apollo 14 mission report

8/8/2019 Apollo 14 Mission Report

http://slidepdf.com/reader/full/apollo-14-mission-report 1/272

- 1

I

....................................................................................................................................................................................................................................';@If- ..:*... .e... ..................................................................................................................................... *.*.'.'

.......................

...........................................................................................................................................................................................................................................................................................................................................................................................................................................................................................................................................................................................................................................................................................................................................

.......................

.......................................................................................( N B A-T M-(NASA)

N AT I O N A L AERO

X - 7 4 2 4 0 ) APOLLO

N A U T I C S A N D SPACE

MSC-0411

A D M I N I S T R AT I

APOLLO 14 MISSION REPORT

1 4 HISSION REPORT N76-7 80 6

Unclas00/98 01216

\

D I S T R I B U T I O N AN D R E F E R E N C I N G

l h l r popor i s not ruito blo for gonorol distribution or roforoncing. It may bo roforonconly in othor working corrospondonco and docurnonts by participating orgonixotions.

M A N N E D S PA C E C R AF T C E N TH0 STON TEXA S

RtPRODUCEDB Y MAY 1971NATIONAL TECHNICA LINFORMATION SERVICE

U S D E PA R l M E W lOf COMMERCESPRINCfIELD.VA ZlSl



MS C-0 4112

APOLLO 1 4 MISSION mPORT

PREPARED BY

Mission Evaluat ion Team

APPROVED BY

.W T * -

A

James A. McDivittColonel , USAF

M Apollo Spacecraft Program

NATIONAL AERONAUTICS AND SPACE ADMINISTRATION

MANNEDSPACECRAFT CENTER

HOUSTON, TEXAS

A p r i l 1 9 7 1



Apollo 14 ift-off.



ii i

TABLE OF CONTENTS

S e ct on P a g e

1 . 0 MISSION SUMMARY . . . . . . . . . . . . . . . . . . . . . 1-1

2.0 INTRODUCTION . . . . . . . . . . . . . . . . . . . . . . 2-1

3.0 LUNAR SURFACE EXPERIMENTS . . . . . . . . . . . . . . . . 3-1

3.1 APOLLO LUNAR SURFACE EXPERIMENTS PACKAGE. . . . . 3-5

3.2 LASER RANGING RETRO-REFLECTOR . . . . . . . . . . 3-12

3.3 LUNAR PORTABLE MAGNETOMETER EXPERIMENT. . . . . . 3-12

3.4 S O U R W I N D COMPOSITION EXPERIMENT . . . . . . . .3.5 LUNAR GEOLOGY . . . . . . . . . . . . . . . . . .

. 3.6 LUNAR S O I L MECHANICS . . . . . . . . . . . . . . .3.7 MODULAR EQUIPMENT TRANSPORTER . . . . . . . . . .3.8 APOLLO L A N D I N GS I T E S . . . . . . . . . . . . . . .

4.0 LUNAR ORBITAL EXPERIMENTS . . . . . . . . . . . . . . . .4 . 1 S-BAND TRANSPONDER . . . . . . . . . . . . . . . .4. 2 BISTATIC RADAR . . . . . . . . . . . . . . . . . .4 .3 CECENSCHEIN/MOULTON POINT PHOTOGRAPHY

FROM LUNAR ORBIT . . . . . . . . . . . . . . . .4 .4 APOLLO W I N D O WMETEOROID EXPERIMENT . . . . . . . .4.5 DIM-LIGHT PHOTOGRAPHY . . . . . . . . . . . . . .4.6 COMMAND A N D SERVICE MODULE ORBITAL SCIENCE

PHOTOGWHY . . . . . . . . . . . . . . . . . . .4.7 PHOTOGRAPHS OF A CANDIDATE EXPLORATION SI T E . . .4.8 V I S I B I L I T Y AT H I G H SUN ANGLES . . . . . . . . . .4.9 TRANSEARTH LUNAR PHOTOGRAPHY . . . . . . . . . . .

5 . INFLICHT DEMONSTRATIONS. . . . . . . . . . . . . . . . .5 . 1 ELECTROPHORETIC SEPARATION . . . . . . . . . . . .

5.3 HEAT FLOW AND CONVECTION . . . . . . . . . . . . .5 . 4 COMPOSITE CASTING . . . . . . . . . . . . . . . .

5 .2 LIQUID TRANSFER . . . . . . . . . . . . . . . . .

3-14

3-14

3-15

3-163-18

4-1

4 -1

4 - 1

4-2

4-3

4-4

4-4

4-5

4-5

4-6

5-1

5-1

5-1

5-4

5-4



iv

Se t on Page

6 .0 T R A J E C T O RY . . . . . . . . . . . . . . . . . . . . . .6 . 1 L AU NC H AN D T R A N S L U N A R T R A J E C T O R I E S. . . . . . .6.2 L U N A R O R B I T . . . . . . . . . . . . . . . . . .6 . 3 T R A N S E A RT H A N D E N T RY T R A J E C T O R I E S. . . . . . .6 .4 S E RV I C E M O D UL E E N T RY. . . . . . . . . . . . . .

7 .0 COMMANDAND S E RV I C E M O DU LE P E R FO R M A N CE. . . . . . . .7 .1 S T R U C T U R A L A N D M E C H A N I C A L S Y S T E M S. . . . . . .7.2 E L E C T R I C A L PO W ER. . . . . . . . . . . . . . . .7 .3 C RY O G E N I C S T O R A G E. . . . . . . . . . . . . . .7. 4 C O M M U N I C AT I O N S E Q U I P M E N T. . . . . . . . . . . .7.5 I N S T R U M E N TAT I O N . . . . . . . . . . . . . . . .7. 6 G U I D A N C E . N AV I G AT I O N A N D C O N T RO L. . . . . . . .7.7 R E A C T I O IJ C O N T R O L S Y S T E M S. . . . . . . . . . . .7.8 S E RV I C E PR O P U L S I O N S Y S T E M. . . . . . . . . . .7. 9 E N V I R O N M E N TA L C O N T R O L A N D C R E W S TAT I O N. . . . .7.10 C O N S U M A B L E S . . . . . . . . . . . . . . . . . .

8. 0 L U N A R M O D U L E P E R F O R M A N C E. . . . . . . . . . . . . . .8 . 1 S T R U C T U R A L A N D M E C H A N IC A L S Y S T E M S. . . . . . .8. 2 E L E C T R I C A L P O W E R. . . . . . . . . . . . . . . .8 .3 C O M M U N I C AT I O N S E Q U I P M E N T. . . . . . . . . . . .

8.5 I N S T R U M E N TAT I O N . . . . . . . . . . . . . . . .8 .6 G U I D A N C E . N AV I G AT I O N A N D C O N T R O L. . . . . . . .8.7 D E S C E N T P R O P U L S I O N. . . . . . . . . . . . . . .8 . 8 A S C E N T P R O P U L S I O N. . . . . . . . . . . . . . .8.9 . E N V I R O N M E N TA L C O N T R O LAND CREW STATION . . . . .8.10 E X T RAV E HI CU L A R M O B I L I T Y U N I T. . . . . . . . . .8.11 C O N S U M A B L E S . . . . . . . . . . . . . . . . . .

9 .0 PILOT'S REPORT . . . . . . . . . . . . . . . . . . . .9 . 1 T R A I N I N G

. . . . . . . . . . . . . . . . . . . .9 . 2 LAUNCH . . . . . . . . . . . . . . . . . . . . .

8.4 RADAR . . . . . . . . . . . . . . . . . . . . .

6- 1

6- 1

6- 1

6-12

6-12

7-1

7-1

7-1

7-2

7-3

7-4

7-5

7-117-12

7-12

7-15

8- 1

8-1

8-4

8-4

8-5

8-5

8-6

8-13

8-14

8-15

8-16

8-17

9-1

9- 19-1



S e c t i o n

V

Page

9.3

9.4

9.5

9.6

9.7

9.8

9.9

9.10

9.11

E A RT H O R B I T . . . . . . . . . . . . . . . . . .T R A N S L U N A R I N J E C T I O N. . . . . . . . . . . . . .T R A . N S L U N A R F L I G H T. . . . . . . . . . . . . . .L UN AR O R B I T I N S E R T I O N. . . . . . . . . . . . .D E S CE N T O R B I T I N S E R T I O N. . . . . . . . . . . .LUNAR MODULE CHECKOUT. . . . . . . . . . . . .P O W E R E D D E S C E N T. . . . . . . . . . . . . . . .L U N A R S U R FA C E A C T I V I T Y. . . . . . . . . . . . .A S C E N T. R E N D E Z V O U S . A N D D O C K I N G. . . . . . . .

9.12 COMMANDAND SERVICE MODULE LUNAR ORBITA C T I V I T I E S . . . . . . . . . . . . . . . . . .

9.13 T M S E A H T H I N J E C T I O N. . . . . . . . .9.14 T R A N S E A RT H C O A S T. . . . . . . . . . . . . . . .9.15 E N T RY AND L A N D I N G . . . . . . . . . . . . . . .

10.0 B I O M E D I C A L E VA L U AT I O N. . . . . . . . . . . . . . . . .1 0 . 1 B I O M E D I C A L I N S T R UM E N TAT IO N A ND P H Y S I O L O G I C A L

D ATA . . . . . . . . . . . . . . . . . . . . .10.2 M E D I C A L O B S E RVAT I O N S. . . . . . . . . . . . . .10.3 P H Y S I C A L E X A M I N AT I O N S. . . . . . . . . . . . .10 .4 F L I G H T C REW HE ALTH S T A B I L I Z AT I O N. . . . . . . .1 0 . 5 Q U A R A N T I N E

. . . . . . . . . . . . . . . . . . .11 .0 M I S S I O N S U P P O RT P E R F O R M A N C E. . . . . . . . . . . . . .11.1 F L I G H T C O N T R O L. . . . . . . . . . . . . . . . .11.2 NETWORK . . . . . . . . . . . . . . . . . . . .11.3 R E C O V E RY O P E R AT I O N S. . . . . . . . . . . . . .

12.0 A S S E S S M E N TOF M I S S I O N O B J E C T IV E S. . . . . . . . . . .12.1 PA RT I A L LY C O M PL E TE D O B J E C T I V E S. . . . . . . . .12.2 I N F L I G H T D E M O N S T R AT I O N S. . . . . . . . . . . .12.3 A P P R O V E D O P E R AT I O N A LTESTS . . . . . . . . . . .

13.0 L A U N C HPHASE SUMMARY . . . . . . . . . . . . . . . . .13.1 WEATHER CONDITIONS . . . . . . . . . . . . . . .

9-2

9-2

9-2

9-49-1;

9-5

9-6

9-8

9-17

9-19

9-27

9-27

9-28

10-1

10-1

10-11

10-14

10-14

10-1511-1

11-1

11-2

11-3

12-1

12-3

12-4

12-4

13-1

13-1



vi

Sec t i on

13.2 AT M O SP H ER IC E L E C T R I C I T Y E X P E R I M E N T S

13.3 L A U N C H V E H I C L E S U M M A RY. . . . .1 4 . 0 ANOMALY SUMMARY. . . . . . . . . . . .

1 4 . 1 C OM MA ND A N D S E R V I C E M O D U LE. . .1 4 . 2 L U N A R M O D U L F :. . . . . . . . . .14.3 G OV ER NM EN T F U R N I S H E D E Q U I P M E N T.1 4 . 4 APOLLO LUNARS U R FA C E E X P E R I M E N T S

15 .0 C O N C L U S I O N S. . . . . . . . . . . .A F P E N D I X A- V E H I C L E : D E S C R I P T I O N - .

A . 1 C O M M A N D A N D S E RV I C E M O D U L E.A . 2 LUNAR MODULE. . . . . . . .A . 3 E X T R AV E HI C U LA R M O B I L I T Y U N I T

A . 4 E X P E R I M E N T E Q U I PM E N T. . .A . 5 MASS P R O P E R T I E S . . . . .A P P E N D I XB - S PAC E C R A FT H I S T O R I E S. . . .A P P E N D I X C- P O S T F L I G H T T E S T I N G. . . . .A P P E N D I X D- D AT A AVA I L A B I L I T Y . . . .A P P E N D I XE - M I S S I O N R E P O KT S U P P L E M E N T S

A P P E N D I XF - G L O S S A RY . . . . . .R E F E R E N C E S . . . . . . . . . . . . . . .

.

* .

L L

Page

13-1

13-6

1 4 - 1

14-1

14-2414-42

14-47

1 5 - 1

A - 1

A - 1

A -6

A - 1 0

A-10A - 1 3

B-1

c-1D - 1

E-1

F- 1

R - 1

I L . L



1-1

1.0 MISSION SUMMARY

The Apollo 1 4 mission, manned by Alan Shepard, J r . , Commander;S t u a r t A. Roosa , Command Module P i l o t ; and Edgar D. M i t c h e l l , L u n a rM.:dule P i l o t ; w a s laun ched from Kennedy Space Cente r, Fl o ri da , a t

4:03:02 p.m. e . s . t . (21:03:02G . m . t . )

on January 31, 1971. Because ofu n s a t i s f a c t o r y w e a t h e r c o n d i t i o n s a t t h e p l a n n e d t i m e o f l a u n c h , alaunch delay (about 40 minutes) w a s e xp er ie nc ed f o r t h e f i r s t t i m e i nt h e Ap oll o p ro gram . The a c t i v i t i e s d u r i n g e a r t h o r b i t a nd t r a n s l u n a ri n j e c t i o n were s i m i l a r t o t h o s e o f p r e v i o u s l u n a r l a n d i n g m i s s i o n s ; how-e v e r , d u r i n g t r a n s p o s i t i o n an d d o ck in g f ol l ow i n g t r a n s l u n a r i n j e c t i o n ,s i x a t t e m p t s were r e q u i r e d t o achieve docking because of mechanical d i f -f i c u l t i e s . Te l e v i s i o n w a s u se d d u r i n g t r a n s l u n a r c o a s t t o observe acrew insp ec t io n of t h e probe and drogue. A l l i n d i c a t i o n s w e r e t h a t t h esystem w a s func t ion in g normally. Excep t f o r a s p e c i a l c he ck of a s c e n tb a t t e r y 5 i n t h e l u n a r m od ule, t r a n s l u n a r c o a s t a f t e r d o ck i ng pr o ce e de da cc or di ng t o t h e f l i g h t p l a n . Two m i d c o u r s e c o r r e c t i o n s were performed,on e a t about 30-1/2 hours and th e ot he r a t about 77 hou rs . These cor-r e c t i o n s a ch ie ve d t h e t r a j e c t o r y r e q u i re d f o r t h e d e s i r e d l u n a r o r b i ti n s e r t i o n a l t i t u d e a n d t i m e parameters.

