i d e , pleaae.

The entry is typical of that that we demonstratedon Apollo 8 , We have capability for a very large reentrymaneuver footprint, 1,200 to 2,500 nautical miles. We wPllnominally target for 1,350,Th i s tends to enhance our abf lity to make a goodreentry in t h e e v e n t that we have to use one of t h e backupcontrol modes or guidance mode.We wiT1 allow for weather avoidance in the recoveryarea by target ing for a change i n the vehicle trajectoryabout one day prior to reentry if the weather in t h e recoveryarea looks l i k e it is beyond acceptable l i m i t s ,Next s l i d e , please,

A l i t t l e b i t more about the reentry corridor. l t q snominally six-and-a-half degrees f l i g h t path angle t o t h elocal horizontal of t h e atmosphere at t h e p o i n t t ha t you


54/84

TRANSEARTH SUMMARY MAY 1969

TE FL IGHTTIME, HR

n LAUNCH WINDOW OPEN

U LAUNCH WINDOW CLOSED

LAUNCH PATE


55/84

TRANSEARTH SUMMARY M A Y 1969(CONCLUDED)

TOTAL .MCSSKM 192TINE, HR( 8 DAYS)

LAUNCiaWISa0:d- OPEN !J

-

-CLOSE

LAUNCH DATE


56/84

ENTRYO E N T R Y RANGE CAPABIL ITY - 1200 TO 2500 N. MI.

0 NOMINAL E N T R Y R A N G E - 1350 N. MI.

0 SHORT R A N G E S E LE CTE D FOR NOMINAL MlSS iON B E C A U S E :

o RANGE FROM E N T R Y TO L A N D I N G C A N B E S A M E FORP R i M A R Y A N D BACKUP CONTROL MODES

0 PRIMARY MODE E A S I E R TO MONITOR WITH S H O R T R A N G E

6 WEATHER A V O I D A N C E , WITHIN ONE D A Y PR1OR TO E N T R Y , I SA C H I E V E D USING ENTRY RANGING C A P A B l l E T Y TO 2 5 0 0 N. MI.

0 U P TO ONE D A Y PRIOR TO E N T R Y U S E PROPULSION S Y S T E MTO C H A N G E LANDING POINT

..


57/84

ENTRYFLIGHT- PATHANGLE, DEG

ENTRY CORRIDOR

26 27 28 29 30 31 32 33 34 35 36 37 38 3 9 X l dENTRY INERTIAL VELOCITV, V., FPSI


58/84

f i r s t enter into sens ib le atmosphere, t h i s six-and-a-halfdegrees p l u s or mfnus appsoxfmstely one degree at th eve loc i t i es that we ell be returning from the muon, roughly36,000 feet per second,

The limits of that entry corridor I think ham beendtscunsed before, but vary b r i e f l y ff we came in too shallowwe f i n d a situatbon where the spacecraft would skip backout of the atmosphere, and this is an unacceptable colld%tionbecause you would rind up w i t h the vehic le going i n to an o r b i tthat would exceed the duration of th e expendables aboard t h ecommand module.

The lower limit %e one where you start to experienceacceleratfona t h a t are beyond the capability 0% t h e machineryand the c r e w if you come $a too steeply,

There are a couple of other limits that have to dowith th e thermal capability ai t h e heat shield. Th i s longrepresents t h e total heat that the s h i e l d must dissipate incoming down through the atmosphere. T h i s l i t t l e one here isa heat rate limit. In other w~sdls, there i s a limit to t h etotal h e a t , and there is a limit $0 how mch heat you canabsorb in any given small increment of time.

Th 5 s is th e plot of the reentry pso%ile showinga l t i t u d e in thousands 0% feet here versus range to go herein nautical miles. T h i s 58 nominally c a l l a d a constant greentry, StastAng at 400,008 feet these l ines (indicatf g)represent approximately 30 seconds -- 30 seconds betweenthese lines,There are two peaks in this reentry trajectory,

t h e peaks in t h e g load an the spacecraft, one in t h i s regionthat gets up to about 6,3 pulse g and one a% t h i s point thatgets up just s h o r t of 6 g,

The vehicle then comes on down and we get drogue andmain chute deployment w i t h touchdown of a l i t t l e over 14minutes after &re genetrate the sen s ib le atmosphere,


59/84

GEO

G E O D E T I CA L T I T U D E ,

FT

M P A O 47 ,DETIC ALTITUDE VERSUS RANGE TO GO4 0 0 x 1 0 ~ NOTE: T I M E TICKED E V E R Y '/2 MIN

FROM E N T R Y INTERFACE

E N T E R S - B A N D B L A C K O U T

E X I T S - B A N D B L A C K 0TERMlNATtON OF C M C G U I D A N C ED R O G U E P A R A C H U T E D E P L O Y M E N T

MAIN P A R A C H U T E DEPLOYMENTT O U C H D O W N . I T = 1 4 :

