A13_PressKit

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N E W S

PRESSKIT

I NATIONAL AERONAUTICS A N D SPACE ADMINISTRATION WO 2-4155WASHINGTON,D .C. 0546 T E L S 4 WO 3-6925

RELEASE NO: 70-~OKFOR RELEASr? THURSDAY A . M .A p r i l 2 , 1 9 7 0

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RELEASE NO: 70-50

APOLLO 13 THIRD LUNAR LANDING MISSION

Apollo 1 3 , the third U . S . manned lunar landing mission,will be launchefi A p r i l 11 from Kennedy Space Center, Fla., t oexp l o re a h i l l y upland region of the Moon and bring back r o c k sperhaps f i v e billion years old,

The Apollo 13 lunar module will s t ay on the Moon moret h a n 3 3 hours and the l and ing crew will leave the spacecrafttwice t o emplace s c i e n t i f i c experiments on t h e lunar s u r f a c eand t o continue g e o l o g i c a l investigations. The Apollo 1 3landing site is i n t h e F r a Mauro uplands; the two NationalAeronautics and Space Administration ppevious landings were inmare or ''sea" areas, Apollo 11 in t h e Sea of Tranqullfty andA p o l l o 12 in the Ocean of S t o r m s .

Apollo 1 3 crewmen are commander James A . Lovell, Jr.;command module pilot momas K . MBttingly 111, and lunar modulepilot Fred W. Haise, Jr. Lovell is a U . S . Navy cap ta in ,Mattingly a Navy l i e u t e n a n t commander, and Haise a c i v l l i a n .

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Launch vehicle is a Saturn V .Apollo 1 3 o b j e c t i v e s a re :*sampling o f materials i n a preselected region of theFra Mauro fo rma t i on ,c Deploy a n d a c t i v a t e an Apollo Lunar SurfaceExperiment Package ( A L S E P ) ,* Develop man's capability t o w o r k i n t h e lunarenvironment.*

Perform s e l e n o l o g ic a l i n s p e c t i o n , survey a n d

Obtain p h o t o g r a p h s o f candidate exploration s i t e s .Cur ren t l y 11 television transmissions in color are

scheduled: one i n E a r t h o r b i t an hour and a half afterlaunch, t h r e e on the outward voyage t o t h e Moon; one o f thelanding s i t e from a b o u t n i n e miles u p ; two from th e l u n a rs u r f a c e w h i l e the astronauts work outside the spacecraf t ;one a t the command service rnodule / lunar module d o c k i n g operation;one o f t h e Moon from lunar orbit; and two on t h e return t r i p ,

The Apollo 1 3 l a n d i n g s i t e is in the h l l l y uplands tot h e n o r t h o f the crates F r a Mauro. Lunar co o r d i n a t e s f o r thel a n d i n g s i t e a re 3.6 degrees south l a t i t u d e by 1 7 . 5 degreesw e s t l o n g i t u d e , a b o u t 9 5 . 6 nautical miles e a s t o f the A p o l l o1 2 landing p o i n t a t S u r v e y o r I11 crater.

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Experiments emplaced a t t he F ra Mauro s i t e as part o ft h e ALSEP 111 w i l l gather and r e l a y l o n g - t e r m s c i e n t i f i cdata t o E a r t h fos a t l e a s t a year on t h e Moon's p h y s i c a l ande n vi ro n me n ta l p r o p e r t i e s . Five exper imen t s are co n t a i n ed i nt h e ALSEP: a lunar passive seismometer w i l l measure and relaymeteoroid impacts and moonquakes; a heat flow exper imen t w i l lmeasure the h e a t f l u x from t h e lunar i n t e r l o r t o t h e s u r f a c eand conduct iv i ty o f the s u r f a c e m a t e r i a l s t c a depth o f a b o u t1 0 f e e t ; a charged particle lunar environment experiment willmeasure pro t ons and e l e c t r o n s t o determine t h e e f f e c t o f t h esolar wind an the l u n a r environment; a c o l d cathode gaugeexper iment w i l l measure d e n s i t y and t emp er a t u r e variations i nt h e l unar a tmosphere ; and a d u s t d e t e c t o r e x pe r im e nt ,

The empty t h i r d s t a g e of t h e S a t u r n V l aunch vehiclew i l l b e t a r g e t e d t o s t r i k e t h e Moon b e f o r e t h e lunar landingand its impact will b e r eco r d ed b y the s ei sm om e te r l e f t byt h e A p o l l o 12 a s t r o n a u t s l a s t November. The s pen t l u n a r m o d u l ea s c e n t s tage , as in Apollo 12, w i l l b e d i r e c t e d t o i m p a c t t h eMoon a f t e r rendezvous and final LM s e p a r a t i o n t o provide asignal t o both seismometers .

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-4-C a n d i d a t e f u t u r e A p o l l o l a n d i n g s i t e s -- Censoyinus,

Davy R i l l e , and Descar tes -- w i l l b e photographed w i t h alarge-format lunar topographic camera c a r r i e d f o r t h e f i r s ttime on A p o l lo 1 3 . The lunar t o p o g r a p h i c camera will make h l g h -resolution 4 .5 i n c h square black-and-white p h o t o s in o v e r l a p p i n gsequence f o s m o s a i c s o r in s l n g l e frames. The camera mounts i nt h e command module crew access h a t c h window when i n u s e . A f t e rl u n a r orbit rendezvous with t h e lunar module and LM j e t t i s o nt h e command nodule w i l l make a plane-change maneuver t o drivet h e orbital t r a c k o v e r Dtiscartes and Davy R i l l e f o r t o p o g r a p h i cphotogPaphy.

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The ApoLlo 13 f l i g h t p r o f i l e i n g e n e r a l f o l l o w s thoseflown b y A p O l l 0 5 11 and 1 2 w i t h one m a j o r e x c e p t i o n :i n s e r t i o n b ur n n o . 2 has been combined with d e s c e n t orbitinsertion and t h e docked s p a c e c r a f t w i l l b e p l a c e d i n t o a 7x57naut ica l . mi l e l u n w osbit by use of the s e r v i c e p r o p u l s i o ns y s t e m . Lunar module d e s c e n t p r o p e l l a n t i s conserved b ycombining t h e s e maneuvers t o p r o v i d e 15 s e c o n d s o f a d d i t i o n a lhover time d u r i n g t h e l an d l n g .

l u n a r o r b l t

Lunar s u r f a c e touchdown i s s c h e d u l e d t o take p l a c e at9 : 5 5 p.m. E S T A p r i l 15, and two periods of e x t r a v e h i c u l a ra c t i v i t y are planned a t 2:13 a.m. E S T A p r i l 1 6 and 9 : 5 8 P . m .EST A p r i l 1 6 . The LM a s c e n t s t a g e will l i f t off a t 7 : 2 2 a.m.A p r i l 17 t o r e j o i n the o r b i t i n g command module a f t e r m o r e than3 3 h o u r s on the lunar s u r f a c e .

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Apollo 1 3 will leave l u n a r o r b i t a t 1 : 4 2 p.m. EST A p r i l1 8 f o r r e t u r n t o E a r t h .south of the E q u a t o r will b e a t 3:17 p.m, E ST A p r i l 21.

Splashdown i n t h e mid-Pacific j u s t

A f t e r t h e s p a c e c r a f t has l a n d e d , the crew will pu t onclean coveralls and f i l t e r masks pas s ed i n to them throughthe h a t c h by a swimmer, and t hen t r a n s f e r by h e l i c o p t e r to aMobi le Q u ar an t i n e Facility (MQF) on t h e USS Iwo Jima. TheMQF and crew w i l l be o f f l o a d e d i n Hawaii and placed aboard a(2-141 a i r c r a f t f o r t h e flight back t o t h e Lunar ReceivingLaboratory a t t h e Manned S pacec ra f t Center i n Hauston. Thecrew w i l l remain in quarantine up to 21 days from completionof' the second EVA.

The mew of A p o l l o 1 3 s e l e c t e d the c a l l s i g n s Odyssey f o rt h e command/sesvice module and Aquar ius for the l u n a r module.When all three crewmen are a b o a r d the command module, the c a l lsign will b e "Apollo 13.'' A s in t h e two previous lunar landingm is s ions , an American flag w i l l b e emplaced on the l u n a r s u r f a c e .

' A plaque bearing t h e d a t e o f t h e A p o l l o 13 l a n d i n g and t h e crews i g n a t u r e s i s a t t a c h e d t o t h e LM.

Apol lo 13 backup crewmen are USN commander John W. Young,commander; c i v i l i a n John L . Swigert, Jr,, command module p i l o t ;and LkAF Major C h a r l e s M , Duke, J r . , lunar module p i lo t .

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APOLLQ I3 - LAUNCH TO LUNAR SURFACE.....

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APOLLQ 13 - LUNAR DRILL & ALSEP PACKAGE


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T-9 hours

T-8 hour s , 05 minutes

B u i l t - i n h o l d for 9 hours and 13minutes . A t end of h o l d , pad i scleared f o r LV propellant loadingLaunch v e h i c l e p r o p e l l a n t l o a d l n g -Three s tages ( L O X i n first s t a g e ,LOX and LR 2 in second and thirdstages). Continues t h r u T-3hours 38 minutes

T-4 hours , 1 7 minutes Flight crew alertedT-4 h o u r s , 0 2 minutes Medical examinat ionT-3 hours , 3 2 minutes BreakfastT-3 h o u r s , 30 minutes One-hour ho l dT-3 hours, 07 minutes Depart Manned Spacecraft OperationsBui l d i ng f o r LC-39 v i a crew transfer

V a n .T-2 h o u r s , 55 minutes Arrive a t LC-39T-2 h o u r s , 4 0 minutes Start f l i g h t crew i n g r e s sT-2 hours Mission C o n t r o l Center - Houston/s p a c e c r a f t command checksT - 1 h o u r , 5 5 minutes A b o r t advisory s y s t e m checksT-1 h o u r , 51 minutes Space Vehic le Emergency D e t e c t i o nSys t em (EDS) e s t'11-43 minutes Retract Apollo a c c e s s a r m t o stand-by p o s i t i o n (12 de g r e e s )T-42 minutes A r m l a u n c h e s c a p e s y s t e mT-40 minutes

T-30 minutes

F i n a l launch. e h i c l e range safetychecks ( t o 35 minutes)Launch v e h i c l e power transfer t e s tLM s w i t c h over t o i n t e r n a l power

T-20 minutes t o T-10 minutes Shutdown LM o p e r a t i o n a li n s t r u m e n t a t i o nT-15 minutes S p a c e c r a f t t o i n t e r n a l power

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T-6 il15.nutas Space v e h j c l e final status c h e c k sT-5 mi.nu.+;es 30 r , emuds A r m d e s t r u c t systemT-5 minuts: Apollo a c c e s s arm f u l l y r e t r a c t e dT -3 minutes, 7 secoi ids Fi r ing command (automatics e q u e n c e )

Launch v e h i c l e transfer t o internalpowerT-8.9 S ~ C ~ ~ C S Ignition s e q u e n c e s t a r tT-2 L ~ > c o ! I ~ : ; All e n g i n e s r u n n i n gT-0 L i f t o f f

Note: Some c h a n g e s in t h e above countdown a r e p o s s i b l e as ar e s u l t of e x p e r i e n c e ga ined in t h e countdown demonstration t e s twhich occ i i r s abou t 1 0 d a y s b e f o r e l a u n c h .L i g h k n i n g ??>ecautlons.-

During t h e Apollo 1 2 m i s s i o n t h e space v e h i c l e wass u b j e c t e d t o two distinct e l e c t r i c a l d i s c h ar g e events.However, no serious damage occur red and t h e x i s s i o n p r o -ceeded t o a s u c c e s s f u l c o nc l us i on . I n t e n s i v e i n v e s t i g a t i o nl e d t o t h e c o n c l us i o n t h a t no h a r d w a r e changes were n e c e s s a r yto p r o t e c t t h e s p a c e v e h i c l e from s i m i l a r events. F o r Apollo13 the mission r u l e s have b e e n r e v i s e d t o r educe t h e p r o -bability that t h e s p a c e vehicle will b e l a u n c h e d I n t o c l o u df o r m a t i o n s that c o n t a i n c o n d i t i o n s c o n du c iv e t o initiatingsimilar electrical discharges although f l f g h t into a l lc l o u d s i s n o t p r e c l u d e d .