The combined spacecraft were i n s e r t e d i n t o l u n a r o r b i t a t approx i -mately 82 hour s , and t w o r e v o l u t i o n s l a t e r , t h e d e s ce n t o r b i t i n s e r t i o nmaneuver p laced the spacecra f t in a 58.8- by 9.1-mile o r b i t . The l u n a rmodule c rew en te re d th e veh ic l e a t approximately 101-1/4 hours t o pre-p a r e f o r t h e d e sc en t t o t h e l u n ar s u r f a c e.

The lunar module w a s undocked fro m t h e command module a t about103-3/4 hours.t o the computer as t h e r e s u l t of a malfunc t ion bu t a r o u t i n e w a s manu-a l l y l o ad e d i n t h e co mpu ter t h a t i n h i b i t e d t h e r e c o g n i t io n o f an a b o r td is c r et e . The powered des cen t maneuver w a s i n i t i a t e d a t about 108 hours .A rang ing s ca le p rob lem, which would have p reven ted a cq u i s i t i on o f rad ard a t a u n t i l l a t e i n t h e d es ce n t, w a s c o r r e ct e d by c y c l in g t h e c i r c u i tbre ake r of f and on. Landing i n the Fra Mauro h igh lands occur red a t108:15:09.3.o n d s s o u t h l a t i t u d e a n d 17 degrees 27 minutes 55 seconds w e s t l o n g i t u d e .

P r i o r t o p owered d e s c e n t , an abort command w a s d e l i v e r e d

The land ing coord ina tes were 3 degrees 40 minutes 24 sec-

The command and service module, a f t e r undocking and separa t ion , w a sp l a c e d i n a c i r c u l a r o r b i t h av in g an a l t i t u d e o f a p pr o xi m at el y 60 milest o p h ot og ra ph t h e p r o po s ed D e s c ar t es l a n d i n g s i t e , as w e l l as performlandmark t rack in g and o t he r t a sk s r equ i red f o r th e accompl ishment o flu n ar o r b i t experim ents and photography. Communications between t h e com-

mand and se r v i ce module and ea r th dur in g th i s p e r i od were i n t e r m i t t e n tbecause of a prob lem wi th th e h igh-ga in an tenna .



1-2

P r e pa r at i on s f o r t h e i n i t i a l p e r i o d of l u n a r e x p l o r a t i o n beganabout 2 h o ur s a f t e r l a n di n g.communications delayed cabin de pr es su ri za ti on about 50 minu tes. The Com-mander egressed a t about 113-3/4 hours and deployed th e modular equipmentstowage assembly as h e d e s ce nd ed t h e l a d d e r, p r o v i d i n g t r a n s m i s s i o n o fc o l o r t e l e v i s i o n .Subsequent ly, t h e S-band antenna w a s e r e c t e d and a c t i v a t e d , t h e Ap ol lolunar su r face exper iments package was deployed, and va ri ou s documentedlunar samples were t a k e n d u ri n g t h e e x t r a v e h i c u l a r p e r i o d which l a s t e dabout 4 3/4 hours . A modula r equ ipment t r anspor te r, used on th i s m i s -s i o n f o r t h e f i r s t t i m e , a s s i s t e d t h e crew i n c a r r y i n g e qu ip me nt andlunar samples .

A procedural problem w i t h t h e l u n a r m odule

The Lunar Module P i l o t e gre ss ed a few m i nu t es l a t e r .

P r e p a r a t i o n s f o r t h e s ec on d e x t r a v e h i c u l a r p e r i o d w ere be gun f o l -lowing a 6 1/2-hour r e s t p e r i o d .p e r i o d w a s t o t r a ve r s e t o t h e area of Cone Crater. Although t h e crewe x p e r i e n c e d d i f f i c u l t i e s i n n a v i g a t i n g , t h e y r e a c h e d a p o i n t w i t h i napproximately 50 feet of t h e r i m of t h e c r a t e r . Thus, t h e o b j e c t iv e sa s s o c i a t e d w i t h re ac hi ng t h e v i c i n i t y o f t h i s c r a t e r a nd o b t a in i n g t h ede si re d samples were achieved. Various documented rock and s o i l samplesw er e c o l l e c t e d on t h e r e t u r n t r a v e r s e f rom Cone C r a t e r , and, upon com-p l e t i n g t h e t r a v e r s e , t h e a n t en n a on t h e l un ar -e xp er im en t- pa ck ag e c e n t r a ls t a t i o n w a s rea l ign ed . The second ex t rav eh icu la r pe r iod l a s t e d about4-1/2 h ours fo r a t o t a l e x t r a v e h i c u l a r t i m e of approximately 9-1/4 hours .About 96 pounds of lunar samples were c o l l e c t e d d u r i n g t h e tw o e x t ra -v e h i c u l a r p e r i o d s .

T h e g o a l o f t h e s e c o n d e x t r a v e h i c u l a r

The a s c e nt s t a g e l i f t e d o f f a t abou t 141-3 /4 hours and t h e veh i c l ew a s i n s e r t e d i n t o a 51.7- by 6.5-mile o r b i t . A di rec t r endezvous w a sperformed and t h e command-module-active docking op er at io ns were normal .However, dur ing th e f i n a l b rak ing phase , t h e l un ar module abort guidances y s t e m f a i l e d a f t e r t h e s y s t e m w a s no longer r equ i red .t r a n s f e r t o th e command module, t h e asce n t s t ag e w a s j e t t i s o n e d a nd

guided t o impact approximately 36 m i l e s w e s t o f t h e A p o l l o 1 4 l a n d i n gs i t e .

Following crew

Tr a n s e a r t h i n j e c t i o n o c c u r r e d d u r i n g t h e 3 4 t h l u n a r r e v o l u t i o n a tabou t 148-1 /2 hours . Dur ing t r an se a r th coas t , one midcourse co r r ec t i onw a s made u s i n g t h e s e r v i c e module r e a c t i o n c o n t r o l s y st e m. I n a d d i t i o n ,a s p e c i a l o g g e n f l o w r a t e t e s t w a s performed and a n a v i g a t i o n e x e r c i s es i m u l a t i n g a r e t u r n t o e a r t h w i t ho u t g ro und c o n t r o l w a s conducted usingon ly t h e gu idance and nav iga t ion sys tem. In f l ig h t demons t ra tions o f fou rtypes o f p rocesses under ze ro -grav i ty cond i t ions were a l s o pe r fo rmed andt e l ev i s ed t o e a r th .

Entry w a s normal and t h e command module lan ded i n t h e P a c i f i c Ocean

The l a n d i n g c o o r d in a t e s were 27 degrees 0 minutes 45 sec -t 216:01:58.onds sou th l a t i tu d e and 172 degrees 39 minutes 30 seconds west l o n g i t u d e .



2.0 INTRODUCTION

The Apollo 1 4 mission w a s t h e 1 4t h i n a s e r i e s u s i n g A p o l l o f l i g h thardware and ach ieved th e th i r d lunar l and ing . The ob jec t ives o f th e

m i ss i on wer e t o i n v e s t i g a t e t h e l u n a r s u r f a c e near a p r e s e l e c t e d p o i n ti n t h e Fra Mauro formation, deploy and act iv at e an Apollo lun ar su rfa ceexperiments package, fur ther develop man's c a p a b i l i t y t o w ork i n t h elun ar environment, and obta in photographs of candid ate ex plo rat ion s i t e s .

A complete analysis o f a l l f l i g h t d a t a i s n o t p o s s i b l e w i t h in t h et ime a l lowed f o r p repa ra t ion o f t h i s r e p o r t .ments w i l l be publ ished f o r cer ta in Apol lo 1 4 systems analyses , as shownin appendix E. This appendix also l i s t s t h e c u r r e n t s t a t u s of a l l Apollomiss ion supp lements , e i t h e r pub l i shed o r i n p r e p ar a t io n .ments w i l l be publ ished as necessary.

I n t h i s r e p o rt , all a c t u a l times p r i o r t o e a r t h l and inga re

e l a p s e dtime f rom range zero, es tabl ished as t h e i n t e g r a l s eco nd b e fo r e l i f t - o f f .Range ze ro fo r th i s miss ion w a s 21:03:02 G . m . t . , January 31, 1971. Thec lock onboard the spacecra f t w a s changed a t 54:53:36 by adding 40 min-u tes and 2.90 seconds; however, t h e t i m e s g iv en i n t h i s r e p o r t do n o tr ef le ct t h i s c lock update . Had t h e clock update not been performed, in-d i c a t i o n s o f e l a p s e d t i m e i n t h e crew 's da t a f i l e would have been i n er-r o r by th e amount of t h e delay i n l i f t - o f f s i n c e t h e m id co ur se c o r r e c t i o n swere t a r g e t e d t o a c hi e ve t h e p r el a un c h -d e si r ed l u n a r o r b i t i n s e r t i o n t i m e .Greenwich mean t i m e i s used fo r all times a f t e r e a r t h l a n d i n g . All r e f -e r en c es t o m ile ag e d i s t a n c e a re i n n a u t i c a l miles.

Therefore , r epor t supp le -

Other supple-



3.0 LUNARSURFACE EXPERIMENTS

The exper iments discussed i n t h i s s e c t i o n c o n s i s t o f t h o s e a ss o ci -a t e d w i t h t h e A p ol lo l u n a r s u r f a c e e x p e ri m e nt s package ( a supra the rmali o n d e t e c t o r , a cold cathode gage, a pass ive se i smomete r, an a c t i v e s e i s -

mometer, an d a c ha rge d p a r t i c l e e nv ir on me nt d e t e c t o r ) , as w e l l as a l a s e rr a n g in g r e t r o - r e f l e c t o r e x p er i m en t , a lunar portable magnetometer exper i -ment, a s o l a r wind compos it ion exper iment , lun ar geo logy, and s o i l mechan-i c s . Desc r ip t ions o f t h e purposes and equipment of experiments c a r r i e df o r t h e f i r s t t im e on p r ev i o u s m i s si o ns are given i n t h e r e p or t s of t h o s em i s s i o n s , a nd t h e a p p l i c a b l e r e p o r t s are re fe renc ed where ap prop r ia t e .A b r i e f des c r i p t i on o f t he experiment equ ipment used f o r th e f i r s t t i m eon Apollo 14 i s g i v e n i n appendix A.

Lunar s ur fa ce s c i e n t i f i c a c t i v i t i e s were per fo rmed genera l ly asApproximately 5 1 / 2 hoursl an ne d w i t h in t h e a l l o t t e d t i m e p e r i o d s .

a f t e r. l a n d i n g , t h e c rew e g r e s s e d t h e l u n a r module f o r t h e f i r s t t r a v e r s eo f t h e lunar s u r f a c e .

w h i c h l a s t e d 4 hours 47 minutes 50 seconds , the c rew:

D uring t h e f i r s t e x t r a v e h i c u la r a c t i v i t y p e r i o d ,

a . Deployed t h e modular equipment stowage as sembly.

b. Deployed and o p er a te d t h e c o l o r t e l e v i s i o n camera as r e q u i r e dt o t e l e v i s e c rew a c t i v i t i e s i n t h e v i c i n i t y o f t h e l una r module.

c . Tr a n s f e r r e d a con tingency sample t o t h e lu na r module.

d. E r e c t e d t h e U n i t e d S t a t e s f l a g a nd t h e s o l a r w in d c o mp os i ti onf o i l .

e . Deployed and loaded th e modular equipment t r an sp or te r used t o

a i d t h e a s t r o n a u t s i n t r an spo r t i ng equ ipment and samples .

f . C o l l e c t e d surface samples inc lud i ng two "smal l - foo tba l l - s i ze"specimens weighing approximately 4.4 and 5.5 pounds.

g . Photographed act ivi t ies , panoramas and equipment .

h . Deployed th e Apol lo luna r s u r f ac e exper iments package fo r th ec o n t i n u i n g c o l l e c t i o n of lunar s c i e n t i f i c data v ia r a d i o l i n k .



3-2

Following a p la nn ed r e s t p e r i o d , t h e s ec on d e x t ra v e h i c u l a r a c t i v i t yp e r i o d b eg an w i t h p r e p a r a t i o n s f o r M e x te n de d g e o l o g i c a l t r a v e r s e . Thed u r a t io n o f t h e se co nd e x t r a v e h i c u l a r a c t i v i t y p e r i o d w a s 4 hours 34 min-u t e s 4 1 seconds , cover ing a t r av er s e of approximate ly 1 .6 mi le s , dur ingwhich t h e crew:

a . Obtained lunar portable magnetometer measurements a t t w o s i t e s

a lo ng t h e t r a v e r s e .

b . Co l lec ted documented, co re tu be , and t r en ch -s i t e samples .

c . Col lec ted a "la rge -foo tba l l - s iz e" specimen weighing approximately19 pounds.

d . Photographed the area covered, including panoramas and samples i t e s .

e . R e t ri e v ed t h e s o l a r w in d co mp os it io n f o i l .

f . A d j u s t e d t h e a n t e n n a o n t h e A p o l l o l u n a r s u r f a c e e x p e r i m e n t s

pa ck age c e n t r a l s t a t i o n .