1400 1200 1 0 0 0 a00 600 400 200 QRANGE TO GO, . M I ,


60/84

MAY WINDOWNOM INAL RETURN LOCI

GEODETIC.cr _ " - ----LATITUDE, 0 !-* , - ;>+ :-DEG L- -- -is \ , 20-* ? ',-- - =-&

:* * -- : = LAUNCH I20 ' -- -\- M A Y 18- -

LONGITUDE, DEG


61/84

Ne x t slide, please.( S l f d e )As I mntioned earlier, th e nominal splashdown

longitude 2s 165 degrees west longitude, just a l 5 t t l e b i twest of Hawaii and south, Further aouth on the 18th. Closerto Hawaif on the 20tb,And then to make sure we avoided the i s l a n d group

h e r e around Hawaii, we mowed over to 175 degrees west long%-tude on t h e 23rd, 24th, and 25th.

Next s l i d e , pleasa.

I would Like to t a l k gust briefly about some ofthe Launch abort capability t h a t we have in the system.It has been in th e mfssfon rules from the beginning of theprogram, We basically have four modes of abort during tholaunch phase, l i s t e d I through EV as shown here.Their bssfc di f f erences are:Mode I abort uses launch escape tower,Mode 11 abort merely allows the command servicemodule to use a little RCS thrust t o get away from th e launchvehicle and then I t goes on and coasts, separates, and re-enters at a suborbital velocity using th e normal chuterecovery.Mode 1x1 a b r t As th e higher velocity one whichrequires that we burn t h e SPS system in a retrograde wayto s l o w the veh ic l e down for reentry.Finally, Mode IV is an abort mode where we useth e capwbility of the 5-IfbB as ehown here s taging offthe S-11 earlier in the event we have a problem to carrythe vehicle an up into o r b i t .The capability s tarts at about a little short of

six minutes into the launch phase.


62/84


63/84

GROUND ELAPSED TIWE OF ABORT, M I H .-.


64/84

We also have capability f f we have problems att h i s period of time to use the service propulsion systemin an accsleratltng way t o carry th e vehicle on up intoorbf t.The conclusion that we have come t o in that when

one gets up 5nto these higher velocity portions of thelaunch phase, the s s f e ~ t ype of abort 5s one into orbit,where you can take some t i m e to sort out the problem andthen perform the normal reentry,Next s l i d e , p l e a s e .( s l ide )T h i s damion, like a l l previous nfasfon%, has f n-valved mt number of alternate misston classes that we are

prepared to f l y in the event of difficulty, There are fourgeneric oms on this mission.%

Like th e 9 mission, we could be l i m i t e d t o a l o wearth orbit m9ssion.We might find ourselms with a translunar in jec t ion

burn on the part of t h e S-ZVB that either leaves us in asemi-synchronous earth orbit, which is very high apogee orbft ,or one that is capable of taking cArcumlunar when we uset h e surface propulsion engine to put t h e l i t t l e bit of extraenergy required to get us out to th e moon.

If that kind of an anomaly occurred, we may not beIn ponftion to go into lunar orbft.Obv%ously,the ultimate situation I s lunar orbitoption.The analysis techniques th a t are employed in de-veloping the rules by which t h o flight directors select whichoption t o go fnto in the event of trouble are shown on thenext slide, and this slide is a =presentative example ofa logic dAagram where we just took this one case whe r e wecompleted t h e translunar injec t ion burn and t h e next event

is the LM extraction, and obviously the two options you havethere are e i ther , "Yea, we are able to," or ''No."


65/84

A L E R N A T E MlSS' l ON CLASSES

LOW EARTH ORB1tSEMI SYNCHRONOUS EARTH ALTERNATE

e RCUMLUNAR@ LUNAR ORBI T


66/84

MISSION F EARTH ORB I T ALTERNATE, MISSIONS

CSM / LM EARTHEARTH ORB I T ORSIT MISSION I NR E N D E Z V O U S SEKT SYNCHRObiOUS

{ M!SSION E L L I P S E A

7NO'


67/84

If t h e answer is '#yeswand we are able to completet h e lunar module extraction, we fo l lm t h i s path.