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May Launch Opportuni t iesThe three o p p o r t u n i t i e s established f o r May -- i n c a s et h e launch i s pos tponed from April 11 -- p r o v i d e , i n effect,t h e f l e x i b i l i t y o f a choice o f two launch a t t empts . Theoptimum May launch window occurs on May 1 0 . The t h r e e d a ywindow permits a c h o i c e o f a t t e m p t i n g a launch 24 hoursearlier t h a n t h e optimum window and i f n e c e s s a r y a f u r t h e rc h o i c e o f a 24 hour o r 48 h o u r r e c y c l e . I t a l s o permits achoice o f making the f i r s t l a u n c h a t t e m p t on the optimumday with a 24-hour recycle c a p a b i l i t y . The May 9 window (T-24hrs) requi res an a d d i t i o n a l 24 hours i n l u n a r orbit b e f o r ei n i t i a t i n g powered d e sc e nt t o arrive a t the l a n d i n g s i t e a tt h e same time and hence have th e same Sun angle f o r l a n d i n gas on May 1 0 . Should t h e May 9 window l a u n c h attempt be

sc rubbed , a d e c i s i o n w i l l be made a t that t i m e , based on t h ereason f o r t h e s c ru b , s t a t u s of s p a c e c r a f t cryogenics andweather p r e d i c t i o n s , w h e t h e r t o recycle for May 10 (T-0 h r s )or May 11 (T+24 h r s ) . If launched on May 11, the flightp l a n w i l l be similar f o r t h e May 10 mtss ion b u t the Sune l e v a t i o n angle a t lunar l a n d i n g w i l l b e 18.5O i n s t e a d of7.8O.

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K**+*ASCENT STAGE-JETTISON. (REV 34)

tM INSERTiONl O % N M EARTHPARKING ORIIT LM POWERED DESCENTINlf lATION WV 14)

CSM/LM SEPARATIONCIRCULARIZATION(REV 12) 60 NMCM SPLASHDOWN

S-IVB RESTARTTRANS LUNAR INJECTION -LO1 CSM W

S-IVB EVASIVE M A N ECSM LM:: 7 x 57z (12 ORBITS)

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APOLLO 13 FLIGHT PROFILE


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LAUNCH, M I S S I O N TRAJECTORY A N D MANEUVER DESCRIPTIONThe information p r e s e n t e d h e r e i s based on an on-timeA p r i l 11 l a u n c h and i s s u b j e c t t o change b e f o r e o r d u r i n gt h e m i s s i o n t o meet c h a ng i ng c o n d i t i o n s .

Launchcraft from Launch Complex 39A, NASA-Kennedy S p a c e C e n t e r , F l a .The azimuth may vary from 72 t o 9 6 deg ree s , depend ing on t h etime o f l aunch . The azimuth changes w l t h l aunch t i m e t op e r mi t a fue l -op t imum in jec t ion from E a r t h parking orbit t oa free-return circumlunar t r a j e c t o r y .

A S a t u r n V l a un ch ' v e h i c l e will l i f t t h e Apol lo 1 3 space-

A p r i l 11 l a u n c h p l a n s c a l l for l i f t o f f a t 2:13 p.m. ESTon an azimuth of 7 2 degrees. The v e h i c l e w i l l r e a c h an a l t i t u d eo f 36 nautical miles before f i r s t s t a g e cutoff 51 nm downrange.During t h e 2 minu tes 4 4 seconds o f powered f l i g h t , t h e firststage w i l l i n c r e a s e v e h i c l e v e l o c i t y t o 7 , 7 7 5 f e e t p e r secondfFirst s t a g e t h r u s t w i l l r e a c h a maximum o f 8 , 9 9 5 , 1 0 8 poundsb e f o r e c e n t e r e ng i ne cutoff. Afte r eng ine shu tdown ands e p a r a t i o n from t h e second s t ag e , the b o o s t e r w i l l fall I n t ot h e A t l a n t i c Ocean a b o u t 364 nm downrange from the l a u n c h site( 3 0 deg rees Nor th l a t i t u d e and 74 degrees West l o n g i t u d e )about 9 minutes 4 seconds a f t e r liftoff.

The second s t a g e (S-11) w i l l c a r r y t h e space v e h i c le t oan a l t i t u d e o f 1 0 2 nm and a d i s t a n c e of 8 9 2 nrn downrange. A te n g i n e shutdown, t h e v e h i c l e will b e moving at a v e l o c i t y of21 ,508 f p s .3 2 seconds dur ing the powesed p h a s e , b u t t h e center eng inewill b e c u t o f f 4 minutes 47 seconds after S - I 1 ignition.

The f o u r o u t e r J - 2 e n g i n e s w i l l b u r n 6 minu tes

A t o u t b o ar d e n g i n e c u t o f f , t h e S - I 1 will separate and ,following a b a l l i s t i c t r a j e c t o r y , plunge i n t o t h e A t l a n t i ca b o u t 2 ,450 nm downrange f r o m t h e Kennedy Space Center ( 3 1degrees N or t h l a t i t u d e and 33.4 d e g r e e s West l o n g i t u d e ) some20 minutes 4 1 seconds after liftoff'.The s i n g l e engine of t h e S a t u r n V t h i r d s t a g e (S-IVB)will i g n i t e a b o u t 3 seconds after t k : e S-I1 s t a g e s e p a r a t e s .The e n g i n e w i l l f i r e f o r 143 s e c o n d s t o insert the spacevehicle into a c i r c u l a r Earth p a r k i n g o r b i t o f lo3 nm beg i n -i n g a b o u t 1,468 nrn downrange. V e l o c i t y a t E a r t h o r b i t a l

i n s e r t i o n will b e 24,243 f p s at 11 minu tes 5 5 second grounde l ap sed t i m e ( G E T ) . I n c l i n a t i o n w i l . 1 be 33 degrees t o t h ee q u a t o r .*NOTE: Multiply nautical miles b y 1.1508 t o o b t a in s t a t u t emiles ; multiply f e e t per second by 0 . 6 8 1 8 t o o b t a i ns t a t u t e m i l e s p e r h o u r .


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The crew w i l l have a backup to launch veh ic le gu idancedur ing powered f l i g h t . If the Sa t u rn instrument unit i n e r t i a lp l a t fo rm f a i l s , the crew can swi tch guidance to the commandmodule systems fox- first-stage powered f l i g h t automaticcontrol. Second and t h i r d stage backup guidance is throughmanual takeover in which spacecraft commander hand c o n t r o l l e rinputs are fed through the command module computer to the Saturninstrument unit.

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Launch EventsRangei m e A ItIud VelocityH P S . Min. ~ Z C . Event Feet Ft /Sec JC Naut . Mi.

00 00 00 First Motion 198 0 000 01 23 Maximum Dynamic Pressure 42,139 1,600 3

0 0 0 2 4 4 S-IC Outboard Engines C u t o f f 218,277 7 , 7 7 5 5100 0 2 45 S-IC/S-I1 Se pa r a t i on 220 ,576 7,804 5200 0 2 46 S-I1 Ignition 225,368 7,788 54

00 0 3 20 LET Jettison 313 ,619 8,276 9500 07 4 3 S-II Center Engine Cutoff 588,840 17,650 60300 09 18 S-11 Outboard Engines C u t o f f 615,508 21,503 89 20 0 09 19 S-II/S-IVB S e p a r a t i o n 615 ,789 21 ,517 8950 0 o g 2 2 S-IVB I g n i t i o n 616,616 21,518 90 600 11 4 5 S - I V B F i r s t C u t o f f 6 2 7 , 9 9 6 2 4 , 2 3 9 1 ,429

00 0 2 15 S-TC Center Engine Cutoff 139,856 5 ,120 24

00 0 3 14 S-I1 A f t I n t e r s t a g e Jettison 300 ,222 8 , 1 7 3 88

P a r k i n g Orbit Insertion 6 2 8 , 0 1 4 24 ,243 1 , 4 6 80 0 11 55

* Not including v e l o c i t y due t o Earth's rotation, abou t 1,350 fee t -per - second.


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Apolla 13 Mission EventsE v e n t s

E a r t h o r b i t insertionTranslunar injection(S-IVB Engine ignition)CSM separation, dockingE j e c t i o n f r o m SLAS-IVB evasive maneuver

Midcourse correction 1Midcourse correction 2( H y b r i d t r a n s f e r )Midcourse correction 3Midcourse correction 4

Lunar o r b i t insertion

S-IVB impact

GET Vel. ChangeHrs. :Min. Date/EST Feet/Sec. Purpose & Resultant O r b iI n s e r t i o n into 103 nm c icular Earth parking orbi0 0 ; 11 11 2 : 2 4 p.m. 25,593

02 : 35 11 4 :48 p.m. 1 0 , 4 3 7 I n j e c t i o n into free-retutranslunar trajectory w i210 nm pericynthion.0 3 : 0 6 11 5:l .g p.m, -I Hard-mating of C S M and L04 : 0 0 11 6 : 1 4 p.m. 1 Separa'ces CSM-LM fromS-IVB-SLA.0 4 :19 11 6 : 3 2 p.m. 9.4 PrGvides separation prioto S-IVB propellant dumpand thruster maneuver to

T L I t 9 h r s 12 1;54 a.m. "0 *These midcourse correc-cause lunar impact.t i o n s have a nominal vel3 0 : 4 1 12 8 : 5 4 p.m, 1 5 city change of 0 f p s , buw i l l be calculated i n retime t o correct TLI d i s -

LOI-22 hrs. 13 9 : 3 8 p.m. * O persions. MCC - 2 is an Smaneuver (15 f p s ) to lowLOI- 5 h r s , 14 2 :38 p.m. * O pericynthion to 59 nm;trajectory then becomesnon-free return.Inserts Apollo 13 into57x168 nm elliptical l u norbit.

77: 25 14 7 3 8 porn* - 2 8 1 5

77 :46 14 7 : 5 9 p . m . -- Seismic event.


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GET Yel. ChangeEvents firs, :Min. 3 a t e / E S T Feet/Sec. Purpose & Resultant O r b-Descent o r b i t insertionCSM-LM undocking

CSM c i r c u l a r i z a t i o nLF powered deszenti n i t i a t i m :PD:>

LF tovtzhdown on l u n a rs u r f a c e .

81:45

100 351 0 3 : 3 1

Depressurlzation f o r 1 3 8 : O Of l y s t l u n a r s.,:.rface E V A ,CP3 s te p 5 t o s u r f a c e 108 15

108 :21Xi? o l l z c t s contingencysamgles;I,?.?teps to su r face 108: 7CC? unstows and e r e c t s 108 2$-:isnd antennaLM? aounts TV camera on 1 @ 8 : 3 4t;': ;? 36.

1 1 ~ 5 8 .m.15 5 : 2 9 p.m.

1 5 6 : 4 8 p.m.15 9:44 p . m .

1 6 2 2 9 a.m.16 2 : 3 4 a.m.16 2 : 4 0 a.m.16 2 : 45 a.m.16 2 : 4 7 a.m.