The eva lua t ions d i scussed i n t h i s s e c t i on are based on the d a t ao b t a i n e d d u r i n g t h e f i r s t lunar day - argely on crew comments andreal- t ime i n f o rm a t i o n . C e r t a i n e qu ip me nt d i f f i c u l t i e s m en ti on ed i n t h i ss e c t i o n are d is cu ss ed i n g r e a t e r d e t a i l i n s e c t io n 1 4 . 4 .hens ive resul ts w i l l be summarized i n a separa te s c i e n c e r e p o r t t o bepubl i s hed when th e de ta i l ed ana lyses a re comple te ( append ix E ) .s i t e s a t which t h e v a ri o u s l u n a r s ur f a c e a c t i v i t i e s were conducted areshown i n t h e f i g u r e 3-1. The s p e c i f i c a c t i v i t i e s a t e ac h l o c a t i o n a r ei d e n t i f i e d i n t a b le 3-1.

More compre-

The



3-3



3-4

St a t o n

TABLE

A c t i v i t i e s

3-1.- LUNAR SURFACE

Apol lo lunar su r face exper iments

Laser r a n g i n g r e t r o - r e f l e c t o r s i t e

package deployment s i t e

Comprehensive sample s i t e

Small-footbal l -s ize rock s i t e

a c t i v i t y p e r io d

st' L i L L L

Sampling and photography

Apol lo lunar su r face exper imenta c t i v i t i e s a nd p h ot og r ap h y

Deployment of instrument andphotography



Sampling, photography and f i r s tdeployment o f lunar p o r t a b l emagnetometer


Sampling

Photography


Photography

Sampling, photography andsecond deployment of lu na r

. portable magnetometer



Sampling

Sampling


Sampling and photographySampling and photography


L I -

. .L .



3-5

3.1 M O L L 0 LUNAR SURFACE EXPERIMENTS PACKAGE

The Apollo lunar surface experiments package w a s deployed wi th thec e n t r a l s t a t i o n p o s i ti o n e d 600 f e e t w e s t- n o rt h w es t o f t h e l u n a r m odu le( f i g . 3-2).

o r s e t t i n g them up f o r t h e t r a v e r s e o t h e r th a n an i n i t i a l d i f f i c u l t y i nla tc hi ng t h e dome removal to ol i n t h e f u e l cask dome. The crew i n s t a l l e dt h e f u e l c a p s u le i n t h e r a d i oi s ot o p e t h e r m o e l e ct r i c g e n er a t o r and lock-on data were o b t a i n e d w i t h i n i t i a l an tenna a l ignment a t 116 hours 48 min-u t e s .

No d i f f i c u l t i e s were e x p e r ie n c e d i n o f f - l o a d i n g t h e p a l l e t s

NASA-5 -71-1618

Lunar moduleFirst geophone --I

detector experiment

Third geophone --.).gage experiment

Note: Distances n d to Scale

Figu re 3-2.- Arrangement of t h e A p o l l o lunar s u r f a c e e x p er i m en t s.

3.1.1 C e n t r al S t a t i o n

I n i t i a l c o nd it io ns of t h e c e n t r a l s t a t i o n ( r e f . 1) were normal .Power output of t h e r a d i o i s o t o p e t h e r m o e l e c t r i c g e n e r a t o r w a s 69.1 w a t t s ,and t h e c e n t r a l s t a t i o n t he rm a l p l a t e t e m p er a tu r e a v er a ge d 73.8' F. A



3-6

re se rv e power read ing of 43.5 w a t t s i n d i c a t e d t h a t t h e b a s i c p ower c on-sumption w a s normal for Apollo lunar s c i e n t i f i c e x p e r i m e n t p a c k a g e s t a r t -up. A s th e genera to r warmed up , th e power ou tpu t inc r ease d t o 72 .0 wat tsand has remained near ly constant a t t h a t l e v e l .

The t r a n s m i t t e r s i g n a l s t r e n g t h a t i n i t i a l a c q u i s i t i on w a s lowerthan expected, and about 4 dB lower than th a t o f t h e Apollo 12 exper iment

package.t i m e o f t h e w or st -c as e c o n d i t i o n o f t h e r e l a t i v e e arth -m oo n p o s i t i o n s .I n a d d i t i o n , l u n a r s u r f a c e ph ot og ra ph y shows t h a t t h e a n t e n na w a s n o tf u l l y s e a t e d i n t h e g im bal i n t e r f a c e s o c k e t ( r e s u l t i n g i n a misalignmentw i t h g i mb al s e t t i n g s ) a nd t h e g i m ba l p o i n t i n g t ow a rd t h e e a r t h w a s o f ft h e no mi na l p o i n t i n g a n g l e . S ub se qu en t m o n it o ri n g i n d i c a t e s t h a t t h es i g n a l s t r e n g t h o b t ai n ed from t h e A p o l l o 1 4 u n i t i s now equa l t o th a t o ft h e A p ol lo 1 2 u n i t and t h a t s i g n a l s t r e n g t h v a r i a t i o n c an b e p r e d i c t e dbased on th e re la t i v e ear th -moon po s i t io ns .

This w a s p a r t i a l l y t h e r e s u l t of a c q u i s i t i o n o c c u rr i ng a t t h e

The .Apo llo lunar s c i e n t i f i c e x pe ri me nt p ack ag e c e n t r a l s t a t i o n w a scommanded t o th e hig h- bi t-r ate mode a t 116 hours 56 m in ut es f o r t h eac t i ve s eism ic experiment/ thumper mode of o pe rat ion , which cont inuedu n t i l 117 hours 34 minutes . Using th e hig h- bi t - r a te mode, only t h ea c t i v e s e i s m i c e x pe ri m en t d a t a a nd l i m i t e d e n g i n e e r i n g d a t a c an be re -ce ived f rom th e cen t r a l s t a t i on . The o th er exper iments were tu r ned onfo l lowing th e ac t i ve se i sm ic exper iment/ thumper mode of ope ra t io n .

D urin g t h e dep loym en t o f t h e c e n t r a l s t a t i o n , t h e s u n s h i e l d e r e c t e dnorm ally. However, th e crew had t o lift one s ide on th ree occas ions be-cause it w a s sagging. L u n a - s u r f a c e p ho to gr ap hy i n d i c a t e s t h a t t h e sun-s h i e l d had b een bumped downward i n a counterclockwise di re ct io n. However,t h e s a g g i n g c o n d i ti o n h a s ha d no a d ve r se e f f e c t on t h e c e n t r a l s t a t i o nt h e r m a l c o n t r o l s y s t e m , and t h e c e n t r a l s t a t i o n h a s be en o p e r a t i n g w i t h inthermal l i m i t s .

The Apollo lunar s c i e n t i f i c e x p e r i m e n t p a c k a g e 12-hour t im er pu lse sd i d not occur a f t e r i n i t i a l c e n t r a l s t a t i o n t ur n- on . S ub se qu en t t e s t sv e r i f i e d t h a t t h e m e ch an ic al s e c t i o n of t h e t i m e r w a s not ope ra t i ng . Thet ime r f u n c t i o n s s t a r t e d t o o cc u r on F eb r ua ry 11 and the t imer prov ided12-hour pu l ses th i r t ee n times i n s u cc e ss io n be f or e f a i l i n g . Loss o f t h et im er has no adverse e f fe c t o f t he Apol lo luna r exper iment package s i nc eall fu nc ti on s ar e being accomplished by ground command. This problem i sd i s c u ss e d f u r t h e r ' i n s e c t i o n 1 4 . 4 . 4 .

The lunar d u s t d e t e c t o r of t h e c e n t r a l s t a t i o n i s showing normalou tpu ts f rom a l l t h r e e p h o t o e l e c t r i c c e l l s . No c ha ng es i n t h e o u t p u t sof t h e s e c e l l s w e r e o b s e r v e d d u r i n g o r a f t e r lunar module ascen t , ind i -

c a t i n g t h a t d u s t from t h e a s c e n t e n g in e e x h a us t d i d n o t s e t t l e on thec e n t r a l s t a t i o n .



3-7

3.1 .2 Passive Seismic Experiment

The pass ive se i smic exper iment ( r e f . 2 ) w a s deployed 10 f e e t n o r t ho f t h e c e n t ra l s t a t i o n ( f i g . 3-2) . No d i f f i c u l t y W:LS e x p e r i e n ce d i n de-p l o y i n g t h e e x p e ri m en t o t h e r t h a n t h e i n a b i l i t y t o make t h e r i b b o n c ab1.el i e f l a t on t h e s u r f a c e un d er t h e t h er m a l s h ro u d s k i r t . All elements

have operated as planned w i t h t h e f o l lo w i n g e x c e p ti o n s .

a. The long-period vertical component seismometer i s u n s t a b l e i nt h e normal mode (f la t - r esp on se mode).c u s s i o n o f t h i s a no ma ly.)feedback f i l t e r and oper a t ing i n t h e peaked- response mode. In t h i s mode,the s iesmometer has a r e s o n a n t p e r i o d o f 2 . 2 seconds i n s t e a d o f t h e n o r -m a l p e r i o d o f 1 5 s e co n d s . Witho ut t h e e x t en d e d f l a t r e s p o n s e , t h e low-f requency da ta i s more d i f f i c u l t t o e x t r a c t . However, u s e f u l d a t a a rebe ing ob ta ined o ver t h e p lanned spect rum by d a t a p r o c e s s in g t e c h n i q u e s .

( S e e s e c t i o n 14.4.6 f o r a d i s -T h e problem w a s e l im ina ted by removing th e

. b. The gimbal motor which le v e ls t h e Y-axis long-period seismometerhas no t responded t o commands on se ve ra l occas ions . In th es e ca se s , t he

res e rv e power s t a t us ind ica t es th a t no power i s b e in g s u p p l i e d t o t h emotor. The power co nt ro l c i r c u i t of th e motor i s c o ns id e re d t o b e t h emost li k e l y caus e of t h i s problem. Response t o commands has b e e n achievedi n a l l cases by re pe at i ng th e motor dr iv e command.f o r a more d e t a i l e d d i s cu s s i o n o f t h i s p r ob l em . )

( S ee s e c t i o n 14.4.5

3 . 1 . 3 A c t i v e Seismic Experiment

The a c t i ve s e i s mi c experiment (appendix A , s e c t i o n A.4.1) w a s de-p l oy e d d u r i n g t h e f i r s t e x t r a v e h i c u l a r p e r i o d w i t h t h e f i r s t geophoneapproximately 10 f e e t s o u t h w e s t o f t h e c e n t r a l s t a t i o n a n d t h e g e o p h o n earray e x t en d i ng i n a s o u th e r ly d i r e c t i o n ( f i g s . 3-2 an d 3-3). The Apollol una r sc ien t i f i c exper iment package w a s commanded t o t h e h ig h-b i t - r a temode fo r 28 minutes dur ing t h e act ive seismic experiment/ thumper mode o fop er at io n. Thumping op era tio ns began a t geophone 3 ( t h e f u r t h e s t fromt h e c e n t r a l s t a t i o n ) and p ro ce ed ed f o r 300 f e e t a t 1 5- fo ot i n t e r v a l s t o -ward geophone 1.

The a tt em pt s t o f i r e t h e i n i t i a t o r s r e s u l t e d i n 13 f i r e d and 5 m i s -f i r e d . T hr ee i n i t i a t o r s were d e l i b e r a t e l y n o t f i r e d . I n some i n s t a n c e s ,two a t t empts irere made t o f i r e a n i n i t i a t o r .f u r t h e r d i s c u s s i o n o f t h i s a no maly.)

( S e e s e c t i o n 14.4.1 f o r

A c a l i b r a t i o n p u l s e w a s s e n t p r i o r t o t h e l a s t thu mper f i r i n g v e r i -

f 'y in g t h a t a l l three geophones were o p e r a t i o n a l . The mortar package, wasdeployed 10 f e e t n o rt h -n o rt h we s t o f t h e c e n t r a l s t a t i o n an d aimed t o f i r efo ur grenades on command from e ar th t o d is t an ce s of 5 0 0 , 1000, 3000 an d



NASA-S-7 1-16 9

F i g u r e 3-3. - Apbl lo lunar su r face exper iment packagecomponents deployed on the. lunar surf ace.



3-9

5000 f e e t i n n r t h e r l y d i r e c t i o n . F i r i n o f t h e f o u r m o r t a r s h a s n o tbeen scheduled . Pos tmiss ion t e s t s and ana lyses a re be ing performed t oe s t a b l i s h t h e a p p r o p r i a t e t im e and p r o v i s io n s f o r c on d uc ti ng t h i s p a r to f t h e e x p e r i m e n t .

3.1.4 Suprathermal Ion Detector Experiment

The supra thermal ion de tec to r exper iment ( r e f . 2 ) was deployedsou thea s t o f t he Apol lo lunar su r fac e exper iments package ce n t ra l s t a -t io n ( f i g . 3 -2) . Noisy da ta were rece ived at tu rn-on ( sec t ion 1 4 . 4 . 2 )b u t t h e d a t a were s a t i s fa c t o r y a f t e r s e a l break and dus t co ver removal .The experiment i s re t u rn ing good sc ie n t i f i c da t a , wi th low backgroundr a t e s . Despi te a la rg e amount of lu na r du st which adhered t o one end ofthe package when i t f e l l o ver s e v er a l t imes dur in g deployment ( f i g . 3-41 ,t h e t empera tu res th roughout the lu nar day and n ig h t remained wi th i n th erange a l lowed fo r t h e ins t rument . ,Fho tographs show tha t t h e ins t rum enti s pro per ly deployed and al igned.