If "no," w& go down another path whAch has asimilar structure to it,Each on& of t h e s e paths leads t o a set of m i ~ s i o arules th a t lead to an alternate mission,For example, if at th e tfrne of TLI we found thatth e bum wa s short and would result in a m a x i m um altitudearound the earth of around 13,000 mAlas, we would modifythat orb i t and come down to a CSWUS loaf earth orbital rendez-

vous mission very similar to what we d i d on Apollo 9.If th e bum was greater than th a t required t o getto 13,000 miles apogee, we would go on into t h i s dec i s i onblock (Lndicating) which looks at the capability of thatTLf burn and could leave us either with th e option to go

i n t o a lunar mission or go down into a miss ion which is avery high earth orbital m i s s i o n that would not p e rm i t us tomodify it back d m o low orbita l mission because of t h elimited d e l t a V propellants aboaml th e service module.Now, there f~ a whole family of these d ec i s io nblocks t h a t are u s e d ' i n developing She pyramid of alternate

missions that fall below t h e s e three genetic categories,Next slide, please.(Slide)I would like t o t a l k just for a moment here about

t h e Apollo 10 TY operational plans, I don't propose to gothrough and read t h i s chart.J u t before coming down to t h e briefing, f w a sadvised that the latest planning ca l l s for a total of 11d i f f e r e n t crew operations involving W , hey are scatteredthroughout t h e mission, and most of them are about 15 minu t e sin duration,As you ~ 5 1 1 ote here* it is our i n t e n t to fly anexperiment involving color TV if we can dev e l o p it and get

it prepared t o f l y in time to support this mission.


68/84

k? r j LLO tO TV OPERATIONS PLAN

o OBJECT tVESEXTERIOR VIEWS OF THE LUNAR SURFACE AND EARTHFROM LUNAR 13 I STANCE

0 INTERIORVIECVS OFCREW ATTHEIR OPTIONr PROVt LIES INFORIVtd f lON WHICH WIILLASSIST INEVALUATION OF THE POTENTIAL USEFULNESS OF N FROMLUNAR Dl STANCE.

0 EQUI PMENT USED (STOWED N CM3CM BUCK AND WHITE N CANERA IR C A)* CM COLOR TV CAMERA (WESTINGHOUSE)W lDE ANGLE LENS (800 FQVl100 mrn LENS ( FOV)ROTATING FILTER

MISSION TIME LINEPER1OD V IEWS

TIC I NTERI OR - EXTER1OR tEARTHlMOON)B E T W E E N LOI 1 and LO12 LUNAR SURFACEF O R W T I . O N FLY NGDUR1NG RENDEZVOUS EXTERIOR - LMPOST RENDEZVOUS EXTERIOR - LMTEC I NTERIOR AND EXTERIOR (EARTH~WIOG&!)


69/84

APOLLO 10 PHOTO OPERATIONS PUN

CAMERAS:HAS SEIBLAD 70MM - I M & CMMAUER 16MM - LM & CM

TD & ELM INSPECTIONLM ACTIVE RENDEZVOUS AND DOCKINGSEXTANT PHOTOGRAPHYCREW ACT IV I T IESGENERAL EXTRIORLUNAR ORBITAL PHOTOGRAPHYLONG DISTANCE EARTH - MOON


70/84

I3 we are able t o -- and my guess is that are haveabout a 50-50 chance of making f t -- we wuuld do most oft h e p5cture~ ith color W rather than black and white,Thfe gives you a short rundown on th e per idsduring the mission when we would be doing various kinds oftelevision coverage, That list is t yp i ca l . There areactually now planned, as % said esrlfer, 13 d i f f e r e n t TVperiods of a b u t 15 minutest duration.Ne x t slide, please.

En addit ion to the colbr 1PV, we would be carryingt h e standard complement of Hasselbkad still cameras and t h eMauer 16 mm, movie cameras, bath in the lunar and commandmodules.

These cameras w i l l be used in consonance w i t h th ephotographic flight plan that has been developed w i t h thecrew to cover these critical phases of the mission.Next s l i d e , please.( S l i d e )Now, in surmpary, 1 believe this one chart givesus on earth th e best birdseye view of what is going to takeplace as s funct ion of time from launch to insert ion intolunar orbit through the various descent and rendezvousmaneuvers of the two v e h i c l e s until finally t h e command andservice module burns out 0%orbit and heads back for h m e .This is a very close representation of the geometry

in an angular sense, in that the moon will be travellingabout through this kind of an orbit during the period oftime t h a t the two spacecraf $ are in the v i c i n i t y of themoon.I think t h a t with those (3ommentean the m i s s i o n

that we plan to f l y , k would like to open the seasion toquestians. But before I do, I would like to paint out t h a tI have a m o d e ahich was prepared by MSCPg Flight PlanningDivision which is an excellent movie an describing thegeometry of launch windows and why they are th e way theyare,


71/84

1 thfnk it h a s been shown before p o s s ib ly priorto the Apollo 8 miss%on, but if there are enough of youwho are in tere s ted in seeing it, X think you might f i nd itvery good in clarifying some of these constraints that wehave ta live with in f l y i n g t h e s e miss ions tha t are a resultof nature.

OIDONNE ;U : We will take a few questions from here,then go to Houston, and then return here.QUESTION: 011 the launch phase, have. there beenany unmanned launches from 39-B, or fs this the first timet h a t pad will be used?HAGE: 3 9 4 hros not haAi any previous launchesoff of it. Th i s w i l l be the f i r s t launch off of that pad,The original planning for t h e Apallo facilitiesat Remedy fncluded two launch pads, and t h e phil~sophybe-

hind this is I think a very obvious one, in that we foundover the years that one Launch pad 5~ the wrong number inth e event t ha t the program had the misfortune to be facedwith a catastrophfc failure on the pad, Then there wouldbe a very long delay in bringing one pad back up to anactivated status.