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7 0

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SPS bur n p l a c e s CSM/LMi n t o 7x57 nm lunar o r b i tEstablishes e q u i p e r i o dorbit for 2 . 5 nm s e p a r a ta t PD T maneuver .I n s e r t s CSM into 52x62 no r b i t .Three-phase maneuver t obrake LY out of transfero r b i t , vertical d e s c e n ta?d touchdown on l u n a rsuyface.Lr:nar exp lo i*a$ ion , d :p loAL-SEP l u n a r surface geo-:z;ic*L sample c o l l e c t i o?;iotogF?phy.


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GET Vel. ChangeEven t s Hrs. :Min. Date/EST Feet/Sec. Purpose & R e s u l t a n t O r b iLMP reenters LM t o s w i t c ht o S-Band antennaLMP r e t u r n s t o luna rs u r f aceCDR dep loys U.S. f l a gCDR and LMP begin un-stowing and deploymentof ALSEPCDR and LMP r e t u r n t o EMcollecting samples enrou teCDR and LMP a r r i v e backat LM, stow gear andsamplesLMP d e p lo y s s o l a r windcomposition experimentLMP reenters LMCDR r e e n t e r s LMLM hatch c losed , r epressCSM plane changeDepress for EVA-2CDR s t e p s to surfaceLMP s t ep s t o surface

108 3108:57109 : 4

109 30111: 0

111 01 1 1 : 3 4111: 3111: 8111:59113 : 3127 5127 : 8128 : 7

16 2:56 a . m .16 3:lO a . m .16 3:17 a . m .

16 3:43 a.m.16 5 : 2 3 a.m.

16 5:33 a . m .1616161616161 616

5:47 a . m .5:56 a.m.6:ll a.m.6:12 a . m .7 : 5 6 a.m.9 : 5 8 p.m.10:11 p . m .1O:ZO p . m .


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ET Yel. ChangeEvent Hrs. Min. Date/EST Feet/Sec. Purpose & Resultant OrbBegin field geology travers,collect core t u b e and gasanalysis samples, dig s o i lmechanics t r e n c h , magneticsample collec tion. 128:18Complete geology traverse 131:04Return to LM a r e a , r e t r i e v esolar wind experiment, s t o wgear and samples. 131: 5LMP enters LM 131: 8CDR transfers samples,LMP a s s i s t s 131 35CDR enters LM, close h a t c h 131:41Repress cabin 131:44LM ascent 1 3 7 : 09

Insertion into l u n a rorbit 137 16LM RCS concentric sequenceinitiation (CSI) burn 138 19

LM RCS constant d e l t aheight (CDH) b u r n 139 04

161 7

171 717171 71 7

1717

1 7

1 0 ~ 3 1 n .1 : 1 7 a.m.

1:18 a.m.1:41 a.m.1:48 a.m.1 : 5 4 a.m.1:57 a.m.7 : 2 2 a.m. 6 ,044

7 : 2 9 a,m.8 : 3 2 a.m.

9 : 1 7 a .m .

5 0

Boosts stage i n t o 9 x 4 5 nlunar orbit f o r rendez-vous with CSM.

Raises LM perilune to 4 4nm, adjusts o r b i t a l s ha pf o r rendezvous sequence.Radially d o w n w ar d b u r n aj u s t s LM o r b i t t o consta15 nm below CSM.


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GET V e l . ChangeEvent E r a . : M i n, D a t e / E S T Feet/Sec. Purpose & R e s u l t a n t O r b iLM R C S terminal phase 139: 6 17 9 : 5 9 a . m . 211.7 LM thrusts along l i n e o fsight toward CSM, m i d -course and braking maneuvas necessary.Rendezvous (TPF) 140: 7 17 10:40 a.m.Docking 1 4 0 : 4 5 17 10:58 a.m.LM J e t t i s o n , separation(SM R C S ) 143 :04 17 1:17 p,m.

Completes rendezvous se-quence.Commander an d LM p i l o tt r a n s f e r b a c k to CSM.PrevenSs recontact of CSMw i t h LM ascent s t ag e dur-i n g r e m a i n d e r of lunarorbit.

LM ascent s tage d e o r b i t(RCS) 1 4 4 : 3 2 17 2 :45 p . m . -186 Seismometer r e c o r d s i m D aevent.LM ascent s tage impact 145 00 17 3:13 p . m .

Plane c h a n g e f o r photos 154:13 18 1 2 : 2 6 a.m.

Irnpacg at a b o u t 5,508 f pa t - 4 a n g l e 35 nm fromA p o l l o 13 ALSEP.Descartes and Davy-Rillep h o t o g r a p h y ,

Transearth injection(TEI) SPS 167 : 9 18 1:42 p . m , 3,147 T n j e c t C S M i n t o t r ans -e a r t h trajectory.


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GET V e l . ChangeH r s . :Min, D a t e / E S T Feet/Sec. Purpose & Resultant O r bventMidcourse correction 5 1 8 2 :31 1 9 4:44 a . m . 0

Midcourse correction 6 EI-22 h r s 2 0 5 : 0 3 p.m. 0Midcourse correction 7 EI- 3 h r s 21 12:03 p . m . 0CM / SM separation 2 4 0 : 3 4 21 2 : 47 p . m . c-

Entry interface(400,OOOf e e t ) 2 4 0 ; 5 0 21 3:03 p,m. --Splashdown 241: 4 21 3 : 1 7 p.m. --

Transearth midcourse c orections will be computin r e a l t i m e f o r e n t r yc o r r i d o r c o n t r o l and recovery area weatheravoidance.

Command module orientedf o r e n t r y .Command Module e n t e r sEarth's s e n s i b l e atmos-phere a t 36,129 fps.Landing 1 , 2 5 0 nm d o w ~ f -range from entry 1.5South l a t i t u d e by 157.5'West longitude.


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A mid-course correction will b e made w i t h the stage'sa u x i l i a r y propulsion system ( A P S ) ullage motors. A secondAPS b u r n w i l l be used If necessary, at about 9 hours GET, t of u r t h e r a d j u s t t h e impact point. Burn tlme and attitude w i l lbe determined from onboard systems and tracking data providedto ground controllers by the Manned Space F l i g h t Network.The LOX dump by itself would p r o v i d e a lunar impact; themid-course correction burns will p l a c e the S-IVB/IU w i t h i n thedesired target area f o r impact a b o u t 20 minutes a f t e r the com-mand/service module enters lunar orbit.The schedule of events concerning the lunar impact is:

TimeH r s :Min020 4

0 40 4040 40 4060 80977

4 21 9213641414 2005 90 446

EventTranslunar i n j e c t i o n ( T L I ) --maneuver completionBegin S-EVB evasive maneuver ( A P Sengines)End evasive rnaneuve.?LH2 tank c o n t i n u o u s vent onBegin LOX dumpLH2 tank continuous vent o f fEnd LOX dumpBegin first APS burnBegin final APS burn (if required)APS ullage engines o f fLunar impact of S-IVB/IU

T ra n s l u n a r CoastUp to four midcourse correction b u r n s a r e planned duringthe spacecraft's translunar coast, depending upon the accuracyof the trajectory r e s u l t i n g from the T L I maneuver. If required,t h e midcourse correction burns a r e planned at T L I + 9 hours, TLI+3 0 h o u r s , 41 minutes, l u n a r orbit insertion (LOI)-22 h o u r s andL O I - 5 h o u r s . The MCC-2 is a 1 5 f p s SPS h y b r i d transfer maneuverwhich lowers pericynthion from 210 nrn t o 59 nm and p l a c e s A p o l l o13 on a non-free-return trajectory.

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Return t o t h e free-return t r a j e c t o r y i s a l w a y s withinthe capability of the spa c e c r a f t service propulsion o r des-cent propulsion systems.During coast pe r iods between rnidcourse corrections, thes p a c e c r a f t w i l l be in t h e passive thermal control (PTC) or"barbecue" mode i n which t h e spacecraft will rotate slowlyabout its r o l l a x i s t o s t a b i i i z e spacecraft thermal responset o t h e continuous solar e x p o s u r e .

Lunar O r b i t Insertion (LOI)The lunar orbit insertion b u r n w i l l be made a t 77 :25 GETa t an a l t i t u d e of about 85 nm above the Moon. The L O 1 burnwill have a nominal retrograde v e l o c i t y change of 2815 f p s andw i l l insert Apollo 13 i n t o a 57x168 nm e l l i p t i c a l lunar orbit.

Descent Orbit Insertion (DOI)C SM /LM into a 7x57 nm lunar orbit from which t h e LM w i l l begint h e later powered descen t t o landing. I n Apollos 11 and 12,DO1 was a separase maneuver using the LM descent engine.Apollo 13 DO1 maneuver in effect is a combination LOI-2 and D O 1and produces t w o benefits: conserves LM descent propellanttha t would have been used for D O 1 and makes this propel l a f i ta v a i l a b l e for a d d i t i o n a l h ove r t i m e near the surface, and a l low s11 l u n a r revolutions of spacecraft tracking i n t h e descent orbitt o enhance position/velocity ( s t a t e vector) data f o r updatingt h e LM guidance computer d u r i n g the descent and l a n d i n g phase.

A 213 f p s SPS retrograde burn a t 8 1 1 4 5 GET w i l l place t h eThe

Lunar Module S e p a r a t i o nThe l u n a r module w i l l be manned and checked out for un-docking and subsequent landing on t h e l u n a r surface n o r t h oft h e crater, Fra Mauro, Undocking dur ing t h e 1 2 t h r e v o l u t i o nwill take p l a c e a t 99:16 GET. A radially downwa rd servicemodule R C S burn of 1 f p s w i l l place t h e CSM on an equ iper iodo r b i t with a maximum separation of 2.5 nrn.

CSM C i m u l a r i z a t i o na t 100:35 GET w i l l place the CSM i n t o 52x62 nm lunar o r b i t ,which because of perturbations of the lunar gravitational po-t e n t i a l , should become nearly c i r c u l a r a t the time of rendez-vous w i t h the LM,

During the 1 2 t h r e v o l u t i o n , a 70 f p s posigrade SPS burn

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Power Descen t Initiation (.PDI),Lunar LaridingDuring the 14th revolution a three-phase powered descen t(PD) maneuver begins at pericynthion at 103:31 GET using theLM descent engine t o brake t h e vehicle out of the descent orbit.The guidance-controlled PD maneuver starts about 260 nm prior

to touchdown, and is in r e t r o g r a d e attitude to reduce velocityt,o essentially zero a t the time vertical descent begins. Space-c r a f t attitude wlll be windows up from powered descent initia-tion to the end of the braking phase so that the LM landingradar data can b e integrated continually by the LM g u i d a n c ecomputer and better communications can be maintained. Thebraking phase ends at about 7,400 feet above the surface andthe spacecraft is r o t a t e d more toward an upright windows-forwardattitude to permit a view of the landing site. The start of theapproach phase i s called high gate, and t h e start of the landingphase at about 500 feet is called low gate.Both the approach (visibility) phase and landing phaseallow p i l o t takeover from guidance control as w e l l as visualevaluation of the landing site. The final vertical descent totouchdown begins at about 100 f e e t when all forward velocity isnulled out. Vertical descent r a t e w i l l be 3 f p s . The crew mayelect to take over manual control at approximately 500 feet.The crew will be a b l e to return to automatic landing controlafter a period of manned maneuvering if desirable. Touchdownw i l l t a k e p l a c e at 1 0 3 : 4 2 GET.

Lunar Surface ExplorationDuring the 33 1/2 hours A p o l l o 13 commander James Love11

and lunar module pilot Fred Haise a r e on the surface, they w i l lleave the lunar module twice f o r four-hour EVAs. These are ex-tendable to five h o u r s i n r e a l time if the physical c o n d i t i o n sof the astronauts and amount of remaining consumables permit.In addlition to gathering more d a t a on the lunar environ-ment and b r i n g i n g back geological samples from a t h i r d lunarlanding site, Lave11 and Kaise will d e p l o y a series of experl-rnents which w i l l r e l a y b a c k to Earth long-term scientificmeasurements of the Moon's p h y s i c a l and environmental properties.The experiments series, called the Apol l o Lunar SurfaceExperiment Package ( A L S E P ) , w1II be l e f t on the surface and

c o u l d transmit scientific and engineering data to the MannedSpace Flight Network for at least a y e a r .The ALSEP for A p o l l o 13, stowed I n the LM descent stagescientific equipment b a y , comprises components for the f i v eA L S E P experiments -- passive seismic, heat flow, charged par-ticle lunar environment, cold cathode gauge, and l u n a r dustdetector.