,3.1.5 Cold Cathode Gage Experiment

The cold cathode gage (ref . 2 ) was deployed 4 f e e t s o u t h e a s t o f t h es u p r a th e r m a l i o n d e t e c t o r , a imed s l i g h t l y s o ut hw e st ( f i g s . 3-2 an d 3-4).The deployment w a s accomplished a f t e r se ve ra l a t t empts i n which th e crew-man exper ienced d i f f i cu l t y w i t h t h e s t i f f n e s s o f t h e c o n ne c ti n g c a bl esw h i l e h a n d l in g t h e s u p r a th e r m a l i o n d e t e c t o r e x pe r im e n t, t h e c o l d c a t h od egage , and t h e g round sc reen a t t h e same t i m e .

The experiment w a s f i r s t tu rn ed on s ho r t ly be fo re lun ar module de-p r e s s u r i z a t i o n f o r t h e s ec on d e x t r a v e h i c u l a r a c t i v i t y . Commands weres e n t t o t h e i n st r um e n t t o t u r n on t h e h i gh v o l t ag e a nd t o o pen t h e c o l dcathode gage s e a l . The c o l d c at ho de g ag e d a t a came o f f t h e i n i t i a l f u l l -s c a l e i n d i c a t i o n s much more r a p i d l y t h a n e x p e c te d , i n d i c a t i n g t h a t t h es e a l may have been open e a r l i e r than commanded.

Because a s p o nt a ne o u s change i n t h e o p e r a t i o n a l mode o f t h e c o l dca thode gage and th e supra thermal ion de t ec t o r exper iment occur red a f t e rabout 1 / 2 h o u r o f o p e r a t i o n , t h e h i g h v o l t a g e s were s w it ch ed o f f u n t i la f t e r l u n a r s u n s e t .l u n a r s u n s e t , ' t h e r e s p o n s e o f t h e c o l d c a th o de g ag e wen t t o t h e mosts e n s i t i v e r a n g e, i n d i c a t iv e o f t h e low ambient p re ss ur e. When t h ep r e s s u r e r o s e a t l u n a r s u n r i s e as expecte d, t h e mode of o pe rat ion w a schanged by a grou nd command t o a l e s s s e n s i t i v e r a n g e, a nd t h e c a l i b r a t e

pu ls es appear ed normal. The experiment i s o p e r a t i n g n o r ma l ly.

When th e high vo lt ag es were swi tche d back on a f t e r



3-10

NASA-S-7 1-1620

F i g u r e 3-4. - S u p r a th e r m a l i o n d e t e c t o r e x p e ri m en t a nd c o l dcathode gage experiment deployed on t h e lunar surf ace .



3-11

3.1.6 Charged Particle Lunar Environment Experiment

The cha rged pa r t i c l e lu na r env ironment exper imen t ( r e f . 3 ) i n s t r u -m e n t ( f i g s . 3-2 and 3-5) w a s f i r s t commanded on a t 117 hours 58 minutesd u r in g t h e f i r s t e x t r a v e h ic u l a r a c t i v i t y f o r a 5-m inute f u n c t i o n a l t e s ta n d t h e i n s t r u m e n t w a s normal. The complete in st ru me nt checkout showedt h a t pre laun ch and pos t-deployment coun t i ng r a t e s ag reed wi th in 20 per-

c e n t , w i t h t h e e x c e p t i o n o f c ha nn el 6 i n a n al y ze r B .on channel 6 were twice as h i g h as t h e p r e l a u n c h v a l u e s . The c o n d i t i o ni s a t t r i b u t e d t o t h e b e ha vi or of s c a t t e r e d e le c t r o n s i n t h e p h y s ic a la n a l y z e r s w hich b eh av e q u i t e d i f f e r e n t l y i n t h e e f f e c t i v e l y z e r o mag-n e t i c f i e l d o f t h e moon com par ed w i t h t h e 0 .5 -g au ss m a g n et i c f i e l d oft h e ea r t h . The h igh coun ting ra t e s on channe l 6 d o n o t d e t r i m e n t a l l y

The count ing ra tes

NASA-S-7 1-162

F i g u r e 3-5.- C h a rg e d p a r t i c l e l u n a r environment experimentdeployed on the lunar s u r f a c e .



3-12

a f f e c t t h e s c i e n c e da t a . A l l command functions of the instrument wereexecu ted with t he ex cep t ion of t h e fo rc ed h ea te r mode commands. Subse-q u e n t t o t h e c h ec k ou t , t h e e x pe r im e nt w a s commanded t o sta ndb y.

A f t e r l u n a r module a s c e n t , t h e c h a rg ed p a r t i c l e lunar environmentexperiment w a s commanded on a t 142 hours 7 minutes and t h e d u s t c o v e rw a s removed about 1 5 hours and 20 minutes l a t e r . O p e r a t in g t e m p e r a t u r e s

a re nominal. The m a x i m u mt e m p e r a t u r e d u r i n g l u n a r d a y i s 136' F and t h eminimum temperature during lunar night i s minus 11' F. The ins t rument ' sope ra t i ona l hea te r cyc led on au tom at ica l ly when t h e e l e c t r o n i c s t e m p e r a -t u r e reached 32' F a t l u n a r s u n s e t , and was commanded on i n t h e forced-onmode a t 14' F , as planned.

The instrument, on one occasion, changed from t h e manual mode ( a tt h e p l u s 3 50 0- vo lt s t e p ) t o t h e a u t o m a t i c mode.s e q u e n t l y commanded back i n t o t h e manual mode.t h e d a t a which would i nd ic at e th e cau se of t h e mode change.

The instrument w a s sub-There i s no ev idence i n

3.2 LASER R A N G I N GRETRO-REFLECTOR

The l a s e r r an gi ng r e t r o - r e f l e c t o r ( r e f . 4 ) w a s deployed dur ing t h ef i r s t ex t ra v eh i cu l ar a c t i v i t y a t a d i s t a n c e o f a p p r o x i m a t e l y 10 0 f e e twest o f t h e A po ll o l u n a r s c i e n t i f i c e xp e ri m en t p ac ka ge c e n t r a l s t a t i o n( f i g s . 3-2 and 3-6) . Leveling and alignment were accomplished with nod i f f i c u l t y . The i n s t r u m en t w a s rang ed on by t h e McDonald Ob ser vat oryteam p r i o r t o l u n a r module l i f t - o f f an d a h i g h- q u al it y r e t u r n s i g n a l w a sreceived. Ranging a f t e r l i f t - o f f , w h i le n o t y e t c o n c l us i ve , i n d i c a t e sno s e r i o u s d e g ra d a ti o n of t h e r e t r o - r e f l e c t o r r e s u l t i n g f rom t h e e f f e c t so f t h e a s c e n t s t a g e e n g in e f i r i n g .

3.3 LUNAR PORTABLE MAGNETOMETER EXPERIMENT

The lu na r por ta bl e magnetometer (appendix A , sec t ion A.4 .2 ) w a s de -ployed a t s i t e A and near the r i m of Cone Crater ( f i g . 3-1) d u r i n g t h es ec on d e x t r a v e h i c u la r a c t i v i t y p e r i o d .i n a l l res pe c t s . The t empera tu re o f th e exper iment e le c t ro n i cs packagereach ed eq ui lib riu m, between 120' and 150' F .o ve r t h e vo i ce l i n k , i n d i c a t e d t o t a l f i e l d s o f 1 02 210 gammas a t s i t e Aand 4 1 t10 gammas a t Cone Crater. Vector component measurements of theser e a d i n g s were wel l wi th in th e dynamic range o f t h e ins t rum ent . Leve l ing ,o r i e n t a t i o n , and p o s i t i o n i n g were a c c o m p l i s h e d w i t h o u t d i f f i c u l t y ; how-

e v e r , t h e experiment cable was d i f f i c u l t t o r ew in d. T h is pro blem i s d i s -c us se d i n g r e a te r d e t a i l i n s e c t io n 14.4.3.

The i n s t r u m e n t o p e r a t e d n o m in a ll y

Meter r e a d i n g s , r e l a y e d

L L 1 1



3-13

NASA-S-7 1-1622

Figure 3-6.- Laser r ang ing re t r o - re f l ec to r experimentdep loyed on th e lu nar su r face .



3-14

3.4 SOLAR W I N D COMPOSITION EXPERIMENT

The so l a r wind composition experiment ( r e f . 4) a s p e c i a l l y p r e -p a r e d a luminum f o i l r o l l e d on a s t a f f , w a s deployed dur in g t h e f i r s t ex-t r a v e h i c u l a r p e r i o d f o r a f o i l e xp os ur e t i m e of approximately 2 1 h o u r s .Deployment w a s a cc om pl is he d w i t h no d i f f i c u l t y ; h ow ev er, d u r i n g r e t r i e v a l ,

a p p r o x i m a t e l y h a l f t h e f o i l r o l l e d u p m e c h an i c al l y a nd t h e r e m ai n d er h a dt o b e r o l l e d m an u al ly.

3 . 5 LUNAR GEOLOGY

The landing s i t e i n t h e F ra Mauro h igh lands i s c h a r a c t e r i z e d b yn o r th - s ou t h t r e n d i n g l i n e a r r idges t h a t are t y p i c a l l y 160 t o 360 f e e ti n h e i g h t and 6000 t o 13 000 f e e t i n w id th .d i s f i g u r e d by c r a t e r s r a n g i n g i n s i z e from v e r y s m a l l up t o s e v e r a l thou-sand f e e t i n d i a m e t e r.

The r idges and va l l ey s a re

The major ob jec t ive o f t h e geology survey w a s t o c o l l e c t , d e sc r ib e ,and photograph mater ia ls of t h e Fra Mauro fo rm ati on . The Fr a Mauro f o r -mation i s b e l i e v e d t o b e e j e c t a f rom t h e Imbrium B a s in , w h i c h , i n t u r n ,i s b e l i e v e d t o h ave b ee n c r e a t e d by a l a r g e i m p ac t . T h i s mater ia l i sp r ob ab l y b e s t e xp osed i n t h e v i c i n i t y o f t h e l a n d i ng s i t e where i t h asbeen exc avated from below th e re go l i th by t h e impact t h a t formed ConeCra t e r. The m ajo r p a r t o f t h e s ec on d e x t r a v e h i c u l a r a c t i v i t y t r a v e r s e ,t h e r e f o r e , w a s des igned t o sample , d esc r ibe , and photograph represe n ta -t i v e mater ia ls i n t h e Cone Crater e j e c t a . Most o f t h e r e t u r n e d ro cksamples consis t of f ragmental mate r i a l . Photographs t a ken on th e e j e c tablanket of Cone Crater show v a r i o u s d e g r e e s o f l a y e r i n g , s h e e t i n g , andf o l i a t i o n i n t h e e j e c t ed b ou ld er s. A c o n s i de r a b le v a r i e t y i n t h e n at u r eof the re tu rned f ragmenta l rocks has been no ted .

Dur ing the f i r s t e x t ra v e h ic u l ar a c t i v i t y , t h e crew t r ave r sed a t o t a ld i s t a n c e o f a b o ut 1700 f e e t . On t h e i r w a y back t o t h e l u n a r m odu le a f t e rdeployment of t h e Apollo l u n a r s c i e n t i f i c e x p er i me n t p ac k ag e , t h e crewc o l l e c t e d a comprehensive sample a n d t wo " f o o t b a l l - s i z e " r o c k s . The com-prehens ive sample a rea was p ho to gr ap he d w i t h l o c a t o r s h o t s t o t h e A po ll olu na r s c i e n t i f i c exper iment package and t o t h e l u n a r module p r i o r t o sam-p l i n g , a nd s t e r e o p h ot o gr a ph s were t a k e n o f t h e t w o " f o o t b a l l - s i z e " r o c k sb e f o r e t h e y were removed from t h e su rf ac e.l u n a r s c i e n t i f i c e x pe r im e nt p ac ka ge a n d t h e s a m pl i ng a n d p h o t o g r ap h i cs i t e s f o r t h e f i r s t e x t r a v e h i c u l a r a c t i v i t y are shown i n f ig ur e 3-1.

The l o c a t i o n o f t h e Ap o ll o .

i



3-17

NASA-S-71-1623

F i g u r e 3-7. - Modular equ ipment t r an sp or te r i n use du r ingt h e s ec on d e x t r a v e h i c u la r p e r i o d .



3-18

3. 8 APOLLO L A N D I N GSITES

The Apollo 11 through 1 4 miss ions have p laced a c o n s i d e r a b l e amountc f equipment on t h e lun ar su r f ace . F igure 3-8 s h o w s t h e l o c a t i o n s o fa l l Apollo hardware th a t has b e e n p l a c e d o r i m p a c t e d o n t h e l u n a r s u r f a c e .



NASA-S-71-162430 W 25W

3 - 4 7

20w

LUNARPLANNINGCHART (LOC-2) oo



1SE 20E

3-19 -e

Ii

rA

Mercator Projection

PREPARED UNDER THE DIRECTION OF DEPARTMENT OF DEFENSTHE AERONAUTICAL CHART AND INFORM ATION CENTER, UNITEDAIR FORCE FOR NATIONAL AERONAUTICS AND SPACE ADMIN ISTRATION.