I

So we have a l w a y ~ lanned to have t w o pads to sup-port the actual lunar landing missfon attempt.

OtDOM3LL: Over here.QUBSTION: I understand there is a reason why thislunar module 4 could not land on t h e moon even if it -8desired to do so. Would you explain that reason, Mr. Mage?HE. HA-: The lunar module being flown on this

f l i g h t , LM 4, has s couple of deficiencies in i t s equipmentthat are partly w result of deciding that we w e r e going toconfigure LM 5 and subsequent for the landing attempt andp a r t ly because we had planned to f l y an F mission for somemonths and test the landing radar.

Now* le t me expand on that a l i t t l e b i t , Thelanding radar on 4 has been augmented in such a way t ha twe will be able t o ve r bf y its operation flying through t h a t


72/84

1- par% of the orbit, about 50,000 feet as Colonel McBdulLenmentioned, and get s long track wish a landing radar of about880 seconds, Normally, t h e Banding radar that would be usedom a landing d s s i o n does no$ %Q& up in a sense on t h e sur-face of the moon until the vehicle gets d m o somethinglike 30,000 f ee t ,

So t h l s landhg radar has been augaaented to provideus w i t h a good vaiidation of t h e landing radar before w eactually commit to a land&= mission on t h e G mission,One other change, which is one t h a t w e have controlover. We have off-loaded roughly half the propellants in t h eascent stage of the lunar module in order to m o r e nearlyrepxaent th e inertias and weights of the ascent stage during

th e rendezvous phase of t h e mission.1 am sure you can understand that the lunar moduloascent stage ks abu t half propellant and about half equip-ment. And when you take off from the moon t h e v e h i c l e weighsapprox5mately 10,000 pounds, and by the time you reach orbitand are ready to dock, it*s almost down to 5,000 pounds.

Th i s is a very large change in weight and inertia, and w ehave off-loaded this vehicle to more nearly match t h e dynamiccondit ions of control that the crew wi11 be faced w i t h duringthe actual rendezvous and docking,QmSTION: Several questions. What will the l i g h t -ing of the moon be at th e time of th e launch? W i l l it be

a half-moon? Crescent moon?MGE: Let's see if X have got that he r e , Thef irst opportunity in duly is an the 16th, and t h a t is forthe aecond prime t a ~ g e t hat 1 ahoared on t h a t chart of the

map of the moon, The s i n e elevation at that target w i l l beabout 10 degrees f r o m the horizontal, and that target isabout 30 degrees around from t h e easterlymost limb. If youare looking at the moon here it's about 30 degrees around.So you would have about a half-crescent,

BlcMULIXN: Put s l i d e 29 up, k think we could seeit. SIlde 29 up, please.

FlAC;$: It will be a new crescent o f f of a n ew mood,and Et w i l l be about half-formed,


73/84

RAGE: Here*s h e direction t o the earth. And,as you can see, you w i l l see this If t l e p l e as lit bythe sun, and that in ef fect will gfve you a new crescent,about a half-formed new crescent, halfway between a newmoon and a half-moon.

QUESTTON: And the other part of my question was:f didn't understand t h e reason behind the h igh apolune of194 nautical miles, Because you don't h a w to go that highin t h e actual planned mission.McMW-N t That*s orrect, But, you see, we are

starting off-- let'^ see, The period of s body revolvingabout another one is a function of a lo t of things, one ofwhich is the s i ~ ef the o r b i t , th e semi-major axis. Sowhen we start our descent orbit InsnrtAon, obviously we arecut t ing d m he size of t h e semi-major axis, As a result ,we are moving about the central body -- that is, about themoon -- faster than we were originally, And the lunar modulewinds up in front of the command and service module.

Now, this was not the condition we would have farrendezvours or for In i t ia t ing rendezvous on the lunar landingmission. fn fact, we'd start o f f with the lunar module'behind.

So, obvfou~ly, omehow we have to ge t the lunarmodule back behind the comand and service module. AndusAng t h e same m le that we just diecussed, we i n s e r t itinto a real larm orbit no the period of i t a rotation aboutthe moon is very large, and, hence, it falls behind the.command and service module. I t winds up r i g h t at t h e sanepl ac e t h a t w e started t h e maneuver, but it Just is somewhatd i f f e r e n t relative t o t h e command and service module.

QUESTION: I have trouble remembering the meaningor the purpose of the CSI and CDH maneuvers, and one reasonX do in X donrt understand the meaning of those mrds"concentric sequence ini t iat ion4' with reference t o theactual maneuver performed, And I was wondering if you couldtake a couple of minutes t o explain the relation of t h e wordsto t h e maneuver,

McMPUN : Ukay. 1 1 r y Could we RaveCbart 36 up, please?