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These experiments a re aimed toward d e t e r m i n i n g thes t r u c t u r e and s t a t e of t h e lunar i n t e r i o r , t h e compositionand s t r u c t u r e o f the l i i n a r s u r f a c e and p r o c e s s e s which modifyt h e s u r f a ce , and e v 1 3 1 ut i o n a ry s e q u e n c e l e a d i n g to t h e Moon'spresent c h a r a c t e r i s t i c s . The P a s s i v e S e i s mi c E x p e r i me n t w i l lbecome t h e s ec on d p o i n t i n a lunar s e i s m i c n e t b eg un w i t h t h efirst ALSEP a t t h e Surveyor I11 l a n d i n g s i t e of Apollo 1 2 .Those two seismometers must; cont j -nue t o operate untll the nex tse i smomete r i.se mp la ce d t o c o mp l e t e t h e three-station s e t . Thehea t f l o w exper imen t i n c l u d e s d r i l l i n g two 10- foo t h o l e s witht h e l u n a r sur l face d r i l l .While on t h e surface, t h e crew's o p e r a t i n g r a d i u s will b el l i n i t e d b y t h e r a n g e p r o v i d e d b y t h e oxygen purge sys t em (OF 'S) ,t h e r e s e r v e oaekup .for e a c h man's p o r t a b l e l i f e s u p p o r t s y s t e m(PLSS) backpack . The OPS supplies 45 minu tes o f2mergencyb r e a t h i n g 0xyge.n a nd s u i t p r e s s u r e .Among o t he r t a s ks as s i gne d t o L o v e l l and Haise for thetwo EVA p e r i c d s a r e :% C o l l e c t a c o n t i n g e n c y sam pl e of a b o u t t w o pounds ofl u n ar m a t e r i a l .#Ga t he r about 95 pounds o f r e p r e s e n t a t i v e lunar s u r f a c ematerial, i n c l u d i n g co;-e samples, individual rock samples andf i n e - g r a i n e d f r a g me n t s f ro m t h e Fra Mauro h i l l y u p l a n d s s i t e ,The crew will p h o t o g r a p h t h o r o u g h l y t h e a r e a s from which sam-p l e s are t a k e n ."Make observations and g a t h e r da ta on t h e m e c ha n ic a lproperties and t e r r a i n characteristics o f t h e l u n a r surfaceand c o n d u c t i n g o t h e r l i i na r f i e l d g e o l o g i c a l s u r v e y s, i n c l u d i n gdigging a two-foot d e e p t r e n c h f o r a s o i l mechanics i n v e s t i g a t i o n .* P h o t o g r ~ p hw i t h -.;he l u n a r stereo c l o s e u p camera smallg e o l o g l c a l f e a t u r e s t ha t would b e d e s t r o y e d i n a n y a t t e m p t s t og a t h e r them f o r r e t i i r n t o E a r t h .* D e p l o y and r e t r i e v e a windowshade- l ike so la r wind compo-s i t i o n experiment s imi l a r t o the ones used i n A p o l l o s 11 and 12.E a r l y in t h e f l p s i ; E V A , L o v e l l and Haise w i l l s e t u p the

e r e c t a b l e S-Band an';enria near t h e LM f u r relaying v o i c e , T V ,and EM t e l e m e t r y t o MSFN s t a t i o n s . A f t e r t h e a n t e n n a i s de-p l o y e d , Haise will cl i rab b a c k i n t o t h e LM t o s wi t c h from theLM s t e e r a b l e S-Band a n t e n n a t o t 3 e e r e c t a b l e a n te n na w h i l eL o v e l l makes f i n a l adjustments t o t h e antenna's a l i g n m e n t .Haise will t h e n r e j o i n L ov el l o n t h e lunar s u r f a c e to s e t upa United S t a t e s f l a g and continue with EVA t a s k s .

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Red s t r i p e s a r o u nd t h e e lb ow s a nd k n ee s of L o v e l l ' spressure s u i t w i l l p e r mi t crew r e c o g n i t i o n d u r i ng EVA t e l e -vision transmissions and on photographs.Ascent, Lunar Orbi t Rendezvous

Following t h e 33-hour lunar stay t h e LM a s c e n t s t a g e w i l ll i f t o f f t h e lunar s u r f a c e t o b e g i n t h e r endezvous sequence ' Iwith t h e o r b i t i n g CSM. I g n i t i o n o f t h e LM ascent e n g i n e w i l l 'b e a t 137:09 f o r a s e v e n minute e i g h t s ec on d b u rn a t t a i n i n g atotal velocity o f 6 , 0 4 4 f p s . Powered ascen t i s i n t w o p h a s e s :v e r t i c a l a s c en t f o r t e r r a i n c l e a ra n ce and t h e o r b i t a l i n s e r -t i o n p h as e . P i t c h o v e r a l o n g t h e d e s i r e d l a u n c h a z im u th b e g i n sas t h e v e r t i c a l a s ce n t r a t e reaches 50 fps about 10 s e c o n d sa f t e r l i f t o f f a t about 2 7 2 f e e t i n a l t i t u d e . I n s e r t i o n into a9 x44 nm l u n a r o r b i t w i l l t a k e place a b o u t 1 6 6 nrn west of t h el a n d i n g s i t e .

Following LM i n s e r t i o n i n t o lunar o r b i t , t h e LM crew willcompute onboard th e majo r maneuvers f o r r endezvous with t h e CSMwhich i s a b o u t 2 6 7 nm a h e ad o f a n d 5 1 m i l e s above t h e LM a t t h Z sp o i n t . All maneuvers in t h e sequences w i l l be made w i t h t h e LMR C S thrusters. The p re mis s io n r endezvous sequence maneuvers ,time, and v e l o c i t i e s , whlch l i k e l y w i l l d i f f e r s l i g h t l y i n r e a lt ime , a r e as f o l l o w s :

C o n c e n t r i c sequence i n i t i a t e ( C S I ) : A t f i r s t LM a p o l u n ea f t e r i n s e r t i o n , 138:19 GET, 5 0 f p s p o s i gr a d e , following some20 mi n u t e s of LM r endezvous r a d a r t r a c k i n g and CSM sextant/VHFranging navigation. CSI will be t a r g e t e d t o p l a c e t h e LM i na n o r b i t 15 nrn below t h e CSM a t t h e t i m e of t h e later c o n s t a n td e l t a h e i g h t (CDH) maneuver (139:Oh).The CSI b u r n m ay a l s o i n i t i a t e c o r r e c t to n s for any o u t - o f -p l a n e d i s p e r s i o n s r e s u l t i n g from i n s e r t i o n az imu th errors. Ther e s u l t i n g EM o r b i t a f t e r C S I will be 4 5 ~ 4 3 . 5 nm and will h a v e acatchup r a t e t o t h e CSM of abou t 1 2 0 f e e t p e r second .

1 3 9 : 4 6 and a d d s 2 4 . 7 f p s a l o n g t h e l i n e o f slght toward t h eCSM when t h e e l e v a t i o n a ng le t o t h e CSM r e a c h e s 2 6 . 6 degrees.The LM o r b i t b e c o me s 61x44 nrn a n d t h e c a t c h u p rate t o t h e CSMdec rea s e s t o a c l o s i n g r a t e of 1 3 3 f p s .

Termina l p h a s e i n i t i a t i o n ( T P I ) : This maneuver occurs a t

M i dc o ur s e c o r r e c t i o n ma ne uv er s w i l l b e made if needed , f o l -lowed b y f o u r braking maneuvers . D ock i ng nomina l ly w i l l t a k ep l a c e a t 140:25 GET t o end t h e t h r e e and one-half hour rendez-vous sequence .The LM a s c e n t s t a g e w i l l be j e t t i s o n e d at143:04 G E T a n da CSM R C S 1 . 0 f p s maneuver w i l l p r o v i d e s e p a r a t i o n .

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Ascent Staae D e o r b i tP r f o r t o t r a n s f e r r i n g t o t h e command module, the LM crewwill s e t up t h e LIfl g u i d a n c e system t o maintain t h e a s c e n t s tagei n a n inertial a t t i t u d e , A t a b o u t 1 4 4 : 3 2 GET t h e LM R C S t h r u s -ters w i l l i g n i t e on ground command f o r 1 8 6 f p s retrograde burnt a r g e t e d f o r a s c en t s t age impact a t 145:OO a b o u t 35 miles fromt h e l a n d i n g s i t e . The b u r n will have a s m a l l o u t -o f -p l a n e n o r t hcomponent s o t h a t ' t h e ground t r a c k w i l l i n c l u d e t h e o r i g i n a ll a n d i n g site. The a s c e n t s t a g e w i l l impact a t a b o u t 5508 f p sa t an a n g l e of f o u r degrees r e l a t i v e to t h e l o c a l horizontal.The a s c e n t s t a g e d e o r b i t s e r v e s t o remove d e b r i s from l unap OP-bit. Imp a c t i n g an o b j e c t with a known veloci ty and mass nearthe l a n d i n g s i t e will p r o v i d e e x p e r i m e n t e r s with an e v e n t f o rc a l i b r a t i n g r ea d o u ts from t h e ALSEP se i smomete r left b e h i n d .A plane change maneuver a t 154:13 GET will p l a c e t h e CSMon a n orbital t r a c k passing directly o v e r t h e c r a t e r Descartesand Bavy Rille e i g h t r e v o l u t i o n s l a t e r f o r p h o t o g r a p h s fromo r b i t . The maneuver w i l l b e a 825 fps /SPS burn ou t of p l a n efar a plane change of 8.8 d e g r e e s , and w i l l r e s u l t i n an o r b f ti n c l i n a t i o n of 1 1 . 4 d e g r e e s .

T r a n s e a r t h Injection (TEI)The n om in al t r a n s e a r t h i n j e c t i o n b u r n w i l l be a t 167:29GET following 90 h o u r s i n lunar o r b i t . T E I w i l l t a k e p l a c e ont h e l u n a r farside, w i l l b e a 3 , 1 4 7 f p s p o s i gr a d e SPS b u r n o f

two minutes 1 5 seconds duration and will prod t lce an en t ryv e l o c i t y o f 3 6 , 1 2 9 f p s a f t e r a 72 h o u r s t r a n s e a r t h f l i g h t t i m e .T r a n s e a r t h Coas t

Three e n t r y c o r r i d o r - c o n t r o l transearth mi d c o u r s e c o r r e c -t i o n burns w i l l b e made If needed: MCC-5 a t TEI+l5 hours,MCC- 6 at entry i n t e r f a c e (EI) -22 hours and MCC-7 at EI - 3 hrs.E n t r y , Landing

Apol lo 1 3 w i l l e n c o u n t e r t h e E a r t h ' s atmosphere ( 4 0 0 , 0 0 0f e e t ) a t 240:50 GET a t a velocity of 36,129 fps and w i l l landa p p ro x i ma t e l y 1 , 2 5 0 nm downrange f rom t h e e n t r y - i n t e r f a c e p o i n tusing the spacecraft's l i f t i n g c h a r a c t e r i s t i c s t o r e a c h t h el a n d i n g p o i n t . Spl as hd ow n w i l l b e a t 241:04 a t 2 . 5 degreesS o u t h l a t i t u d e b y 1 5 7 . 5 degree s West longitude.