€DITION I , JULY I96

1i

Figure 3-8.- Apollo landing site and hardware locations on lunar surface.



4.0 LUNAR ORBITAL EXPERIMENTS

Four l una r o r b i t a l e xp er im en ts w e r e conducted on Apollo 1 4 :S-band t ransponder experiment , t h e d o w n l i n k b i s t a t i c r a d a r e x p e r i m e n t ,gegenschein/Moulton point photography from lunar o r b i t , and t h e A po ll owindow micrometeoroid experiment ( a space exposure experiment not re-q u i r i n g crew p a r t i c i p a t i o n ) . D e t ai l ed o b j e c t i v e s a s s o c i a t e d w i th pho-t og r ap h y w h i le i n l u n a r o r b i t and du r in g t r a n s e a r t h f l i g h t are d i s c u s s e di n a d d i t i o n t o t h e a fo r em e nt io n ed e x p e ri m e nt s . The e v a l u a t i o n s of t h elunar o r b i t a l e x p e r i m e n t s g iven here are based on p re l iminary d a t a .F i n a l r e s u l t s w i l l b e p u b l i s he d i n a s e p a r a t e s c i e n c e r e p o r t (appendix E )when t h e d at a have been completely analyzed.

t h e

4 .1 S-BAND TRANSPONDER

The S-band transponder experiment w a s d e si gn e d t o d e t e ct v a r i a t i o n si n t h e l u n a r g r a v i t a t i o n a l f i e l d c a u s e d b y mass c o n c e n t r a t i o n s a n d d e f i -c i e n c i e s , a n d e s t a b l i s h g r a v i t a t i o n a l p r o f i l e s of t h e s p a c e c r a f t grou ndt r a c k s . T h i s w i l l be accomplished by an al ys is of d a ta obtai ned fromS-band Doppler tr a ck in g of t h e command and se r v ic e module and lunar mod-u le us ing t h e normal sp acec ra f t S-band sys tems .

There were same d i f f i c u l t i e s d u ri ng t h e p rime d a t a c o l l e c t i o n p e ri o d( r e v o l u t i o n s 3 th rough 1 4 ) . Two-way te le m e tr y lo ck w a s l o s t many tim esd u r i n g r e v o l u t i o n s 6 and 9 because of t h e high-gain antenna problem, mak-ing t h e d a t a f o r t h o s e r ev o l ut io n s e s s e n t i a l l y useless . A t o t h e r timesm an eu ve rs , o r i e n t a t i o n s , a nd o th e r o p e r a t i o n s i n t e r f e r e d w i t h t h e d a t a .However, s u f f i c i e n t d a t a w er e r e c e i v e d t o p e r mi t s u c c e s s f u l c o m p le ti o n

o f t h e e x pe r im e nt o b j e c t i v e s . P r e l i m in a r y i n d i c a t i o n s are t h a t t h e m a s sc o n c e n tr a t i o n s i n N e c t a r i s w i l l be b e t t e r d e sc r ib e d and t h e d i s t r i b u t i o no f g r a v i t a t i o n a l f o r c e s a s s o c i a t e d w i t h t h e F r a Mauro f o r m a ti o n w i l l beb e t t e r known. The d a t a w i l l a l s o p e rm i t o t h e r f e a t u r e s t o be e v a l u a t e d .

4. 2 BISTATIC RADAR

The o b j e c t i v e s o f t h e b i s t a t i c r a d a r e xp er im en t were t o o b t a i n d a t aon lunar sur face roughness and t h e d e p th of t h e r e g o l i t h t o a l i m i t of30 t o 60 f e e t . The experiment w a s a l s o d e s i g ne d t o d et er m in e t h e l u n a rs u r f a c e B r e w s t e r angle , which i s a f u n c t i o n of t h e b u lk d i e l e c t r i c c on-s tant o f t h e l u n a r mater ia l . No s p a c e c r a f t e q ui pm en t o t h e r t h a n t h e n o r-m a l s p a c e c r a f t s y s t e m s w a s requ i red f o r t h e exper iment . The experimentdata c o n s i s t s of r e c o r d s o f VHF and S-band tr an sm is si on s from t h e cammand



lr-2

a n d s e r v i c e m o d u l e d u r i n g t h e f r o n t s i d e pass on revo lu t ion 25 , wi thg ro un d- ba se d d e t e c t i o n o f b o t h t h e d i r e c t c a r r i e r s i g n a l s a nd t h e s i g -n a l s r e f l e c t e d f r o m the l u n a r s u r f a c e . Both t h e VHF an d S-band equip-ment performed as r e q u i r e d d u r i n g r e v o l u t i o n 2 5. The r e t u r n e d s i g n a l so f b o t h f r e q u e n c i e s w ere o f p r e d i c t e d s t r e n g t h .were rece ived th roughout th e pass a n d f r e q u e n c y, p h a s e , p o l a r i z a t i o n a n dampli tude were rec orded.i n p a r t , t h e B re ws te r an g le .

S t r o n g r a d a r e c h o e s

S u f f i c i e n t d a t a were c o l l e c t e d t o d e t er m i ne ,

4. 3 GEGENsCHEIN/MOULTON POINT PHOTOGRAPHY F R O M LUNARORBIT

The exper iment r equ i red t h r ee se t s of pho tographs t o be t aken t oh e l p d i f f e r e n t i a t e betw een tw o t h e o r e t i c a l e x p l a n a t i o n s o f t h e gegen-s c h e i n ( f i g . 4-1). Each s e t co nsi s t ed of two 20-second exposures and

NASA-S-71-1625

Toward

?7////A undefined)

to scale)

Figure 4-1 .- Camera a im i ng d i r e c t i o n s f o r g eg e ns c h ei n /Moult on point photography.



4-3

one 5-second exposure taken i n r a p i d s u c c e s s i o n .t h e e a r t h o r b i t s t a b i l i t y p o in t i n t h e ea rt h- su n s ys tem ( Mau lto n p o i n t )t o t e s t t h e t h e o r y t h a t t h e g e g e n s c h e i n i s l i g h t r e f l e ct e d from a con-c e n t r a t i o n o f p a r t i c l e s c a p t u re d a bo u t t h e M au lto n p o i n t .s e t s were taken t o t e s t another theory tha t the glow i s l i g h t r e f l e c t e df r o m i n t e r p l a n e t a r y d u s t t h a t i s s e e n i n t h e a n t i - s o l a r d i r e c t i o n .

t h i s t h e o ry, t h e b r i g h t en i n g i n t h e a n t i - s o l a r d i r e c t i o n i s t h ou g h t t o b edue t o h i gh er r e f l e c t i v i t y o f p a r t i c l e s e x a c t l y o p p os i te t h e sun.a n o b s e r v er on e a r t h , t h e a n t i - s o l a r d i r e c t i o n c o i n c i d e s w i t h t h e d i r e c -t i o n o f t h e Moulton po in t an d t h e o b s e r v e r i s u na bl e t o d i s t i n g u i s h be-tween t h e t h e o r i e s .a n t i - s o l a r d i r e c t i o n by a p p ro x i ma t el y 1 5 d e g r e es , a nd t h e r e f o r e , candis t ingu ish be tween the two poss ib le sources .

One s e t w a s obta ined of

Two a d d i t i o n a l

I n

Fo r

F'rom t h e moon t h e ob se rv er i s disp laced f rom the

The 16-DIEI a ta acqu is i t ion camera w a s used with an 18-EUD o c a ll e n g t h l e n s .vous window w i t h a r igh t ang le mi r ro r assembly a t t ached ahead of thel e n s and a rem ote c o n t r o l e l e c t r i c a l c ab l e a t t a c h e d t o t h e camera sot h a t t h e Command Module Pilot could actuate the camera from the lowere q u i p m n t b a y.exposures added t o it p r i o r t o a nd a f t e r t h e f l i g h t which w i l l permitphotometric measurements of t h e phenomena by means of photographic den-s i tomete r and i sod ens i t race read ings dur ing da t a reduc t ion . The inves -t ig a to r s a l s o ob ta ined ground photography of th e phenomena us in g id en t i -c a l equipment and f i lm p r i o r t o t h e t i m e of Apollo 1 4 d a t a c o l l e c t i o n .

The camera w a s bracket-mounted i n th e r ight-hand rendez-

The f l i g h t f i l m h ad s p e c i a l , l o w - li g h t -l e v el c a l i b r a t i o n

The experiment was accomplished during the 15th r e v o l u t i o n o f t h emoon.o n s t r a t e d t h a t l o n g e x p o s u r e s are p r a c t i c a b l e .

The aiming and f i lming were exce l len t and the exper iment has deni-

4.4 APOLLO WINDOW METEOROID EXPERIMENT

The obdec t ive o f t h i s experiment i s t o d et er m in e t h e meteoroidc r a t e r i n g f l u x f o r p a r t i c l e s r e s p o n s ib l e f o r t h e d eg ra da ti on o f glasssurfaces exposed t o th e space environment. The Apoll o connnand modulewindows are used as m et eo ro id d e t e c t o r s . P r i o r t o f l i g h t , t h e windowsare scanned a t 20x t o determine t h e genera l background of ch ips , sc ra tche sa nd o t h e r d e f e c t s . D ur in g p o s t l f i g h t i n v e s t i g a t i o n s , t h e windows w i l la g a i n be scehned a t 20x t o map a l l v i s i b l e d e f ec t s.e s t w i l l t h e n be magnified up t o 7 6 5 ~ o r f u r t h e r examination.Apollo 12 and 13 s id e windows and hat ch windows were examined fo ll ow in gt h o s e f l i g h t s and t h e r e s u l t s w e r e compared w i t h p r e f l i g h t s c a n s . No

meteoroid impacts larger than 50 microns i n diameter were detected ont h e Apollo 12 windows although t h er e w a s an inc rease i n the number ofch ip s and o the r low-speed sur face e ff ec t s . The Apollo 13 l e f t -hand-s idesrindow had a suspected nreteoroid impact 500 microns i n diameter.

The po in t s o f in te r-The



4-6

4.9 TRANSEARTH LUNAR PHOTOGRAPHY

Photographs were taken of the v i s i b l e d i s c o f t h e moon a f t e r t r a n s -e a r t h i n j e c t i o n t o p r ov i de ch an ges i n perspec t ive geomet ry, p r imar i lyi n l a t i t u d e . The p h ot og r ap h s w i l l be used t o r e l a t e t h e p o s i t i o n s oflunar features a t h ig h er l a t i t u d e s t o fea tures whose pos i t ions are known

t hr o ug h lan dm ar k t r a c k i n g a nd e x i s t i n g o r b i t a l s t e r e o s t r i p s . The pho-tography w a s s u c c e s s f u l u s in g t h e Hasselblad data camera w i t h t h e 80-mmlens and black-and-white f i lm. Addi t iona l coverage wi th the 70-mmHasselblad camera an d t h e 250-mm l e n s u s i n g c o l o r f i lm w a s a l s o o b t a in e d .

I . .Y L I * i - L..



5 .O

5-1

I N n I G H T DEMONSTRATI O N S

In f l ig h t demons tra t ions were conduc ted t o e v a l u a t e t h e b eh a vi o r o fp h y s i c a l p r o c e ss e s o f i n t e r e s t u n d e r t h e n e a r - w ei g h t le s s c o n d i t i o n s o fspace . Four ca tegor ies o f p rocesses were demonstrated, and segments ofthe demons t ra t ions were t e lev i sed over a 30-minute per iod dur ing t r an s -e a r t h f l i g h t b e gi nn in g at approximately 172 h o u r s .four demons t ra t ions w i l l b e p u b l is h e d i n a s u p pl e me n ta l r e p o r t a f t e r anal-y s i s o f d at a has been completed.

F i n a l r e s u l t s o f a l l

(See appendix E . )

5.1 ELECTROPHOFETIC SEPARATION

Most o rg a n ic mo l ec u le s , when p l a c e d i n s l i g h t l y a c i d o r a l k a l i n e

Molecu les o f d i ff e r en t sub-water s o l u t i o n s , w i l l move through them i f an e l e c t r i c f i e l d i s a p p l i e d .This e f f e c t i s known as e l e c t r o p h o f e s i s .stances move at di ffe ren t speeds ; thus , some molecu les w i l l o u t r u n o t h e r sas they move from one end of a t u b e o f s o l u t i o n t ow ar d t h e o t h e r. T h i sprocess might be e x p l o i t e d t o prepare pure samples o f o rg an ic mat e r i a l sf o r a p p l i c a t i o n s i n m ed ic in e an d b i o l o g i c a l r e s e a r c h i f problems due t osample Sedimentation and sample mixing by convection can be overcome.

A s m a l l f l u i d e l e c t r o p h o r e s i s d e mo n st ra ti on a p p a ra t us ( f i g . 5-1) w a su s ed t o d e m on s tr at e t h e q u a l i t y o f t h e s e p a r a t i o n s o b t a i n e d w i t h t h r e esample mixtures having widely d if f e r e n t molecular weight s . They were:(1) mixture o f red and b lue o rgan ic dyes , ( 2 ) human hemoglobin, and( 3 ) DNA ( t h e molecules t h a t carry genetic codes) from salmon sperm.