(Slide)


74/84

The concentric sequence i n it ationm- I mesa Ir e a l l y can't turn the t e r n around, but the purpose ofboth th e concentric sequence AnitAatfon burn and the con-s tant differential height burn is So get us into s circularorbtt at a constant hetght below t h e command and servicemodule orbit,So I guems a simple way to say it is to make surewe are in the same plane, tha t we are in a circular orbit

behind and below th e command and service module, T h e factt h a t we are below means that we are going around faster,land hence we w i l l be catching up, so we want t o atart offfrom a pornition behind.

HAGE: Yay I h e l p a little on that? One way tothink a b u t that is that the maneuver at this p o t n t whichis labeled "concentric sequence An5 iat ion*' does in fact,if it is a perfect maneuver, put thAs vehicle in an orbAtthat i s circular and concentric w i t h i n th e CSM orbit -- ifI t is perfect,

QUESTION: You are making one orbit concentrict o th e other orbit?

Mc-N: Okay. X guess to carry k t one further,the constant dAfferentia1 height is to ensure you maintainjust t h a t constant difference in height above t h e surfaceof the central body.QITgSTION: I have a couple of questions, one ont h e perlcynthion. Can you give us in miles uprange of th eactual landing s i ts the po int on t h e moon where the spacce-craft w5ll be closest and why it w a s adjusted that way?

In other words, what USCON problems you are trying to find,photography of more landing sites than just one, that kindof t h i n g .McBTTJUN: I can answer the gecond one quite c lear l

The d i s t an ce or the po i n t at which w e arrive at psricynthionis detenained by the geometry of th e lunar landing miss ion.This is a f a l l o u t from trying to make t h i ~ i s s i o n i d e n t i c a lt o ' t h e lunar landing miss ion , and ideally in th e lunar l a n d i nmissAon we would at the point of perhcynthion i n i t i a t e apower d e s c e n t ,


75/84

That is to say, we would light th e descent stageand continue to burn ae we slow the veh ic l e down andcontrol its descent down t o a landing at th e landing site.Now, t h e d i ~ t a n c e head of the landing site Ithink is around 237 miles, something l t k e t h a t .QUESTION: The second question is: You burn yourascent propulslan system engine to get rid of th e ascentstage to test the abort guidance system, A t JPL they madea proposal for a transponder fn lunar orbit for about amonth for Apollo Applications to track it continuously toresolve t h i s WLSCON problem. W a s there any conaideratfonever given to using the ascent propulsion or the ascent

stage -- that is, leaving it in lunar orbit af ter you havedone same pro and can maneuvers, retro and posigrade ands t u f f l i k e that?

IIAGE: 1 can't specifically answer whether or notit was considered. f can comment on the fact that thebattery capacity of the ascent atage is limited, and anApollo 9, as I recall, after we had separated the ascentstage and put it in an unmanned mode and made a burn onthe primary ~ S d a n c e ystem, we we= a b l e to get telemetryfor something like nine hours, and then the battery wentdead,

So in order to do wh8t you suggested here f thinkit would have required modkficatfon of the spacecraft,QUIZSTION: I understood you to say that there

rill be 11 TV aptfons. Could you g i v e us the TO time lineagain, the 11 polnts?IEAGE: I'd be glad to do that. I wonder if 1

mighe leave it here with Bill and you a13 can take at. ftis a tentative l i s t , I mean t h e times are tentative.The crew will exercise some option on p r e c i s e l ywhen these windows open up, But there are 11 listed here.Q?JZSTIOW: The time w i l l be in GXT?


76/84

HAEE: Y e s , ground ellapsed time.O'DOHNELL: We will Include thse fn the t ranscr ip t .QURSTION: What is th e consideratfon i n having t h eorbit 60 nautical rnilss and going down t o 50,000 feet?I realize 60 i~ what you're going to do on thelunar landing mission, but why would you d e c i d e on that onth e lunar landing mission?HAGE: In t h e vatrioum tradeoff8 that ham been madeover the years and fPnally converging on t h e profile for theApollo landing, one of these tradeoffa involves the amount

of propulsive energy requimd t o get into an orbit aroundth e moon. The hfgher the orbit, t h e more energy you musttake out of t h e service propulsion tanks to slow the vehic ledown and get it into orbito