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Recovery OperationsLaunch abort l a n d i n g areas e x t e n d downrange 3 , 4 0 0 n a u t i c a l

miles from Kennedy Space C e n t e r , fanwise 5 0 nrn m i l e s above andbelow t h e l i m i t s of t h e v a r i a b l e launch azimuth ( 7 2 - 9 6 degrees)i n t h e Atlantic Ocean. On s t a t t o n i n the l aunch abort area willbe the d e s t r o y e r USS New.The l a n d i n g platform-helicopter (LPH) Iwo Jima, A p o l l o 1-3p r i m e r e c o v e r y ship, will be s t a t i o n e d n e ar t h e Pacific Oceanend-of-miss ion aiming p o i n t p r i o r e n t r y .Splashdown f o r a f u l l - d u r a t i o n lunar l a n d i n g m i s s i o nlaunched on time April 11 will be a t one d e g r e e 34 mi n u t e sSouth by 1 5 7 degrees 30 mi n u t e s West about 180 nautical m i l e sSouth of Christmas I s l a n d , at 24l:04 GET (3:17 p.m. EST) A p r i l21.I n a d d i t i o n t o the p r i m a r y r e c ov e r y v e s s e l l o c a t e d on t h emid-Pacific r e c o v e r y l i n e and the s u r f ace vessel i n t h e l auncha b o r t area, e i g h t HC-130 aircraft will be on standby at f i v estaging b a s e s a r o u n d t h e E a r t h : Guam; H a w a i i ; Azores ;Ascensfon 1sland;and Florida.Apollo 1 3 r e c o v e r y o p e r a t i o n s w i l l b e directed from theRecovery Operations Control Room i n the Mission Control Center,s u p p o r t e d by the Atlantic Recovery Control C e n t e r , Norfolk, V a . ,and t h e Pacific Recovery Control C en t e r , Kunia, Hawaii.After splashdown, t h e Apol lo 13 crew will don c l e a n cover-a l l s and filter masks passed t o them through t h e spacecrafth a t c h b y a recovery swimmer. The crew w i l l be carried b y heli-c o p te r t o the Iwo Jima where they w i l l e n t e r a Mobile Quaran-t i n e F a c i l i t y (MQF) about 90 m f n u t e s after l a n d i n g .

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APOLLO 13 ONBOARD TELEVISION

A p o l l o 13 w : l l c a r r y two c o l o r and one black-and-whi tet e l e v i s i o n cameras . One c o l o r camera w i l l b e used forcommand module c ab in i n t e r i o r s and out-the-window E a r t h /Moon t e l e c a s t : ; , and t h e other c o l o r camera w i l l be s towedi n t h e 3J1 clescenl; s t a g e from where i t w i l l view t h e a s t r o n a u tInitiate e p c s s to t h e lunar swf ' ace and later w i l l b e de-p loyed on il tz . ipod t o transmit a r ea l - t i me p i c t u r e of t h e twoperiods of l u n a r su r f a c e EVA. The black-and-whi te cameraw i l l be carried i n t h e LM c a b i n . I t w i l l o n l y b e used as abackup -GO t h e l u n a r s u r f ace c o l o r camera.T h e two c 0 1 m TV cameras are essentially identical,e x c e p t :?or addi t ! -onal thermal p r o t e c t i o n on t h e lunar s u r f a c e

camera. B i S l t by Westinghouse Electric C o r p . , AerospaceDivis ior i , !alt.imose, Md., t h e c o l o r cameras o u t p u t a s t a n d a r d5 2 5 - l i n ~ , 30 f ra r ie -per-second signal in color b y use o f ar o t a t i n t ; color wheel system.The ccrloi- TV cameras weigh 12 pounds and are f i t t e d w i t hzoom l e n se s for wideangle or c l o s e u p f i e l d s o f view. TheCM came;>a f.s ;.'it ';ed with a t h r e e - i n c h moni to r for framing andfo c u s i n g . The lunar s u r f a c e color camera has L O O f e e t of c a b l eavai l a b 11-eThe b:.ckup hlack-and-whi te l u n a r surface TV camera,' alsob u i l t by Westfnghouse, i s of' the same t y p e u s e d in t h e f i r s t

manned 2unt.r l a n d i n g in Apol lo 11. It weighs 7 . 25 pounds anddraws 6 . 5 w a t t s of 24-32 v o l t s DC power. Scan r a t e i s 10frames-per--ser:onri t 325 lines-per-frame . T h e camera b o d y i s1 0 . 6 i n c h e s long, 6 . 5 i n c h e s wide and 3 .4 i n c h e s d e e p , and isfitted t r i t h hayonet-mount wideangle and lunar day l e n s e s .Du;-inf; t h e two lunar s u r f ace EVA p e r i o d s , A p o l l o 1 3commander Love11 w i l l be r e c o g n i z a b l e b y red s t r i p e s a r o u n dthe elbows and knees of his pressure s u i t .The f o l l o w i n g i s a preliminary p l a n for TV transmissionsbased upon a 2213 p.m. E S T April 11 l aunch .

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D A YSaturdayS a t u r d a ySunday

MondayWednesday'lh ups dayThursday

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D mApr. 11Apr. I1Apr. 12Apr. 13Apr. 15A p r . 16Apr. 16Apr. 1 7A p r . 1 8Apr. 1 8Apr. 20

Recorded only** Tenta t ive

CST2:48 pm4:28 pm7:28 pm

11:13 pm1:03 pm1 : 2 3 am9 : 0 3 pm9:36 am

1 1 ~ 2 3 m1:13 prn6 : 5 8 p m

- G E T01:3503:1530:1558: 095 : 50108: 0

APOLLO 13 TV SCHEDULE

DURATION A C T I V I T Y /SUBJECT7 Min. E a r t h

1 Hr. 8 Min. T r a n s p o s i t i o n & Docking30 Min. Space raft I n t e r i o r(MCC-2 )3 0 Mln. I n t e r l o r & I V T t o LM15 Min. Fra Mauro Landing S l t e

3 Hrs. 52 Min. Lunar S ur f a c e (EVA-1 )127150 6 Hrs. 35 Min. Lunar Surface (EVA-2 )140: 3 12 Min. Dock in166: 10 40 H i n . Lunar S u r f a c e168 0 2 5 Min.22i: 5 15 Mln. E a r t h & S pa c e c r a f t

Lunar Surface ( p o s t m I)I n t e r i o r

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CSMCSMLMLMCS MCS MCSMCSEl

S XK S C **GD SGDSGD SMADGDS/HSKGDSMADMAD*M ADGDS


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-4 a-APOLLO 13 SCIENCE

Lunar Orbital Photographyconduc ted from the C S M during t h e A p o l l o 1 3 mi s s i o n . D u r i n gt h e translunar phase of the miss ion , photography w!Xl betaken o f t h e E a r t h a s w e l l as v a r i o u s o p e r a t i o n a l photography.i n c l u d i n g c a n d i d a t e landing s i t e s C e n s o r i n u s , Descartes andDavy Rille and t h e ApolEo 11 and 1 2 1andir.g s i t e s w i l l bephotographed w i t h t h e L u n a r Topographic Cancra.five astronomical phenomena w i l l b e p h o t o g r a p h e d :

Science experiments and p h o t o g r a p h i c tasks will be

During lunar o r b i t , v a r i o us lunar s u r f a c e f e a t u r e sI n a d d i t i o n ,

Photographs w i l l be t a k e n o f the solar corona usingt h e Moon as an o c c u l t i n g edge t o b l o c k out t h e s o l a rd i s k .P h o t o g r a p h y w i l l be t a k e n o f the z o d i a c a l light whichis b e l i e v e d t o o r i g i n a t e from r e f l e c t e d s u n l i g h t i nt h e astoroid b e l t . Earth o b s e r v a f i o n of zodiacallight i s i n c o n c l u s i v e d u e t o a tmospher i c d i s t o r t i o n .Photography w i l l b e t aken of luna r limb brightening,which a p p e a r s as b r i g h t r i m light above t he horizonfollowing lunar s u n s e t .Photographs w i l l be t a k e n o f t h e Comet J . C . B e n n e t t ,1969i which s h o u l d b e visible from lunar o r b i t d u r in gt h e Apollo 1 3 m i s s i o n .Photographs w i l l b e t a k e n of t h e region of Gegenschefnwhich i s a f a i n t l i g h t source c o v e r i n g a 20 ' field ofview a b o u t t h e Earth-Sun l i n e on t h e o p p o s f t e side o ft h e Earth from t h e Sun ( a n t i - s o l a r a x i s ) , One of t h et h e o r i e s f o r the Gegenschein source is t h e existenceo f t r a pp e d p a r t i c l e s o f mat te r a t t h e Moulton p o i n twhich produce b r i g h t n e s s due t o r e f l e c t e d sunlight.The Moulton point i s a t h e o r e t i c a l point l o c a t e d940 ,000 s t a t u t e miles from the E a r t h a l o n g t h e a n t i -solar axis a t which t h e sum o f a l l g r a v i t a t i o n a l forcesi s z e r o . From t h e v a n t a g e p o i n t of lunar orbit, t h eMoulton p o i n t r e g i o n may be photographed from a p p r o x i -m a t e l y 15' o f f t h e E a r t h / S u n l i n e .should show I f Gegenschein results f rom t h e Moultonp o i n t theory or from z o d i a c a l light o r a s i m i l a r source.

These p h o t o g r a p h s

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Photographic s t u d i e s w i l l b e made on Apollo 13 of t h ei c e p a r t i c l e flow fallowing a water dump and o f t h e gaseouscloud which surrounds a manned s p a c e c r a f t in a vacuum andr e s u l t s f rom l i q u i d dumps, o u t g a s s i n g , e t c .

I n a d d i t i o n t o the photographic s t u d i e s , an exper imen tw l l l b e conducted w i t h the CSM VHF communications l i n k .During t h i s exper imen t , t he VHF s i g n a l will b e r e f l e c t e d f r o mt h e lunar s u r f a c e and r e c e i v e d b y a 150-foot an t en n a on E a r t h .By analysis of t h e wavelength o f t h e received signal, c e r t a i nl una r s u b s u r f a c e c h a r a c t e r i s t i c s may be d i s c e r n i b l e such ast h e d e p th o f t h e lunar r e g o l i t h layer, This exper imen t Isc a l l e d VHF Blstatic Radar.Charged P a r t i c l e Lunar Environment Experiment (CPLEE)

T h e s c i e n t i f i c objective o f t h e Charged Particle L u n a rEnvironment Experiment is t o measure t h e p a r t i c l e e n e rg i es ofp r o t o n s and electrons that reach t h e l u n a r surface from t h eSun. Increased knowledge on the energy d l s t r i b u t l o n o f thesep a r t i c l e s will h e l p us unders t and how t h e y p e r t u r b t h e E a r t h -Moon system. A t some point e l e c t r o n s an d p r o to n s i n t h emagnetospher ic t a i l of t h e Earth a re accelerated and p lungei n t o t h e t e r r e s t r i a l atmosphere causing t h e spectaculara u r o r a s and the Van Allen radiation. When t h e Moon i s i ni n t e r p l a n e t a r y space t h e CPLEE measures pro ton and e l e c t r o n sfrom solar f l a r e s which results i n magnetic s torms In theE a r t h ' s atmosphere. S i m i l a r i n s t r u me n t s h av e been f lown onJ a v e l i n r o c k e t s a nd on satellites. The lunar surface, however,allows d a t a t o be g a t h e r e d over a long period o f time and f r o ma r e l a t i v e l y s t a b l e p l at fo r m i n s pa ce .To study these phenomena, the CPLEE measures t h e energyof p r o t o n s and e l e c t r o n s s i m u l t a n e o u s l y from 5 0 e l e c t r o nv o l t s t o 5 0 , 0 0 0 electron volts (5OKev).- The solar radiationphenomena measured are as f o l l o w s :a .b .