Postmission review of the f i l m e d d a t a reveals t h a t t h e r e d a n d b l u e

organ ic dyes separa ted as expected; however, sep ara t io n of t h e hemoglobinand DN A cannot be detected. P o s t f l i g h t e x am in at io n o f t h e a p p ar a t u s i n -d i c a t e s t h a t t h e sa mp le s w ere n o t r e l e a s e d e f f e c t i v e l y t o p e r m i t g oods e p a r a t i o n , c a us i ng t h e d yes t o s t r eak . However, t h e f a c t t h a t t h e d y e ss e p a r a t e d s u p p o r t s t h et h a t s e d i m e n t a t i o n a n dthe space environment .because they con ta inedp r i o r t o a c ti v a ti o n , o f

p r i n c i p l e o f e l e c t r o p h o r e t i c s e p a r a t i o n a n d s h o w sc o n v e c t i o n e f f e c t s a r e e f f e c t i v e l y s u p p r e s s e d i n

The hemoglobin and D N A samples d id no t sepa ra teb a c t e r i a t h a t consumed the organic moleculest h e a p p a r a t u s .

5 .2 LIQUID TRANSFER

The l i q u i d t r a n s f e r d e m o ns tr at io n ( f i g . 5-2) was d e s i gn e d t o e v al u -a t e t h e u se of t an k b a f f l e s i n t r a n s f er r i n g a l i q u i d f ro m o ne t a n k t o



NASA-S-71-1626

Figure 5-1.- Electrophoresis demonstration unit.



5-3

NASA-S-7 1-1627



I -

5-4

anoth er under near-zero-gravi ty con di t ion s . The demonstra t ion w a s con-d u c t e d u s i n g t w o s e t s o f t a n k s , o n e s e t c o n t a i n i n g b a f f l e s and t h e o t h e rw i th o ut b a f f l e s . Tr a ns f e r of l i q u i d b etw ee n t h e u n b a f fl e d t a n k s w a s un-s u c c e s s f u l , as e x pe c te d . Tr a n s f e r b et we en t h e b a f f l e d t a n k s d e mo n st ra t edt h e e f f e c t i v e n e s s o f tw o d i f f e r e n t b a f f l e d es i g ns . P h ot og ra p hi c d a t a i n -d i c a t e t h a t b ot h de s ig n s w ere s uc ce ss fu l i n p e r m i t t i n g l i q u i d t r a n s f e r .

5 .3 HEAT FLOW AND CONVECTION

The purpose of the h e a t f low and convect ion 'demonstra t ion ( f ig . 5-3)was t o o b t a i n data on t h e t y p es an d amounts of convection t h a t can occuri n t h e near-weight les s environment of space.a lmos t suppressed under these cond i t ions ; however, convect ive f l u i d f lowcan o cc ur i n s p a c e by means of mechanisms ot h er th an g r av i ty . For i n -s t a n c e , s u r f a c e t e n s i o n g r a d i e n t s a n d, i n some c a s e s , r e s i d u a l a c c e l e r a -t i o n s c a us e l ow - le v el f l u i d f lo w. . F ou r i n de p en d en t c e l l s of s p e c i a l de-sign were used t o d e te c t c o nv ec ti on d i r e c t l y, o r d e t e c t c o nv e ct iv e e f f e c t sby measurement of heat f low ra tes i n f l u i d s . The h e a t f lo w ra tes werev i s u a l l y d i sp l a ye d by c o l o r- s e n s it i v e , l i q u i d c r y s t a l t h e r m a l s t r i p s andthe co lo r changes filmed w i t h a 16-rn d a t a camera. R e v i e w of t h e f i l mhas shown t h a t t h e expected da t a were obta ined .

Normal ' convect ive f low i s

5.4 COMPOSITE C A S T I N G

T h i s demonstra t ion w a s d e si gn e d t o e v a l u a t e t h e e f f e c t of near-zero-g r a v i t y o n t h e p r e p a r a t i o n of c a s t metals , f ibe r- s t r eng thened mater ia ls ,a n d s i n g l e c r y s t a l s .b e r ( f i g . 5-4) and r e t u r n e d f o r ex a mi n at i on a nd t e s t i n g .

11 specimens w a s processed.ment were noted.occurred.

Specimens were p r oc e s se d i n E s m a l l heating cham-A t o t a l o f

No problems w i t h t h e procedures o r equip:An x-ray of t h e samples v e r i f i e d t h a t good mixing

1

L



5-5

NASA-S-71-1628

Figure 5-3.- Heat flow and convection demonstration unit.



5-6



TABLE 6-1. SEQUENCEOF EVENTS'

Range zero - 21:03:02 G . m . t . , January 31, 1971

Lif t -o ff - 21:03:02.6 G . m . t . , January 31, 1971l ' r anslunar in j ec t i on maneuver, F i r i ng t i m e = 350.8 s e cr r a n s u n a r i n j e c t i o nS-IVB/command module separationl ' ranslunar dockingS p a c e c r a f t e j e c t i o nF i r s t m i d c o u r s e c o r r e c t i o n , F i r i n g time = 10.1 s e cSecond midcourse cor rec t ion , F i r ing t i m e = 0.65 s e cLunar o r b i t i n s e r t i o n , F i r i n g t i m e = 370.8 s e cS-IVB l u n a r i mp ac tDescent o r b i t i n s e r t i o n , F i r i n g time = 20.8 s ecLunar module undocking an d s e p a r a t i o nC i r c u l a r i z a t i o n man eu ve r, F i r i n g t i m e = 4 s e cPowered d es ce nt i n i t i a t i o n , F i r i n g t i m e = 764.6 s e cLunar l a n d i n gS t a r t f i r s t e x t r a v e h i c u l a r a c t i v i t yF i r s t data f r c n n Apol lo lun ar su r f ac e exper iment packagePlane change , F i r ing t i m e = 18.5 s e cComplete f i r s t e x t r a v e h i c u l a r a c t i v i t yS t a r t s e c o n d e x t r a v e h i c u l a r a c t i v i t yE n d s e c o n d e x t r a v e h i c u l a r a c t i v i t yLunar l i f t - o f f , F i r i n g time = 432.1 s e cVern ier adjustment maneuver, F ir in g time = 12.1 s e cTe r m i n a l p h a s e i n i t i a t i o nTe r m i n a l p h a s e f i n a l i z a t i o nDockingLunar module j e t t i sonSeparat ion maneuverLunar module deorbi t maneuver, Fir ing t i m e = 76.2 s e cLunar module lunar impactTr a n s e a r t h i n j e c t i o n , F i r i n g t i m e = 149.2 s e cT h i r d m id c ou r se c o r r e c t i o n , F i r i n g time = 3.0 s e cCommand module/service module separationE n t r y i n t e r f a c e .Begin blackoutEnd bla ck outDrogue deploymentLanding

"see table 6-11 f o r ev e nt d e f i n i t i o n s .

E lapsed t i m e ,h r :min : e c

02 :28 202 34 3203 :02 29

05 : 7 4

76 : 8 281 :56 : 4182:37:5286:10:53

103 7 2105:11:46

10 8 2 27108:15 :09113:39 :ll116 :47 58117 :29 33118:27:01131 :08:13135 :42 4141 :45 : 0141 : 6 : 9142:30 :51143 :13:2914 3 32 : 1145 :44 :58145 :49 :43147 :14 :17147:42:23148 36 : 2165 :34:57215 : 2 : 2215 : 7 5215 :48:02215:51:19

216 :01:58

04 :56 :56

30 :36 :08

215 : 6 :08



6- 3

TABLE 6-11.- DEFINITION OF EVENT TIMES

Event-Range zero

D e f i n i t i o n

Final i n t e g r a l s e co nd be f o r e l i f t - o f f

Lift-off I n s t m e n t a t i o n u n i t u m b il i c a l d is c on n ec t

Trans lunar in jec t ion maneuver S t a r t t a n k d i s c h a rg e v a l v e o p e ni n g , a l l o w in gfuel t o be plrmped t o t h e S-IVB engine

s-IVB/cCmmand module repa ra t io n. t r m r lu n a rdocking, r p a c e c r a f t e j e c t i o n . l m a r module s p a c e c r a f t ra te and acce le rometer dataundocking and separa t ion . docking. and com-a d odule l a n d i n g

Conund and rervice module and lunar modulecompute r-c ant rol led maneuvem

Commnd a n d s e r v i c e module an d lunar modulenon-computer-controlled maneuvers

S-IVB lu na r impact

Lunar module descen t eng ine cu toff t ime

The t ime of t h e e v e n t b a a ed o n analysis of

The time t h e computer commands t h e eng ine onan d off

h g i n e i g n i ti o n M i n d i c a t e d b y t h e a p p r o pr i -ate engine b i leve l t e lemet ry measurement

Loss of S-band t ransponder s igna l

B g i n e c u t o f f e s t a b l i s h e d b y t h e b e gi n ni n g o fdrop i n t h w t chamber p r e s s u r e

Lunar module impact

I u n u landing

Beginning ,o f x t r av e h i cu l a r a c t i v i t y

End of e x t r a v e h ic u l a r a c t i v i t y

Apollo lunar rurface experiment package fintd a t a

Comaad module/service module s e p a r a t i o n

E n t r y i n t e r f a c e

Begin and end b lackout

Drogue d e p l q m e n t

E a r t h l a n d i n g

The time t h e f i n a l data p o i n t is t r a n s m i t t e df ro m t h e v e h i c l e t e l e m e t r y s y st e m

P i n t c o nt ac t o f a lu na r module landi ng pa dw i th t h e l u n a r s u r f a c e as d e r i v e d from anal-y s i s of s p a c e c r a f t ra te data

The t i m e c a b i n p r e s s u r e r e a c h e s 3 psi. duringd e p r e s s u r i z a t i o n

The t i m e c a b i n p r e s s u r e r e a c h e s 3 p s i a duringr e p r e s s u r i z a t i o n

Rece ip t of f i n t data c o n si d e re d t o be v a l i dfrom t h e Apo l lo l u n a r r u r f a c e e x pe r im e ntpackage telemetry sys tem

Sepa rat io n in di ca te d by command module/se rvicemodule repara t ion re lqys A an d B v i a t h etelemetry syr tem

The time t h e cormund module rea che s bo0 000fee t g e o d et i c a l t i t u d e u n d i c a t e d by t h eb e s t estimate of t h e t r . j c c t o y

S-band coarmnic ation lor e due t o d r i o n i z a t i o nd ur in g e n t y

Deployment indicated by drogue deploy relaysA an d B r i a t h e t e l e m e tr y r y r t -

The t i m e t h e command module touch es t h e vaterY de te rmined from a c c e l e r o m e t e m



TABLE 6-111.- TRAJECZdRY PA M X B Z E d

Lfannca T i u . wit*. lalait*.bog h r d n : a r 6 6 b 6

-leu p h r.

I u t hI u t h

m 16:58:12.0 0.56 I 6l.b Ykm I 76:58:U.6 I 0 3 6 I I 6l.M tl

&.n

81:56:40.182 :02 :51.5

82:31:52.2

e6 : 0 : 3. 0M : U : + 8

103:47:lr1.6

lO5:U:46.11 q : l l : 5 0 . 1

108:a2:26.5

108:15:09.3

111:29:33.1ll7:29:51.6

l41:45 :cO

141:56 : 9.4

142:30:51.1

lb3:13:29.1

143:32:50.5

145 :a 58.0

145 :C b . 5

141:14 116.91bT:U 33 . 1

14T:b:23.4

148:36:02.3l48:38:Y.5

m u rbi

2.83 I0. U I

6.58 I6.29 I

12.65 I

1.05 I1.04 I

7.38 8

10.63 EU.18 I

0.5 1

l l . 1 I

11.3 I

10.18 I

3.21 8

0.62 I

u.92 I

l2.u I

3 . b 8

7.4l I6.64 I-

h u e-1 ~ 4 . m161.58 1

173.60 Y11b.65 Y

m.Ts I

118.56 I178.35 I

1.s7 Y

96.u I95.40 I

n.1 Y

149.6 Y

16.7 I

161.h Y

21.80 Y

-1p.R Y

61.U 163.53 I

l 9 .61 W

Q . 5 5 w168.85 I

-. 8 r. h

64.9

. 59.259.0

9 . 5

60.1160.3

7.e

62.162.1

11.1

44.t

58.t

58.6

99.9

60 .