Sixty m a l e s turned out to be a good compromisefor minimum energy with a rew9onab'Se he ight above thesurf ce to acconundate guidance and control uncertainties.So it 5s one of the tgplcal kinds of engineeringcompromises t h a t one goes through in mAnimkzing energy and

ye t leaving enough margin for guidance uncertaint ies .QU%ESTION: What about th e 50,000 fest now?MGE: Well, that a lso in an energy consideration,in t h a t the lunar module comes d m rom orbit, from t h e60-mile orbit ensentAally with=- It i n 6 t i a t e s the orbit

t o come down t o 50,000 feat w i t h a very abort burn. I t takesvery l i t t l e energy w t the tkme 00 separation t o bring t h evehic le down t~ 50,000 feet.Fifty thousand fest %s an a l t i t u d e that wasselected when considering the need for a radar to lock on

t o the lsurface of the moon and give updated information onprectsely whe r e the vehicle is relative to the surface oXth e moon, a compromise w d t h b w much propellant we have fnthe descent stage 0% the lunar module, since t h e wholemaneuver, as Colone l McMullen mentioned, f r o m t h e time youge t to 50,000 fest until you land, is a powered burn, andso you wan t to keep that time as short as p o s s i b l e ,


77/84

But, on the otlaer hand, you have got to leaweyourself enough altitude to make a31 the nsvhgation fixesthat are necessary wi th the radar and with th e I n e r t i a lsystem.

QUESTZOPI : Knowing at this time t h e command modulewill be the active vehic le during docking, is this t h e r e s u l to f . t b e difffculty the lunar module commander had ~ 5 t h e ingthe act ive part in th e docking of Apollo 97HA=: 1 would have to say that the decision to usethe command module for the actual docking is a d i r e c t result

of having learned that it is easier to do with t h e commandmodule, and we l e a ~ n e d t on Apolle 9, although L would fur-ther have to say that there fs a strong suspicion in them i n d s of the crews on the bas i s of their simulation worktha t that rill probably turn out to be the preferred modeeven before 9 was flown.

QUESTI014: For how long wlll you be at 50,000 f ee t?There I s a dotted lfne on th e diagram, Could you with yourpointer just continue that and show arbem ft goes from the r e ,for how long it would be there?

M cM I l I J ZM : Could we put slide 31 back up, please?( S l i d e )I f you look at the s l i d e , you can notice that th e

radio lines that pass from t h e surface o f the moun up to thespacecraft are the- tagged. In other words, they start o f fhere at t h e left at 600 seconds before reaching pericynthionand pass on dawn to zero at T O 0 hours and 51 minutes grounde l apsed time, ascend up into th e very large orbit, we a i l 1come back d m gain to rwgh l y 50,000 feet,

UGE: f think t h i s diagrm kfnd of exemplifies*at Tom l a y have mentioned earlier. Th i s shows t h e moonas being round, and 3 t is -- almost. This o r b i t 2s elliptical.So the vehic le never in at a constant altitude. It startsout at higher than 50,000, comes d m to 50,000, and theng m s on up.

But it daesa*t change a l t i tude very fas t over t h i ss t r i p of arc,


78/84

QUESTION: A t this point , an that ellipticalmaneuver, if you have a spacecraft starting off at a fixedpoint on th e surface of the moon in motion and if you weresitting on the moon and couldn't . . . (Inaudible) . . ,There were a number of options, like waiting for t h e commandmodule to go around again, and a number of other t h i n g s .

5 have had it suggested t o me that if t h e timingof.thisburn, or the i n t e n s i t y of it, fa off by any appre-ciable amount t h a t the business of g e t t in g t h e lunar modu l eand the command module back together agatn would be enannous-ly complicated. Would you comment on that?

M c W N : Well, I thfnk we'd mak e a real-timeadjustment t o the phasing burn, A phaaing burn is designedto d o just exactly that -- to account for the difference int i m e of th e two spacecraft pass ing some point. So that ifwe da have a problem g e t t i n g the burn o f f , it w f l l just bea matter of changing the amaunt of velocity change and hencethe s i z e of t h e orbit that we use for phasing, and thatadjusts t h e time automatically,

QUESTION: Could you give me th e total number oforbits the CSM will e e round the moon, th e number oforbits 5t will make wZth the LM detached and the t i m e fromTLX to LOI?

HAGE: Y e s . Ars rt rule of thumb, it is one orbitevery two hours. That is a fairly accurate rule of thumb.I t will be in o r b i t 61-1/2 hours, and roughly 30 orbits .Let's see. The second part of your question was --QUESTION: How many of those orbits w&ll be with

the LM detached?IHAGE: With the LM detached?QUESTIOW: Yes.HAGG: Well, the LM is detached far a l i t t l e over

eight hours, so that would be four o r b i t s ,I QUESTION: Another part was t h e l ength of tkmefrom TLI to LOI.