C.d ,

Solar wind e l e c t r o n s a n d protons 50ev-5Kev.Thermalized s o l a r wind protons and electrons50ev-1OKev.Magnetospheric t a i l p a r t i c l e s 50ev to 50Kev.Low energy solar cosmic rays 40ev-50Kev.

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PHYSICAL A NALYZERELECTRONICS

CHARGED-PARTICLELUNAR ENVIRONMENT/ XPERIMENT SUBSYSTEM-more -


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-51-This exper iment Is d i s t i n c t f r o m t h e ALSEP Solar WindSp e c t ro me t e r (SWS) f lown on Apollo 1 2 which measuresd i r e c t i o n as w e l l as energy levels. The SWS measures e l e c -t r o n s from 1 0 . 5 ~o 1,400ev and pro tons f rom 75ev t o10,000ev.The d e t e c t o r package c o n t a i n s t w o spectrometers p r o v i d i n gd a t a on t h e d i r e c t i o n of the incoming f l u x .Each s p e c t ro me t e r has s i x p a r t i c l e d e t e c t o r s : f i v e C-shaped channeltron p h o t o n - m i l t i p l i e r s and one f u n n e l t r o n , ah e l i c a l shaped photon m u l t i p l i e r . P a r t i c l e s of a given cha rgeand d i f f e r e n t e n er g ie s on e n t e r i n g t h e s p ec t r om e t e r are s u b j e c tt o v a r y i n g voltages and d e f l e c t e d t ow ar d t h e f i v e c h a n n e l t r o n swhile particles of t h e o p p o s i t e charge are d e f l e c t e d towardt h e funneltron. Thus e l e c t r o n s and p r o t o n s a re me a s u re ds i mu l t a n e o u s l y i n s i x d i f f e r e n t energy l e v e l s . The v o l t a g e sa re changed over s i x s t e p s ; + 3 5 V, +350 v o l t s and t3500V. I n

this way e l e c t r o n s and p r o t o n s are-measured f rom SOev t o 7OKevi n a p e r i o d of l e s s than 20 seconds.The c h a n n e l t r o n i s a glass c a p i l l a r y tube h a v i n g an i n s f d ed i a m e t e r o f about one m i l l i m e t e r and a l e n g t h of 10 c e n t i m e t e r s .The h e l i c a l f u n n e l t r o n has an openlng of 8mm . When a v o l t a g ei s a p p l i e d between t h e ends of t h e t u b e , &n electric f i e l d i se s t a b l l s h e d down i t s l e n g t h . Charged p a r t i c l e s entering thet u b e a r e a m p l i f i e d b y a f a c t o r o f 108 .The spe c t r om ete rs have two ranges o f s e n s i t i v i t y and can4measure f l u x e s between 10 and l o l o p a r t i c l e s / c m * - s e c - s t ~ ~ ~ d i ~ ~The c h a r g e d p a r t i c l e lunar env i ronment exper iment ( C P L E E )a n d data analysis are the r e s p o n s i b i l i t y o f D r . Brian O'Brlen,U n i v e r s i t y o f S y d n e y ( A u s t r a l i a ) and Dr. David Reasoner , RiceU n i v e r s i t y , w i t h D r . O'Br ien assuming the role o f PrincipalI n v e s t i g a t o r .

Lunar Atmosphere Detec tor ( L A D )A l t h o u g h t h e Moon I s commonly d e s c r i b e d as a p l a n e t a r ybody w i t h no atmosphere, t h e e x i s t e n c e of 6ome atmosphere cannotbe doubted. Two s o u r c e s o f t h i s atmosphere are p r e d i c t e d :i n t e r n a l , i . e . , degassing f r o m t h e i n t e r i o r of the Moon e i t h e r

b y c o n s t a n t d i f f u s i o n through i t s s u r f a c e o r i n t e r m i t t e n trelease from a c t i v e v en ts ; e x t e r n a l i e., solar wi n d andv a p o r i z a t f o n d u r i n g m e t e o r i t e i m p a c t s , T e l e s c o p i c o b s e r v a t i o n sfrom p o l a r i z ed s c a t t e r e d light i n d i c a t e that t h e a t m o s p h e r i cp r e s s u r e c o u l d n o t exceed one m i l l i o n t h of' a torr ( a torr i sd e f i n e d as 1/760 of the s t a n d a r d a t m o s p h e r e ) .-more-


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LUNAR ATMOSPHERIC DETECTOR(COLD CATHODE ioN GAUGE INSTRUMENT)


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Measurements w i l l b e of t h e gre a t e s t significance ifi t t u r n s ou t through later o r b t t a l sensors that they a re o finternal o r f g i n , The Earth's atmosphere and oceans havebeen re leased f rom the Earth's f n t e r i o r b y degassing. Themost c e r t a i n s o u r c e , however, is t h e solar wind whose i o n i z e dparticles become n e u t r a l i z e d I n t h e lunar atmosphere andthen a re released as n e u t r a l gases. Neon i s the predominantgas e x p e c t e d . L i g h t e r gases such as hydrogen and hel ium escapeand heavier ones s t a t i s t i c a l l y should b e p r e s e n t i n smallquantities. Neutra l p a r t i c l e s are i o n i z e d i n t h e lunar atmos-p h e r e , further reducing the numbers p r e s e n t ; others will e s c a p eas t h e t e m p e r a t u r e r i ses (and c o n c e n t r a t e near the s u r f a c ewhen i t f a l l s ) ,

The LAD utilizes a cold cathode i o n i z a t i o n gauge t omeasure t h e density o f n e u t r a l particles a t t h e lunar s u r f a c eand t h e variations i n d e n s l t y association with lunar phaseo r solar activity. The i o n i z a t i o n gauge is basically a crossede lec t ro-magne t ic field device . E l e c t r o n s i n the gauge area c c e l e r a t e d b y t h e combined magne t ic and e l e c t r i c f l e l d s pro-ducing a colllslon are c o l l e c t e d by t h e c a t h o d e where t h e yform a flow of p o s i t i v e ions. The p o s i t i v e i o n s c u r r e n t i sfound t o b e p r o p o r t i o n a l t o t h e density of the gas moleculese n t e r i n g the gauge. I n addition, t h e gauge temperature i sread over the range of -90' to 1 2 5 O C w i t h + C accuracy.

From the density and t empera tu re data t h e pressure of theambient lunar atmosphere can then be c a l c u l a t e d . Chemicalcomposition of t h e atmosphere however i s not d i r e c t l y measuredbut the gauge has been c a l i b r a t e d for each gas it i s e x p e c t e dt o encounter on t h e lunar s u r f a c e a n d some es t ima tes can bemade o f t h e chemical composition. Any one of seven d i f f e r e n tdynamic ranges may b e s e l e c t e d p e r m i t t i n g d e t e c t i o n o f n e u t r a l

-12p a r t i c l e s from To r r (h ig h es t p r e s s u r e p r e d i c t e d ) t o 10T o m (maximum capability of gauge ) . F o r p r e s s u r e greater than10-loTorr a c c u r a c i e s of - 30% w j . 1 1 be o b t a i n e d ; for p r e s s u r e s+less t h e n 10-loTorr accuracies - 50% w i l l be o b t a i n e d .e x p e r l me n t , therefore, will reduce t h e p r e s e n t u n c e r t a i n t y froma magnitude to a f a c t o r .

+The

The Lunar Atmosphere D e t e c t o r ( L A D ) and data are t h er e s p o n s i b i l i t y of F r a n c i s Johnson , U n i v e r s i t y o f Texas (Dal las)and Dal las Evans, Manned S p a c e c r a f t C e n t e r , with Dr. Johnsonserving as P r i n c i p a l I n v e s t i g a t o r .-more-


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-54-Lunar Heat Flow Experiment (HFE)

The s c i e n t i f i c o b j e c t i v e of th e Heat Flow experimentis t o measure t h e s t eady-s t a t e h e a t f low from t h e lunarinterior. Two p r e d i c t e d sources of heat are: 1) o r i g i n a lheat at t h e time o f t h e Moon's formation and 2 ) r a d i o a c t i v i t y .Scientists believe that heat cou ld have been generated by th ei n f a l l i n g o f material and i t s subsequent compaction as t h eMoon was formed. Moreover, varying amounts of t h e radioactiveelements uranium, thorium and potassium were found p r e s e n tin t h e A p o l l o 11 and 1 2 l u n a r samples which If p r e s e n t atdepth, would s u p p l y significant amounts of heat. No s l m p l eway has been dev i s ed f o r relating the c o n t r l b u t i o n of each ofthese sources to the present r a t e of heat loss. In additionto t empe ra t u re , the experiment is capable of measuring t h ethermal conductivity of the l u n a r rock material.The combined measurement of t empera ture and thermalconductivity g i v es the n e t h e a t f l u x f r o m t h e lunar I n t e r i o rthrough the lunar su r face . S i m i l a r measurements on Earthhave c o n t r i b u t e d basic information t o o u r understanding ofvolcanoes, earthquakes and mountain b u i l d i n g processes. I ncon3unction w i t h t h e seismic and magnetic data obtained onother lunar experiments t h e values derived from the h e a t flowmeasurements will h e l p s c i e n t i s t s t o b u i l d more exac t modelsof the Moon and t h e r e b y give us a b e t t e r unders tand ing o f itsorigin and h i s t o r y .The Beat Flow experiment consists o f instrument p r o b e s ,e l e c t r o n i c s and emplacement t o o l and the lunar su r f a c e drill.Each o f two probes is connected by a cable to an e l e c t r o n i c sbox which r e s t s on t h e lunar s u r f a c e . !?&e e l e c t r o n f c s , whichprovide control, monitoring and data p r o c e s s i n g for t h eexperiment, i s connected t o t h e ALSEP c e n t r a l s t a t i o n .Each probe consists o f two identical 20-inch (50 em) longs e c t i o n s e a c h of which c o n t a i n s a ''gradient" sensorb r i d g e , a ''ring'' sensor b r i d g e and t w o heaters. Each b r i d g ec o n s i s t s of four platinum r e s i s t o r s mounted in a thin-walledf i b e r g l a s s c y l h d r i c a l s h e l l , Adjacent areas o f the b r i d g e

are located i n sensors at opposite ends of the 20- inch f i b e r -glass probe s h e a t h . G r a d i e n t b r i d g e s consequently measure thetemperature difference between two s e n s o r locations.

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APOLLb LUNAR SURFACE DRILL-more -


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PROBE PACKAGE ELECTRONICS PROBE CARRY1NG PACKAGECABLE TRAY PACKAGE (CONTAINS 2 PR05ES BEMPLACEMENT TOOt)\ I

THERMAL i CABLE BRACKETMAS K REFLECTOR REMOVED DURINGDEPLOYMEN

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I n thermal conduct iv i ty measurements a t very low valuesa heater su r r o u n d i n g the g r a d i e n t s e n s o r i s e n e r g i z e d w i t h0 . 0 0 2 watt? and t h e g r a d i e n t s e n s o r v a l u e s monitored. Therise i n t empera tu re of t h e g r a d i e n t s e n s o r i s a f u n c t i o n o ft h e t h e r ma l co n d u c t i v i t y of t h e su r r o u n d i n g lunar m a t e r i a l .F o r higher range of v a l u es , t h e h e a t e r is energized a t 0 ,5watts o f hea t and moni tored by a r i n g s e ns o r. The rate oft empera tu re rise, moni tored by t h e s i n g se nso r i s a f u n c t i o nof t h e thermal c o n d u c t i v i t y o f t h e su r r o u n d i n g lunar mater ia l .The ring s en s o r , approx imate ly f ou r inch es f rom the h e a t e r , isa l s o a p l a t i n u m r e s i s t o r . A k o t a l of e i g h t thermal conduc-t i v i t y measur emen ts can be made. The t h e r m a l c o n d u c t i v i t ymode of t h e expe rime nt w i l l b e implemented about twenty d a y s( 5 0 0 h o u r s ) a f t e r , deployment . T h i s i s t o allow s u f f i c i e n tt i m e for the p e r t u r b i n g e f f e c t s . of drilling and emplacing t h eprobe i n t h e b o r eh o l e t o decay; i . e . , f o r the probe and c a s i n g st o come t o e q u i l i b r i u m w i t h t h e lunar su b su r f ace .