51.i51.t

0.C

60 I66.!

8 061.45 458.5

5 W.85 m . 5

5 435.8

5 2 n . 35 342.1

5 565.6

5 333.15 333.3

5 5 u . 5

5 396.6

5 %5.5

5 353.5

5 344.6

5 S 1 . T

5 358.15 m . 0

5 704.9

5 3Lo.68 9 5 . 0

9.911.3

-0.08

-0.m-1.52

-0.10.99

0.00

-0.040 .U

0.m

o.n

-0.-

0. U

0.-

0 .LL9

0 .ola0.019

-3.685

-0.115 . w

-4 T . Ss3B. la

a4r.Urb6.94

PL1.Q

8M.M8 M .36

W0e

an.&r4l.m

2W.l

W .0

W . 5

268.06

ml.9

2 e . 3

161.3nd1.l

rm.1

nb0.ma66.m

L



6-5

TABLE 6-1v.- DEFINITION OF TRAJECTORY AND ORBITAL PARAMETERS

TrqJec tory Darnmetere

G e o d e t i c l a t i t u d e

S e l e n o g r a p h i c l a t i t u d e

Longitude

A l t i t u d e

Space- f ix ed ve loc i y

Space- f ixed f l igh t -pa th ang le

Space-fixed he ading angle

Apogee

P e r i g e e

Apocynthion

P e r i c y n t h i o n

P e r i o d

I n c l i n a t i o n

Longitude of t h e ascending node

D e f i n i t i o n

The spher ica l coord ina te measured a long e meridian on the

e a r t h f ro m t h e e q u a t o r t o t h e p o i n t d i r e c t l y b e ne at h t h es p a c e c r a f t , d e g

T h e d e f i n i t i o n i s th e same 8s t h a t o f t h e g e o d e t i c l e t i -t u d e e x c e p t t h a t t h e r e f e r e n c e b o d y i s th e moon ra th ert h en t h e e a r t h , de g

T h e s p h e r i c a l c o o r d i n a t e , as m ea su re d i n t h e e q u a t o r i a lp lan e , between th e p lene of th e re fe renc e body ' s p r imemer idian and the p lane of t he sp ace cra f t mer id ian , dey,

The distance measured along e v e c t o r fr om t h e c e n t e r o ft h e e a r t h t o t h e s p a c ec r a f t. . When t h e r e f e r e n c e body i sth e moon, i t i s th e d i s tan ce measured f rom th e r ad ius o ft h e l a nd in g s i t e t o t h e s p a ce c r a ft a lo n g a vector fromt h e c e n t e r o f t h e moon t o t h e s p a c e c r a f t , f t or miles

M ag nitu de o f t h e i n e r t i a l v e l o c i t y v e c t o r r e f e r en c e d t ot h e b o dy - ce n te r ed , i n e r t i a l r e f e r e n c e c o o r d i n a t e s ys t e m,f t / s e c

Flight- path angle measured po si t i ve upward from the body-c e n te r e d l o c a l h o r i z o n t a l p l a n e t o t h e i n e r t i a l v e lo c it yvec tor, deg

A ngle o f t h e p r o J e c t i o n o f t h e i n e r t i a l v e l o c i t y v e c t o ron to th e body-cen te red lo ca l hor iz on t a l p lan e , measuredpos i t ive eas tward f rom nor th , deg

The po in t o f maximum or b i ta l a l t i t ud e of th e space cra f ta bove t h e c e n t e r o f t h e e a r t h , m i l e s

The po in t o f min imum orb i ta l a l t i tude of the spacecra f tabove t h e c e n t e r o f t h e e a r t h . m i l es

The point of maximum orbital al t i tude above the moon asmeasured from the ra d ius o f th e lun ar l and ing s i t e , miles

The poi nt of minimum or bi ta l a l t i t u de above the moon asm ea sur ed f ro m t h e r a d i u s o f t h e l u n a r l a n d i n g s i t e , miles

Time r e q u i r e d f o r s p a c e c r a f t t o c o m pl et e 360 degrees ofo r b i t r o t a t i o n , m i n

The t r ue an'gle between the spa cec ra f t o r b i t p lane and ther e f e r e n c e b o dy ' s e q u a t o r i a l p l a n e , d eg

T h e long i tude at w hic h t h e o r b i t p l a n e c r o s s e s t h e r e f e r -ence body 's equ a to r ia l p lane go ing f rom t h e Southern t oth e Northern Hemisphere, deg



6-6

P r o P ~ i ~

I e r r l n pmpulsion

8 . d c a propulsion

TABLE 6-v.- MANEWER SUMMARY

30 :36 :07 .9 10.1 n.1 67 8130

76:58:12 0.65 3.5 61 8153

rgnitim time.hr:Lln:m*c

81 : 6 : b o .7

86:lo:53

103: h7 : 1.6

105:l.l A6.1

lo8:02:26.5

l.l7:29:33.1

1 b 1 L5 :b O

1 b 1 : % : b9 .b

1L2:30 :s1.1

1b3:13:W .1

145 :b9 :b2.5

1 4 1 lb :16.9

firing tin.sec

370.8

20.8

2.7

L O

764 :6

18.5

L 9 . l

l2.1

3.6

26.1-

15.8

76.2

3022.b

205.7

0. 8

77.2

6639.1

3T0.5

6066.1

10.3

88.5

32.0.

3.b

186 .l

I r t i tud . ,de8:dn

4:lh I

2:56 I

2:os I

2 : z l I

2:12 I

mLlt-*dbg:8in

172:24 w

1 7 3 5 2 W

1=:52 w

167:bd 1

167rb1 I

L r r i n l t i mhr .in :*c

82:15:19

&:ll:Za

82:01:01

&:OO:b5

&:bo136

169 o

58.8

60.2

63.9

62.1

51.7

51.2

60 .l

61.5

63.4

56.1

58.1

9.1

7.8

56 .O

s7.7

8.5

8 .b

b6.0

58.2

56.8

-59.8

. .I I L L L- L- L L



6-7

hig her descen t p ropu ls ion sys tem pr op e l l an t marg in . Both ve h i c le s re -m ai ne d i n t h e lo w - pe r ic y nt h io n o r b i t u n t i l s h o r t l y a f t e r l u n a r modules e p a r a t i o n . After sep ara t ion , t h e per icy n th io n o f t h e command and se rv-ice modules w a s i n c r e as e d t o 56 m i l e s an d a plane-change maneuver w a sl a t e r e x e cu t ed t o e s t a b l i s h t h e p r o p e r c o n d i t io n s f o r r en d ez vo us .

6.2.3 Lunar Descent

P r e p a r a t i o n s f o r l u n a r d e s c e n t .- The powered descent and lunar land-i n g were s imi la r t o t h o s e of p r e v io u s m i s s i o n s .p e rf o rm e d i n p r e p a r a t i o n f o r po we re d d e s c e n t w a s more a cc ur ate becauseof t h e command and ser vi ce modules be ing i n t h e 58.8- by 9.1-mile desc ento r b i t f o r 22 h o u r s p r i o r t o p ow er ed d e s c e n t i n i t i a t i o n . W hi le i n t h i so r b i t , the Network ob ta ined long per iods of r ada r t r a c k i n g o f t h e un pe r-tu rbed spacecra f t f rom which a more a c c u r a t e s p a c e c r a f t s t a t e v e c t o r w a sdetermined. The po si t i on of t h e command module re l a t iv e t o a known land-m a r k n e a r t h e l a n d i n g s i t e w a s a c c u r a t e l y d e t e r m i n e d f r o m s e x t a n t markst ak en on t h e landmark . Cor rec t ions f o r known of f s e t ang les between th e

lan dm ar k a n d t h e l a n d i n g s i t e were used t o compute a v e c t o r t o t h e l an d-i n g s i t e . T h i s v e c t o r w a s s e n t t o t h e l u n a r m odule. Also, t h e M i ss io nCont ro l Cen te r p ropaga ted t h i s v e c t o r f or wa rd t o t h e t i m e o f l a n d i n g t op r e d i c t e r r o r s due t o n a v i g a ti o n . T h i s p ro ce du re w a s performed duringt h e t w o revo lu t ions before powered descen t and a f i n a l l an d in g s i t e up-date of 2800 f e e t w a s computed and r e l a y e d t o t h e crew. A f t e r i g n i t i o nf o r t h e p ow er ed d e s c e n t , t h e c rew m an u al ly i n s e r t e d t h e u p d a t e i n t o t h ecomputer.

However, t h e nav iga t ion

Powered descent .- Tr a j e c t o r y c o n t r o l d u r i n g d e s c e n t w a s nominal ,a n d o n l y o n e t a rg e t r e d e s i g n a t i o n o f 35 0 f e e t l e f t ( t o wa r d t h e s o u t h )w a s made t o t a k e a d va n ta g e o f a smoother landing a r e a .t a k e o v e r , t h e c rew f l e w approximately 2000 feet downrange and 300 f e e tn o r t h ( f i g . 6-1) b ec au se t h e t a r g e t e d c o o rd i n at e s o f t h e l a n d i n g s i t egiven t o th e lu n ar module computer were i n e r ro r by about 1800 f e e t .

A f t e r manual

C o o rd i na te s o f t h e l a n di n g p o i n t are 3 degrees 40 minutes 24 sec-onds s o u t h l a t i t u d e a n d 1 7 degrees 27 minutes 5 5 seconds w e s t l o n g i t u d e ,which i s 55 f e e t n o r t h a n d 165 f e e t e a s t o f t h e p r el a u nc h l a n d i n g s i t e( f i g . 6-2).8.6.)

( F u r t h e r d i sc u s s i o n o f t h e d e s ce n t i s c o n ta i ne d i n s e c t i o n



6-9

-0d-

.m



6-10

H o r i z o n t a l R a d i a l

f t / s e c ft secData s o ur c e v e l o c i t y, v e l o c i t y ,

Primary guidance andnav iga t ion sys tem 5544 30

P ow ered f l i g h t p r o c e s s o r 5544 29

Abort gu ida nce system 5542 29

6. 2. 3 Lunar Ascent and Rendezvous

A l t i t u d e , ft

60 311

60 345

60 309

To accomplish a d ir ec t rendezvous wi th t h e command module, a re-ac t io n co n t ro l sys tem ve rn ie r ad jus tment maneuver o f 10 .3 f t / s e c w a sperformed approximately 4 m i nu t es a f t e r a s c e n t e n g i n e c u t o f f .neuver w a s necessary because the lunar module ascent program i s t a r g e t e dt o a c hi ev e a n i n s e r t i o n v e l o c i t y an d n o t a s p e c i f i c p o s i t i o n v e c t o r.Direct rendezvous w a s nominal and docking occurred 1 hour 47 minutes10 seconds a f t e r lunar l i f t - o f f .

The ma-

The l u n a r module rendezvous nav ig ati on w a s accomplished throughoutthe rendezvous phase and all s o l u t i o n s a g r e e d c l o s e l y w i t h t h e g r o u n dso lu t i on . The comand module which w a s performing backup rendezvousn a v i g a t i o n w a s n o t a b l e t o o b t a i n a c ce p ta b le VHF r a ng in g d a t a u n t i l a f t e rt h e t e r m i n a l p ha se i n i t i a t i o n m an euv er.s e c t i o n 1 4 . 1 . 4 . Figure 14-7 i s a c om pa ri so n o f t h e r e l a t i v e r a n g e asmeasu red by l u n a r module ren dez vou s r a d a r and command module VHF, anddetermined from comnand module s t a t e v e c t o r s a n d t h e b e s t - e s t i m a t e t r a -je ct o ry pro pag atio ns . The VHF mark t a k e n a t 142:05:15 and inc orp ora tedi n t o t h e command module computer's s t a t e v e c t o r f o r t h e l u n a r m odulecaused an 8 .8-mile re la t i v e range e r ro r.

The VHF anomaly i s d i s c u s s e d i n

Sev era l s ex tan t marks were t a ken a f t e r t h i s e r r o r w a s i n t r o d u c e d .Because the compu ter weigh s t h e VHF marks more h e a v i l y t h a n t h e s e x t a n tm ar ks , t h e a d d i t i o n a l s e x t a n t marks d i d n o t r e du ce t h e e r r o r s i g n i f i c a n t -l y . The ran ging problem apparen t ly c le are d up a f t e r t h e t e r m i n a l p h a s e



6-11

i n i t i a t i o n m an eu ve r an d t h e VHF w a s u se d s a t i s f a c t o r i l y f o r t h e mid co ur sec o r r e c t i o n s .s o l u t i o n s .

Table 6-VI prov ides a summary or t h e rendezvous maneuver

TABLE 6-v1. - RENDEZVOUS SOLUTIONS

Maneuver

Terminal phasei n i t i a t i o n

F i r s t m i d c o u r s ec o r r e c t i on

Second m idcours ec o r r e c t o n

Computed ve lo c i ty change , f t sec

Network~~

v = 63.0

# = 67.0Vt = 92.0

No grounds o l u t i o n .

fl = 1 . 0

Z

No grounds o l u t i o n .

Lunarmodule

v = 62 .1\r = 0.1V = 63.1V = 88.5

v = -0.9

vy = 0 .6

t

v" = 0 . 2

vt" = 1.1

v = -0 .1

Vy = -1 .4v" = 0 . 1

vt = 1 .6

Command an dservice module

V = -67.4fl = 0 . 5Vy = -69.2V = 96.6

v = 1 . 3vx = -0 .1vy = -1.1

zv = 1 .7

v = 0 .6

t

v" = -0 .2vy = -2 .2v; = 2 . 3

6.2.4Lunar Module Deorbit

Two hours a f t e r docking, the command and service modules and lunarmodule were o r i e n t e d t o t h e l u n a r m odu le d e o r b i t a t t i t u d e , u nd oc ke d, a ndt h e command and se rv ic e modules then se pa ra ted from t h e lun ar module.The lu na r module was d e o r b i t e d on t h i s m i ss io n , s i m i l a r t o A po ll o 1 2 .The deorb i t w a s performed t o e l i m i n a t e the lunar module as an o r b i t a ld e b r i s h a z a rd f o r f u t u r e m i ss io n s a nd to provide an impact that couldb e u s e d as a ca l i b r a t ed impulse fo r th e se i smograph ic equipment. Ther e a c t i o n c o n t r o l s y s te m o f t h e l u n a r module w a s u s ed t o p e rf or m t h e7 5- se co nd d e o r b i t f i r i n g 1 hour 24 minutes 19 .9 seconds a f t e r t h e com-mand and se rv ic e modules had sep arat ed from t h e lu na r module. The lun armodule impac ted the lunar su r face a t 3 degr ees 25 minutes 12 seconds

s o u t h l a t i t u d e a n d 19 degrees 40 minutes 1 second wes t long i tude wi th av e l o c i t y o f a bo ut 5500 f e e t pe r second.Apollo 14 l a n d i n g s i t e , 6 2 m i l es f r om t h e A p ol lo 1 2 l a n d i n g s i t e , a n d7 miles from t h e p re la u nc h t a r g e t p o i n t .

T h i s p o i n t w a s 36 miles from t h e



6-12

6.3 TRANSEARTH AND ENTRY TRAJECTORIES

A nomina l t r ansear th in jec t ion maneuver w a s performed a t about148 hours 36 minute s. Seventeen hour s a f t e r t r a n s e ar t h i n j e c t i o n , t h et h i r d an d f i n a l mid co urse c o r r e c t i o n w a s performed.