79/84

3LBGE: TLI to XX)X? TLf occurs at twa hours and34 Pimtes from launch, and TEI occurs at Piwe days, IS hoursand 26 Ipimtes f m m launch,

QUESTXOB: W h a t about M)I?QaESTfOH: Could you repeat thuse ffgnres?HhQg: T r m s l u ~ a r njection, t w o b u r s and 34 mmfutesfrom launch, Lumar orbit insertion, the f f r s t orbit , t h e el-

liptical orblt, t m ays, four h o w , and 49 minutes. A n dtrrrnseartb injecrtion, f i v e days, 18 hours and 26 minutes.QUiWTIm: mce the lunar nodule is detached and

Zn its el1ipt ical orbit, if the ascent engine f a i l s is thereany way tha t the command module can dock with the lunar module?HkGE: Y e rst 8e. just comment on the afssion

philosophy. It In ident ical to t b e philusophy we had onA p a l l o 9 , There &a no situation during the separated rendez-vous wherein there isn't a backup propulsion made availablein the event t h a t th e primary mode f a i l s , such as usfng t h eBCS instead of the ascent propulsion, and on every maneuvert h e command module s5ll be targeting for a mirror imagemaneuver, and i n the e v e n t t h e I& i g n i t i o n does not takeplace, th e command and service modale will in effect makea mirror image maneuver that would bring t h e twa of them backtogether again.

Sa no single propulsion system fa i lure would presenta crew hazard, s i n c e t h e r e is always an alternate option wayof g e t t i n g the tw o vehicles together.QUESTION: Could we have that GBT chart up whilewe are talkfng? .HA=: Sure. Chart 12, please ,

O m ~ W I : hese charts will a l l be inc luded inth e tranacrfpt, incidentally.

let's switch now to Houston. When we come back, w ewill get some questions up in t h e back,


80/84

Does Houston have some questions?QUESTION: A s b p l e question, We d i d not haveth e benefit of th e slides that you had in Washington, Will

you give us throughout th e ent i re m i s s i o n t h e GET time formajor operations? Would you give us the npeckfic launchdays and the specific times of t h e windows for each day?Would you give us the GET times for th e TY?O'IDBN?4EXlfr: Those all will be Included in th e trans-

crfpts that we w i l l ge t out tomorrow. We w i l l get them downto Houston just as soon as we can.Do you have any more questions?QUESTIOPI: However, t h a t doesn't h e l p i f we arewriting a story ton i ght ,HAGE: B i l l , can I suggest that these might besent by telephone d i r e c t l y af ter t h e br i e f i ng?0-LL: All right, We a i l 1 send them down

by FAX machine. You should be get t ing them in another hour.Okay. Back here now,QUESTION: I'm i n t e r e s t e d in the earliest possiblelaunch, As I recall, Mr. Hage gave us 11:49 p .m . , E . S . T . ,

making t h i s the earliest p o s s i b l e launch, and then la terhe referred to a da y l i g h t launch and recovery, Will you cleart h i ~ p for me, please?

HAW: 1'11 t r y . 11:49 a , m . Eastern Standard Timean th e 18th, which resu l t s in a daylight launch and a day-l i g h t recovery,QUESTIm: Isn't there some confusion f i r s t of all,George? You keep saying 11 40 Eastern Standard, and th ecountry is on dayl ight . You mean 12:49, Eastern Daylight,dan*t you?HAGB: You" get me on th a t one, Jules. I thinkthis fs standard time. T think this is computed in standardtime. I t has not been corrected for d a y l i g h t yet .QUESTION: Okay. In there any chance st a11 of ,

t h e TY camera, black and white or color , being operated from


81/84

t h e Lhl during any of those low passes?AAGE: No, the prooisiom for t h e TV systemdontt exist in the lunar module, The activfties that the

crew will be involved in during that phase of the missfonare so demanding that we j us t didn't make provision for it.QUESTION: There is no way of simply bracket ingthe camera on while they are doing t h e i r landmark s i g h t i n g

and --MGE: There are no electrical connections for t h ecamera fn LM-4.QUESTION: Could someone summarize t h e number ofburns that will be made while you are in lunar orbit and

how many of these will take place out of sight of t h e earth?ISAGE: Both of the lunar orbit i n s e r t i o n burns,first the e l l i p t i c a l and then the circular orbit , are behindthe moon. Colonel McMullen is g d n g through the ones involvedin lunar o r b i t .McMULLBN: There w i l l be a total of f i v e Llld burnsthat are out of s i g h t e o f Manned Spaceflight Network and a

t o t a l of five that we will be a b l e to see from earth, so f i v ewe cannot and f i v e we can.QEST ION: The l as t f i v e lunar module?McMULUN: A l l t e n of those I gave were lunar moduleburns,RAGE: Transearth 3njection burn fs also Prom behindthe moon, the one that brings them out on the way home.McMULlZN: If you are keeping book on these, three

of t h e burn8 I-ve you were the braking maneuver, so we allwind up with numbers adding up to the r ight number of burns.