A 30-fOOt ( 1 0 meter) c a b l e connec t s each p ro b e t o t h ee l e c t r o n i c s b o x . I n t h e u p p e r six feet of the b o r e h o l e t h ec a b l e c o n t a i n s f o u r evenly spaced thermocouples : a t t h e topo f t h e p r o b e ; a t 2 6 " ( 6 5 em), 45' ' (115 ern), and 66" (165 c m ) .The thermocopules w i l l measure temperature transients p r o -pagating downward from t h e l u n a r surface.t empera tu re for each t he rmocoup l e i s l o c a t e d i n t h e e l e c t r o n i c sbox . I n f a c t , t h e f e a s l b i l i t y of making a h e a t flow measure-ment depends t o a l a r g e d e g r e e on t h e l o w thermal c o n d u c t i v i t yo f t h e lunar s u r f a c e l a y e r , the r e g o l i t h . Measurement o f l u n a rs u r f a c e t e mp e ra t ur e v a r i a t i o n s b y E a r t h - b a s e d telescopes aswell as t he Surveyor and Apol lo miss ions show a remarkablyr a p i d r a t e o f c o o l i n g . The wide f l u c t u a t i o n s i n t em pe s at ur eo f t h e lunar surface ( f rom -25OOF t o +Z50) are ex p ec t ed t oi n f l u e n c e o n l y t h e u pp er s i x f e e t a nd n o t t h e bottom 3 f e e tof t h e b o r eh o l e .

The r e f e r e n c e j u n c t i o n

The astronauts w i l l use t h e A p o l l o Lunar S u r f a c e D r i l l(ALSD) t o make a l i n e d boreho le i n t h e lunar s u r f a c e for t h eprobes. The drilling energy will be provided b y a b a t t e r y -powered rotary percusslve power head.of f i b e r g l a s s t u b u l a r s e c t i o n s r e i n f o r c e d with boron f i l a m e n t s( each a b o u t 20 Inches o r 5 0 cm long). A closed d r i l l bit,placed on t h e f i r s t drill r o d , i s capable of p e n e t r a t i n g th ev a r i e t y of rock including three feet o f v e s i c u l a r basalt( 4 0 p e r cent porosity). A s l u n a r s u r f a c e p e n e t r a t i o n pro -gresses, additional drill rod s e c t i o n s w i l l b e connec ted to thed r i l l s t r i n g . The d r i l l s t r i n g i s l e f t i n p l a c e t o s e r v eas a h o l e casing.

The d r i l l rod c o n s i s t s

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-5 8-An emplac ement to o l i s used b y t h e a s t r o n a u t t o i n s e r tth e p r o b e t o f u l l d e p t h . A lig nm en t s p r i n g s p o s i t i o n thep r o b e w i t h i n t h e c a s i n g a n d assure a w e l l - d e f i n e d r a d i a t i v et hermal co ,upl ing be tween t h e p r o b e a n d t h e b o re h o l e .R a d i a t i o n s h i e l d s o n the h o l e p re v e nt d i r e c t s u n l i g h t f romr e a c h i n g t h e b o t t o m o f t h e h o l e .T h e a s t r o n a u t w i l l d r i l l a t h i r d h o le n e a r t h e HFEand o b t a i n c o re s o f l u n a r mate r ia l for s u b s e q u e n t a n a l y s i s oft h e r m a l p r o p e r t i e s .Heat flow e x p e r i m e n t , d e s i g n and da ta analysis aye t h er e s p o n s i b i l i t y o f D r . Marcus L a n g s e t h o f the Lamont-DohertyGeolog ica l O b s e m a t o r y ; Dr. Sydney Clark, Jr., Yale U n i v e r s i t y ,and D r . M. G , Simmons, MIT; w i t h D r . L a n g s e t h a s s u m i n g t h er o l e o f P r i n c i p a l I n v e s t i g a t o r .

P a s s i v e S e i s m i c Exper im en t ( P S E )The ALSEP P a s s i v e S e i s m i c E x p e r i m e n t (PSE) will measures e i s m i c a c t i v i t y of t h e Moon a n d o b t a i n i n f o r m a t i o n on t h ep h y s i c a l p r o p e r t l e s of t h e luna r c r u s t a nd i n t e r i o r . ThePSE will d e t e c t surface t i l t produced b y ttdal d e f o r m a t i o n s ,moonquakes and m e t e o r i t e impacts.The p a s s i v e s e i s m o m e t e r d e s i g n a n d s u b s e q u e n t e x p e r i m e n ta n a l y s i s a r e t h e r e s p o n s i b i l i t y o f Dr.Gary Latham o f t h e Lamont-Doherty G e o l o g i c a l O b s e r v a t o r y ,A similar p a s s i v e seismic e x p e r i m e n t was d e p l o y e d as p a r t

of t h e A p o l l o 1 2 ALSEP s t a t i o n a t S u r v e y o r c r a t e r l a s tNovember and has t r a n s m i t t e d E a r t h w a r d lunar s u r f a c e seismica c t i v i t i e s s i n c e t h a t t i m e . The Apol l o 1 2 and 1 3 seismometersd i f f e r from t h e Seismometer left a t T r a n q u i l i t y Base i n July1 9 6 9 by the A p o l l o 11 crew i n that t h e y a r e c o n t i n u o u s l ypowered by a SNAP-27 r a d i o i s o t o p e e l e c t r i c g e n e r a t o r , w h i l et h e A p o l l o 11 seismometer was powered by s o l a r energy and c o u l do u t p u t d a t a on ly d u r i n g t h e l u n a r day a t i t s location.A f t e r Love11 and Haise a s c e n d from t h e l u n a r s u r f a c e andr e n d e z v o u s w i t h t h e command module i n lunar orbit, t h e lunarmodul e a scen t s t ag e will b e j e t t i s o n e d and l a t e r ground-commanded t o i mpac t on the lunar s u r f a c e a bo ut 4 2 s t a t u t e

m i l e s from t h e Apollo 13 l a n d i n g s i t e a t F r a Mauro. Impacto f a n o b j e c t of known mass a n d v e l o c i t y will a s s i s t i n c a l i -b r a t i n g the Apollo 1 3 s e i s m o m e t e r readouts as well as providingc o m p a r a t i v e r e a d i n g s b et we en t h e A p o l l o 1 2 and 13 s e i s m o m e t e r sf o r m i n g t h e f i r s t two stations of a lunar s u r f a c e s e i s m ic n e t -work.-more-

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. SENSORY A SSYW lTHlN THERMALMANGANIN RIBBONCABLES-THERMALBARRIER-

L N KALT A T 1ON* T c I A L I l nP

PAIR OFR l 6 B O NCABLES

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There are t h r e e major p h y s i c a l components of the P S E :* The s e n s o r assembly c a n s l s t s of t h r e e , long-periodseismometers with o r t h o g o n a l i y - o r i e n t e d , capaci-tance type se i smic sensors, measuring along tw o

h o r i z o n t a l axes and one v e r t i c a l a x i s . This ismomted on a g i m b a l p l a t f o r m assembly. There i sone s h o r t p e r i o d s e i s mo me t e r which has magnet-typesensors . It is l o c a t e d d i r e c t l y on t h e base o f t h esensor assembly .* The leveling s t o o l al lows manual leveling of t h e sen-sor assembly by the a s t r o n a u t to within + 5 O , andfinal l e v e l i n g t o within 3 arc seconds by controlmotors.* The t hermal shroud covers and h e l p s s t a b i l i z e thet e mp e ra t u re of t h e s e n s o r a s s e m b l y . Also, two radio-

i s o t o p e hea te r s will p r o t e c t t h e instrument fromthe extreme cold of t h e lunar n i g h t .Solar Wind Composi t ion Experiment (SWCE)

The scientific objective of. h e solar wind compositionexper iment i s t o determine t h e elemental and isotopic com-p o s i t i o n o f the noble gases i n the solar wind. (This i snot an ALSEP ex p e r i men t ) .The s o l a r wind compos i t ion detector exper iment des igna n d subsequent d a t a analysis are the r e s p o n s i b i l i t y ofJ. Geiss and P. E b e r ha r d t, U n i v e r s i t y ' o f Ber n (Switzerland)and P. Signer, Swiss Fed era l I n s t i t u t e of Technology, withP r o f e s s o r Geiss assuming th e responsibility of P r i n c i p a lInvestigator.As in A p o l l o 11 and 12 the SWC d e t e c t o r w i l l be deployedon the Moon and brought; back to Earth by t h e astronauts.The d e t e c t o r , however, w i l l b e exposed to the solar wind f l u xfor 20 hours i n s t e a d o f two hours as in Apol lo 11 and 18 hours42 minutes on Apol lo 1 2 .The s o l a r wind composition d e t e c t o r consists of an a l um i numf o i l f o u r square feet i n area and a b o u t 0 . 5 mils t h i c k r i m e dby Teflon for res is tance to t ea r dur ing deployment. A s t a f fand yard arrangement w f l l be used to deploy t h e f o i l and t om a i n t a i n t h e foil approximately perpendicular t o the solarwind f l u x . Solar wind particles w i l l penetrate I n t o thefoil w h i l e cosmic rays will pass r i g h t through. The s o l a r windp a r t i c l e s w i l l b e firmly t rapped a t a d e p t h of seve ra l hundredatomic l a y e r s . After exposure on the lunar surface, the f o i lis ree l ed and re tu rned t o E a r t h .

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Dust Detec torThe ALSEP D u s t D e t e c t o r is and e s i g n e d t o d e t e c t t h e p r e s e n c e o f

impinge on t h e ALSEP o r accumulatelife.eng ineer ing measurementd u s t o r d e b r l s t h a t mayd u r i n g i t s o p era t i n g

The measurement appara tus c o n s f s t s of three c a l i b r a t e ds o l a r c e l l s , one pointing i n e a s t , west and vertical t o facet h e e l i p t i c p a t h of t h e Sun. The d e t e c t o r i s located on thec e n t r a l s t a t i o n .Dust accumula t ion on t h e s u r f a c e of the three s o l a r cellswill reduce t h e s o l a r Illumination d e t e c t e d b y t h e c e l l s .The t empera tu re o f each c e l l will be measured and comparedw i t h predicted v a l u e s .

PUSS DETECTOR'

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Field Geology InvestigationsThe scientific objectives Of the A p o l l o Field GeologyInvestigations are to determine the composition of the Moonand the processes which shape i t s surfaces. This informationwill help to determine the history of t h e Moon and i t s r e la -tionship t o t h e Earth. A p o l l o I1 visited the Sea of Tran-q u i l i t y (Mare Tranquillitatis) and A p o l l o 12 studied the Oceanof Storms (Oceanus Procellarum). The r e s u l t s of these studiesshould h e l p e s t a b l i s h the nature of Mare-type a reas . Apollo 13will investigate a hilly upland area.Geology investigation of the Moon actually began w i t h thetelescope. Systematic geology mapping began 10 years ago witha team of scientists at the U.S. Geological Survey. Ranger,Surveyor, and especially L u n a r Orblter d a t a enormously i n c r e a s e dthe detail and accuracy of these studies. The A p o l l o 11 and 12investigations represent another enormous advancement in pro -

viding new evidence on the Moon% great age, its curious cherni-stry, the surprisingly high density of t h e lunar surfacematerialOn Apollo 13, almost the entire second EVA wfll be devotedt o the F i e l d G e o l o g y Investigations and the collection of docu-menta l samples. The sample locations will be c a r e f u l l y photo-graphed before and a f t e r sampling. The astronauts will care-fully describe t h e setting from which the sample is collected,In addition to specific tasks, the a s t r o n a u t s w i l l be free topho tog raph and sample phenomena whlch they judge to be unusual,significant, and interesting. The astronauts are provided w i t ha package of detailed p h o t o maps which t h e y w i l l u s e f o r plan-

ning traverses. Photographs will be taken from the LM window.Each feature or family of features will be described, relatingt o features on the photo maps. Areas and features where photo-g r a p h s shou ld be t aken and representative samples collected willbe marked on the maps. The crew and their ground support per-sonnel will consider real-time deviation from the nominal p l a nbased upon an on-the-spot analysis of the actual situation. Atrench will be dug.far soil mechanics investigations.The Earth-based geologists w i l l be available to a d v i s e theastronauts in real-time and will work with t h e d a t a returned,t h e photos, the samples of r o c k and the astronauts' observationsto reconstruct here on Earth the astronauts traverse on t h e Moon.Each astronaut w i l l c a r r y a Lunar Surface Camera ( a modi-fied 7 0 mm electric Hasselblad). The camera has a 60 rnm lensand a Reseau plate. Lens apertures range from 5/56 to f/45.I t s f o c u s r a n g e is from three feet to infinity, A removablepolarizing fllter is a t t a c h e d to t h e lens of one of' the camerasand can be rotated in 45-degree increments for light polarizingstudies.

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A gnomon, used f o r metric control of near field (lessthan 10 feet) stereoscopic p h o t o g r a p h y , will provide angularo r i e n t a t i o n relative to the local vertical. Information ont h e distances to o b j e c t s and on the p i t c h , roll, and azimuthof t h e camera's o p t i c axis are t h e r e b y included in each p h o to -graph. The gnomon is a weighted tube suspended vertically ona tripod supported g i mb a l . The t u b e e x t e n d s one foot abovethe g i m b a l and is painted w 1 t . h a gray scale in b a n d s one centi-meter wide. Photogrammetric techniques will be used t o p r o -duce three-dimensional models and maps of the lunar s u r f a c efrom the angular and distance relationship between specifico b j e c t s r e c o r d e d on the film.

The 16 mm Data Acquisition Camera w i l l . p r o v i d e timeszse-quence coverage from within the LM. It can b e o p e ra t e d ins e v e r a l automatic modes , r ang i ng f r o m one frame/second to 24frames/second. Shutter s p e e d s , which are independent of t h eframe rates, range from 1/1000 second t o 1/60 second. T i m eexposures a r e also p o s s i b l e . While a variety of lenses isp r o v i d e d , the 18 mrn lens will be used to record mos t of thegeological activities in the one frame/second mode. A similarbattery powered 16 mm camera will b e carried in EVA.The Lunar Surface Close-up Camera will b e used t o obtainvery high resolution close-up sterecscopic p h o t o g r a p h s of thel u n a r surface to provide fine scale information on lunar soiland r o c k textures. Up to 100 stereo p a i r s can be exposed ont h e pre3.oaded roll of 35 mm c o l o r f i l m . The handle g r i p en-ables t h e a s t r o n a u t to operate the camera from a standing posi-tion. The f i l m drive a n d electronic f l a s h a r e b a t t e r y - o p e r a t e d .

The camera phctographs a 3"x3" a r e a of the lunar surface.Geological sampling equipment includes t o n g s , scoop, ham-mer, and c o r e t u b e s . A 24-inch extension handle is p r o v i d e dfor s e v e r a l of the t o o l s to aid t h e astronaut in using themwithout kneeling.Sample return containers (SRC) have b e e n p r o v i d e d for re-turn of up to 40 pounds e a c h of lunar material for E a r t h - b a s e danalysis. The SRC's are identical to the ones used on theApollo 13 and 12 missions. They are machined from aluminumforgings and a r e designed to maintain an internal vacuum d u r i n gthe outbound and return flights. The SRC's w i l l . be f i l l e d with

representative samples of lunar s u r f a c e material, c o l l e c t e d andseparately bagged by the astronauts on their traverse and docu-mented by v e r b a l descriptions and p h o t o g r a p h y . Subsurfacesamples will b e o b t a i n e d by using drive tubes 16 inches longand one inch in diameter. A few grams of material will bepreserved ur,der l u n a r vacuum conditions in a special environ-me n t a l sample container.-more-


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This container wfll be opened for analysis under vacuumconditions e q u i v a l e n t to that a t t h e luna r surface, Specialcontainers a r e provlded for a magnetic sample and a gas a n a l y s i ssample,SNAP-27

SNAP-27 is one of a series of radioisotope thermoelectricge ne r a to r s , or atomic batterlcc, developed by the U.S. AtomicEnergy Commission under I t s SNAP program. The SNAP (Systemsf o r NucleaP Auxiliary Power) Program is directed at developmentof generators and reactors f o r use in space, on land, and inthe sea .SNAP-27 was first used in the Apollo 12 mission t o p r o v i d eelectricity far the first ApolLo Lunar S u r f a c e Experiments

Package (ALSEP). A duplica'te of the Apollo 12 SNAP-27 willpower the Apollo 13 ALSEP,The b as l c SNAP-27 unit is designed to produce at least 63electrical watts of power. It is a cylindrical generatorf u e l e d with the radioisotope plutonium 238 , It is about 1 8Inches h i g h and 16 inches in diameter, including the heat r ad ia -ting f i n s . The generator, making maximum use of the lightweightmaterial beryllium, weighs about 28 pounds unfueled.The f u e l capsule, made of a superalloy material, is 16.5inches long and 2.5 inches i n diameter. It weighs about 15.5pounds, of which 8.36 pounds represent f u e l . The plutonium238 fuel is f u l l y oxidized and is chemically and b i o l o g i c a l l yinertThe rugged f u e l c a p s u l e is contained w i t h i n a graphitef u e l cask f r o m launch through l una r landing. The cask is de-signed to provide reentry heating protection and added contain-ment for the fuel capsule In the u n l i k e l y event of an abortedmission. The cyliqdrical cask with hemispherical ends Includesa pr imary graphite heat s h i e l d , a secondary beryllium thermals h i e l d , and a f u e l capsule support structure made of t i t a n i u mand Incone l materials, The cask is 23 inches long and eightinches in diameter and weighs about 24.5 pounds. Wlth the fuelc a p s u l e i n s t a l l e a , it weighs about 40 pounds. It is mounted onthe l u n a r module descent stage by a titanium support structure.Once the lunar module I s on the Moon, the lunar modulep i l u t w i l l remove the f u e l capsule from the cask and i n s e r t I ti n t o the SNAP-27 genera tor which w i l l have been p l a c e d on t h elunar surface near the module.

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The spontaneous radioactive decay of the plutonium 238within the f u e l capsule generates heat in the generator.An assembly of 442 lead telluride thermoelectric elements con-verts this heat -- 1480 thermal w a t t s -- directly into e l e c -trical energy -- a t least 63 watts. There are no moving parts.plutonium 238 is an excellent i s o t o p e for use in spacenuclear gene ra to r s . A t the end of almost 9 0 years, plutonium238 will s t f l l supply ha l f of it5 arlginal heat.process, plutonfum 238 emits mainly the nuclei of helium (alpharadiation), a v e ry m i l d t y p e of radiation with a short emissionrange.

In the decay

Before the use of the SNAP-27 system in the Apol lowas authorized, a thorough review was conducted to assure thehealth and safety of personnel involved in the mission and thegeneral public. Extensive safety analyses and tests were con-ducted which demonstrated that the fuel would be s a f e l y con-tained under almost all credible accident conditions.

program

Contractors f o r SNAP-27General Electric Co., Missile and Space Division, Phila-delphia, Pa., designed, developed, arid fabricated the SNAP-27generator f o r the ALSEP.The 3M Co. , St, P a u l , Minn,, fabricated the thermoelectricelements and assembled the S N A P - 2 7 generator.S o l a r Division of International Harvester, San Diego,C a l i f . , fabricated the generator's berylliurr. structure,Hitco, Gardena, Calif., fabricated the graphite structurefor the SNAP-27 Graphite LM Fuel Cask.Sandia Corp,, a subsidiary of Western Electric, o p e r a t o rof AEC's Sandia Laboratory, Albuquerque, N . M . , provided tech-n i c a l direction for the SNAP-27 p r o g r a m ,Savannah River Laboratory, Aiken, S . C . , opera ted by t h eD u P o n t Co. f o r the A E C , prepared the raw plutonium fuel,

. Mound Laboratory, Miamisburg, Ohio, operated by MonsantoResearch C o r p , , f o r the AEC, fabricated the raw f u e l into thefinal f u e l form and encapsulated the fuel.

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PHOTOGRAPHIC EQUIPPENTS t l l l and motion pictures w i l l be made of mostspacecraft maneuvers and crew lunar surface activities,and mapping pho tos from o r b i t a l a l t i t u d e t o aid In plan-ning future l anding missions. During lunar surface a c t i v i t i e s ,emphasis w i l l be on photographic documentation of lunars u r f a c e f e a t u r e s and lunar material sample c o l l e c t i o n .Camera equipment stowed in t h e Apol lo 13 commandmodule c o n s f s t s o f two 70mm Hasselblad e l e c t r i c cameras,a 16~11ll otion picture camera, and the H yc on l u n a r t opograph i ccamera (LTC).The LTC, to be flown on Apollos 1 3 , 24 and 15, isstowed beneath the commander's couch. In use, the cameramounts i n - t h e crew a c c e s s h a t c h window.The LTC w i t h 18-fnch f o c a l l e n g t h f/4.0 l e n s providesresolution of obJec ts as small as 15-25 feet from a 60-nma l t i t u d e and as small as 3 to 5 feet from the 8-nq1,pericynthion.Film format ?is 4.5-inch square frames on 100 foot long F O ~ ~ B ,with a frame rate var i ab l e from 4 t o 75 frames a mlnute.Shutter speeds are 1 / 5 0 , 1/100, and 1/200 second. Spacecraftforwalrd motion during exposures is compensated for by a servo-controlled rocking m o u n t . The f i l m is held flat in t h e focalplane by a vacuum platen connected t o t h e a ux i l i a ry dump valve.The camera weighs 6 5 pounds without film, is 28 inchesl ong , 10.5 i n c h e s wide, and 12 . 2 5 i n c h e s h i g h . It is a mod-i f i c a t i o n of an a e r i a l reconnaissance camera.F u t u r e l u n a r l a n d i n g sites and targets of s c i e n t i f i ci n t e r e s t will b e photographed with the l u n a r topographiccamera in overlapping sequence of single frame modes. Acandidate landing site northwest af the c r a t e r Censorinuswill be photographed from the 8-mile pericynthion d u r i n g theperiod between descent o r b i t I n se r tLon and CSM/LM separa t lon .Additional topographic photos of the Censorinus s i t e and

sites n e a r Davy *Rille and Descartes w i l l be made l a t e r in themPssion from the 60-nm c i r c u l a r orbit. The camera again willb e unstowed and mounted f o r 2 0 minutes of photography of t h el u n a r disc at 5 minute intervals s t a r t i n g at 2 h o u r s a f t e rtransearth i n j e c t i o n ,

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-69-Camesas stowed in t h e lunar module arc t w o 70mmHasselblad da ta cameras f i t t e d wlth 60mm Zc1ss Metr3.c lenses,a 16mm motion picture camera f i t t e d w i t h a lOmm l e n s , and a.Kodak closeup stcrea camera far h i q h r eso l i l tSon p h o t o s on t f i eh n a r s u r f a c e . The LM Hasselblads have crew chest

Date post:	09-Apr-2018
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