O13X)IWBLL: Let's get one question here and we'llswitch to Houston,


82/84

QIIBSTION: I wonder if George &b&e could g i v e usa progress report on t h i s experimental color TV camera thatWestinghouse is supposed to be working with.BAGE: We are quite optimbstfc that we w i l l Gaveit available on Apollo 10, 1 think the last val idat ion t e s twhfcb will give us th e go/no go w i l l be during countdowndemonstration when we can wark it into the whole s y s t e m ,including th e ground processing electronics through the

network to H o u s t o n .OtlXWNEIrZ12 Okay. We w i l l switch to Bouston a m .Any questions fn Houston?(Ho response.)A l l right. Back hare in Washington. A couple more.QlJBSTJON; What happens to th e . , . (Inaudible)?

A r e there any more burns to that to get it out?HA=: Xt will remafn in that high elliptical o r b i t .M c M U U E M : We have no way of commanding the d e s c e n t

stage once w e do tbe staging maneuver aP the lunar module,0'IHNN'EI;Z: Okay, Back here,QIIESTEON: . . . (Inaudible]. . . ill there beany other women's names on the moon as a resu l t of Apollo 101Ma: The procedure by which landmarks on th e moonare off5cially labeled As --QUESTION: X tm talking about unofficial labelling.HA=: 1 would be surprised if there aren't, butI don't know of any specific ones.QaxlpSTroHt Im t h e cs~se0% alternate missions, forimtance, t h e high e l l5 p t i ca l orbit , 5s it impassible inthat case to perfam as- k f d of practice operations?BAGE:. Mo, that part 8%the plan-- ft m i g h t bequite restricted in that w e obv%ously don't want to get t h e

t w o vehicles apart in a sense to tort extent where we can't


83/84

get then back together aga%n, but w@ have exercised t h ealternate missions to % a 8 maximum advantage of LM operations.QUESTION: Bra ApoHlo 8 without *5e I d yo12 had a

gmblem. HQW d o the raaergfns change now especially w i thmspect to propellants ow the BPS?

I.IAGE: Well, as you mentioned, t h e Apollo 8 margfnswere very comfortable because of the fact t h a t we didn'tcarry an LM to the moon, The margins on ApoPlo 10 axe alsoequal ly comfortable on the lunar module because w e are notgoing to land.

So in my own view I kind of equate ApoLlo 8emamand service module margins and 1LBI-4 module margins asequal level.

Xn case of CSM Awl l o 10, we will be operating atth e same consumable margins that we will be operatingApollo 12 st, Those are cwHfnr%able. 1 bel ieve the lowestone we have is something fw the order of 10 par cent of theto ta l , but I want to check that number. I t w # n that generalvltc inity . We have good margins planned into the CSM fort h e landing mission, and we will duplicate those conditkonswith the Apollo 10 PLight.QUXSTIOPI: George, could you dfscuas in a l i t t l emore d e t a i l th e changes that have k e n made to the l and ingradar? How m c h will th e augmented equipment weigh? A r e

you confident that 50,000-foot data will be translatableto 30,000-foot data? A n d what kind of test program for theuaft is scheduled?HA=: Before I get in to the specifics of t h e changes

on LM-4, John, jus t Pet me comment for a minute on t h e testprogram that is already taking place with t h e landing radarfly2ng aircraft.

We have had literally hundmds of equivalentmfssion t y p e s of operation w A t b the Ul landing radar flyingt h e a5rcraft over the colswglets spec%- of ranges tbat itwill be expected to operate over, The only t h i n g that isd i f f e r e n t is t ha t th e radar wa s working against t h e e a r t has a reflector instead of %he moon.

How, Arm order to f l y -4 in a way tbat would giweus the must IXBfoma$i~nlbom-lt the characteristics of the


84/84

lunar surface that might be d i f f e r e n t than we anticipate,we have added essentially electrical pickoffs from t h e fourbeam of t h e radar that are f e d out on telemetry systems,and we w i l l read the s ignature that comes back from t ho s efour 'beams and use it as a means of correlating with whatwe have gotten from our aircraft tests,

So we think ft is going to be a very meaningfultest ,I

OrDOHNELL: Any more questions?Back here.QUESTION: You s a i d that th e phase burn was designed

to g ive similar lighting condftions for the rendezvous, A r ethere other parameters?McWLLEES: PhasSng burn will w ind up with e ~ s r e n t i athe same lighting condit ions s i n c e it will be occurring inessentially the-- It will wind up within positions to giveus a rendezvous essentially above the same point s on t h e lunarsurface, so es sen t ia l l y the phasing burn coupled w i t h theinsert ion burn-- A t t h e completAon af the i n ser t i on burn weshould have conditions that are identical to what we will beseeing on t h e lunar landing mission at t h e completion of th e

l aunch and insertion into orbit from the lunar surface.O'DONNEU: One more,QUESTION: You mentioned th e possibility of th ecommand module going t o rendezvous wi th t h e lunar module.Does this in any way compromise your ability to leave thelunar, get the command back?HAGE : The service propulsion system propellantincludes capability for that kind of rescue, and the margins

apollo briefings

Documents