F i f t e e n m in u te s D r i o r t o e n t e r i n g t h e e a r t h ' s a t mo s p he r e, t h e corn--mand module was s e p a r a t e d frolii tne se rv ice n lodu ie . Th e command modulew a s t h e n o r i e n t e d t o blunt -end-forvrard f o r ea r t h en t r y. En t ry w a s nom-i n a l a nd t h e s p a c e c r a f t l a n d ed i n t h e P a c i f i c Ocean l e s s than one m i l efrom t h e p re l au n c h t a r g e t p o i n t .

6.4 SERVICE MODULEENTRY

The se r v i ce module sho u ld have en te red th e ea r t h ' s a tmosphere andi t s d e b r i s l a n d e d i n t h e Pa c i f i c Ocean approx imate ly 650 miles southwestof t h e command module la nd in g p o i n t . No r a d a r coverage w a s planned nor

. were t h e r e any s i g h t i n g s r e p o r t e d f o r c o n f i r m a t i o n .



7.0 COMMANDAND SERVICE MODULE PERFORMANCE

7 .1 STRUCTURALND MECHANICAL S Y S T ~

S t r u c t u r a l lo a d s on t h e s p a c e c r a f t d u r i n g all phases o f t h e miss ionwere w i t h i n d e s i g n l i m i t s . The pre d ic ted and ca lc u l a te d loads a t l i f t -o f f , i n t h e region of maximum dynamic pr es su re , a t t h e end of f i r s t s t ag eb o o s t , a nd d u r i n g s t a g i n g w e r e s imilar t o t h os e of prev ious miss ions .Camand module a c ce l er o m et e r d a t a p r i o r t o S-IC c e n t e r e n g i ne c u t o f f i n -d i c a t e a s u s t a i n e d 5 - he rt z l o n g i t u d i n a l o s c i l l a t i o n w i th an amplitude ofO.l7g, which i s s i m i l a r t o t h a t m ea su re d d u r i n g p r e v i o us f l i g h t s . O s c i l-l a t i o n s d u r i n g t h e S -I 1 b o os t p ha se h a d a m a x i m u m measured amplitude ofless than 0 .066 a t a frequency of 9 he r t z . The ampli tudes o f bo th os c i l -l a t i o n s were w i t h i n a cc ep ta b le s t r u c t u r a l d es i gn l i m i t s .

. S i x attempts were req uire d t o dock t h e command and s er v ic e modulew i t h t h e lunar module fo llowing t r an s l un ar in je c t io n . The measured r a t e san d in d i c a t e d r e a c t i o n c o n tr o l s ys te m t h r u s t e r a c t i v i t y d u ri ng t h e f i v euns ucce ssfu l docking at tempts show t h at capt ure s hould have occurred eacht i m e . The mechanism w a s ac tua ted and in sp ec te d i n t h e command modulef o l l o w in g do ck i ng . T h i s i n v e s t i g a t i o n i n d i c a t e d t h a t t h e p r ob e m e ch a ni ca lcomponents w e r e f ’unctioning nor mal ly, Subsequen t undocking and dockingwhi le i n lunar o r b i t w e r e normal. The pr obe w a s r e tu r n e d f o r p o s t f l i g h ta n a l y s i s . The docking anomaly i s d i s c us s e d i n d e t a i l i n s e c t i o n 1 4 . 1 . 1 .

7.2 ELECTRICAL POWER

7.2.1 Power Dis t r ibu t ion

The e l e c t r i c a l power d i s t r ib u t io n sys tem performed normal ly excep tP r i o r t o e n t r y, when t h e b u s - t i e m oto r s w i tc h eso r t wo d i s c r e p a n c i e s .

w e r e o p er at ed t o p u t t h e e nt ry b a t t e r i e s on t h e main b u s s e s , b a t t e r y Cw a s n o t p l a c e d on main bus B. This anomaly w a s discovered by the da tareview a f t e r t h e f l i g h t . P o s t f l i g h t c o n t i n u i t y checks r ev e al e d t h a t t h ec i r c u i t b r e a ke r t y i n g b a t t er y C t o main bus B w a s i n o p e r a t i v e . T h i sanomaly i s d e sc r ib e d i n s e c t i o n 14.1 .7 .

The second d i sc repancy occur red dur ing en t r y. P rocedures c a l l fo rmain bus d e a c t i v a t i o n , a t 800 f e e t a l t i t u d e , by o pe nin g t h e bu s t i emotor switches.

d i d no t remove power fromt h e

buses.a f t e r landing, by o pe ni ng t h e i n - l i n e c i r c u i t b r e a k er s on Pa n e l 275 ( anormal procedure) . Review of d a t a i n d i c a t e d a n d p o s t f l i g h t t e s t s con-f i rm e d t h a t t h e m otor s w i t c h which t i e d b a t t e r y A t o m a i n bu s A w a s in-o p e r a t i v e .

Th e crew repor ted t h a t o p e r a t i o n of t h e proper swi tchesThe buses were manual ly deac t iva ted ,

This anomaly i s d e s c r i b e d i n s e c t i o n 14 .1 .6 .



7-2

7.2.2 Fuel Cells

The f u e l c e l l s were a c t i v a t e d 48 h o u r s p r i o r t o l a u n c h , c o n d i t i o n e df o r 4 h o u r s , a n d c o n fi g u re d w i t h f u e l c e l l 2 on t h e l i n e s u p p l y i n g a20-ampere load as r e q u i r e d i n t h e c ountdown p r o c e d u re . F u e l c e l l s 1 and3 remained on op en c i r c u i t u n t i l 5 h ou rs p r i o r t o l a un ch . A t l a u n c h ,f u e l c e l l 1 w a s on main bus A w i t h fuel c e l l 2 , and f u e l c e l l 3 w a s on

main bus B. T h i s c o n f i g u r a t i o n w a s m a in t ai n ed th r ou g ho u t t h e f l i g h t .I n i t i a l l y , t h e l oa d v ar ia nc e was approximately 5 amperes , but i t s t ab i -l i z e d t o 3 o r 4 amperes early i n t h e f l i g h t .o f o t h er f l i g h t s .

Th is i s normal and ty p ic a l

A l l f u e l c e l l pa ra me te rs remained with in normal oper a t in g l i m i t sa nd a gr e e d w i t h p r e d i c t e d f l i g h t v a l u e s .condenser-ex i t t empera tu re exh ib i t ed a p e r i o d i c f l u c t u a t i o n ab ou t ev er y6 minutes th roughout t h e f l i g h t . Th is ze ro-grav i ty phenomenon w a s s i m i -l a r t o tha t observed on all o t h e r f l i g h t s a nd h as n o e f f e c t o n f u e l c e l lperformance ( r e f . 6 ) .

As e xp ec te d, t h e f u e l c e l l 1

"he f u e l c e l l s s u p p l i e d 435 kW-h o f en er gy a t an average cur ren t o f

2 3 amperes p e r f u e l c e l l and a m e a n b us v o l t a g e o f 2 9 v o l t s d u r i n g t h emiss ion .

7.2.3 B a t t e r i e s

The comand and service module entry and p y r o t ec h n i c b a t t e r i e s p e r-formed normal ly. En try b a t t e r i e s A and B were both charged once a t t h el au n ch s i t e and f i v e times d u r i n g f l i g h t wi th nomina l charg ing perform-ance . Load sha r ing and vo l t age de l ive r y were s a t i s f a c t o r y d u r i n g e a c hof t h e s e r v i c e p r o p u l s i o n f i r i n g s .charged at e n t r y.

T h e b a t t e r i e s were e s s e n t i a l l y f u l l y

7. 3 CRYOGENIC STORAGE

C ry og en ics were s a t i s f a c t o r i l y s u p p li e d t o t h e f u e l c e l l s an d t oth e env i ronmenta l con t ro l system th roughout t h e miss ion . The conf igura -t i o n c h a n g e s made as a r e s u l t o f t h e Ap ol lo 1 3 o xy ge n t a n k f a i l u r e aredescr ibed in appendix A. A supplementa l r epor t g iv ing d e t a i l s of sys-t e m performance w i l l be i s s u e d a t a l a t e r da te (appendix E ) .

Dur ing pre f l igh t checkout o f the oxygen sys tem, the s ing le - sea t

During f l i g h t , t h i sch eck v a l v e f o r t an k 2 w a s found t o h a v e f a i l e d i n t h e o p en p o s i t i o n andwas r e p l a c e d w i t h an in - l ine double -sea t va lve .va lve a l lowed gas l eakage i n to t a nk 2 f rom tank 3 . "h e purpose of t h i s



7-3

v a l v e i s p r im a r il y t o i s o l a t e t an k 2 f rom th e remainder o f t h e sys tems h o u l d t a n k 2 f a i l . Thus, i t w a s q u a l i f i e d a t a r e v e r s e d i f f e r e n t i a lp r e s s u r e o f 60 p s i d . T h i s i s s i g n i f i c a n t l y h i g h e r t h a n t h a t n o r m a l l ye x p e r i e n ce d d u r i n g a f l ig h t . Tes t s have been conducted t o c h a r a c t e r i z et h e n a t u r e o f t h e c he ck v a lv e l e ak a ge a t l o w p r e s s u r e d i f f e r e n t i a l a n dshow t h a t t h i s s i t u a t i o n i s n o t d e t r i m e n t a l t o o p e r a t i o n u n d e r a bn or ma l

asw e l l

asnormal condi t ions .

Two f lo w t e s t s o n t h e oxygen sy s te m w er e c o n d u ct ed d u r i n g f l i g h t .One w a s t o d em o ns tr at e t h e c a p a b i l i t y o f t h e s ys te m t o s u p p or t a d d i t i o n a lf lo w r e qu i re m en t s f o r e x t r a v e h i c u l a r a c t i v i t i e s . The o t h e r w a s t o d ete r-m i n e t h e h e a t e r t e m p e r a t u r e w h i l e o p e r a t i n g w i t h t h e o q g e n d e ns it y l e s st h a n 20 p e r c e n t .resu l t s were obta ined a l though t e s t p rocedures were modi f ied because o ft i m e co ns tr ai nt s . The oxygen system i s c a p ab l e o f s u p p o r t i n g t h e a n t i c -i p a t e d r e q u ir e m e nt s f o r Ap o ll o 15 and sub sequ ent mi ss io ns . The low-d e n s i t y f l o w t e s t i n d i c a t e d t h a t t h e oxy gen s ys te m can p r o v i d e r e q u i r e df l o w - r a t e s a t l o w d e n s i t i e s a n d t h e d a t a o b t a i n e d p r o v i d e s f o r a morea c c u r a t e a s s es s me n t o f h e a t e r o p e r a t i n g t e m p e r a t u r e .

The i n t e n t o f t h e se two t e s t s w a s met and favorable

Consumable q u a n t i t i e s i n t h e c r y o ge n i c s t o r a g e s y s t em a r e d i s c u s s e di n s e c t i o n 7 . 10 .3 .

7.4 COMMUNICATIONS EQUIPMENT

The communicat ions sys tem sa t i s f ac to r i ly suppor ted t h e miss ion ex-c e p t f o r t h e f o l l o wi n g d e s c r ib e d c o n di t i o n s.

The high-gain antenna f a i l e d t o a c q u i r e an d t r a c k p r o p e r l y a t v a r i o u stimes dur in g th e miss ion . The p roblems occur red dur in g t h e acqu is i t io no f s i g n a l r a t h e r t ha n a f t e r a c q u i s i t i o n . I n t h i s r e g a r d , t h e p ro bl em i sd i f f e r e n t f r o m t h o s e exper ienced dur ing Apollo 1 2 and 13 where the high-g a in an te nn a l o s t l o c k o r f a i l e d t o t r a c k a f t e r a c q u i s i t i o n . T h i s i sd i sc u s se d i n f u r t h e r d e t a i l i n s e c t io n 1 4 .1 . 2 .

From j u s t p r i o r t o lunar l i f t - o f f t hr ou gh t e r m i n a l p ha se i n i t i a t i o n ,t h e VHF system performance w a s ma rg ina l. Voice communications were weaka n d n o i s y , a nd t h e VHF r a n g in g per for man ce w a s e r r a t i c a n d e r r o n e o u s .The voi ce conhun icati 'ons problem i s n ot r e l a t e d t o t h e VHF problems ex-perienced on previous missions where they were determined t o be proced-u r a l e r ro rs . Swi tch ing an tennas i n th e command and se rv ic e module ande l i m i n a t i o n o f t h e r a n gi n g s i g n a l d i d n o t c l e a r up t h e problems.

problems are be l i eve d t o have been caused by equ ipment mal func t ion , bu tt h e s o u r c e h as n o t b ee n i s o l a t e d t o a par t i cu la r component o f t h e t o t a ls y s t e m . S e c t i o n 14 .1 .4 c o n t a i n s a d e t a i l e d d i s c u s s i o n o f t h i s a n o m a l y.

The



7- 4

7 .5 INSTRUMENTATION

The ins t rum enta t ion sys tem func t ioned normal ly th roughout th e miss ione x c e p t f o r t h e l o s s of t h e r e a c t i o n c o n t r o l s y st em q ua d B oxidizer mani-f o ld pr es sur e measurement d uring s epa rat ion of t h e command and se rv ic emodule f rom th e launch veh ic le . The mos t p robab le cause o f t h e f a i lu re

w a s a b r e ak o f t h e s i g n a l o r power l e a d s i n i t i a t e d by t h e p y r o t ec h n i cs ho ck a s s o c i a t e d w i th t h e s p a c e c r a f t / la u n c h v e h i c l e a d a p t e r panel separa -t i o n . S in ce t h i s i s t h e only f a i l u r e of f o u r m ea su re me nt s o f t h i s t y p eon e ac h o f e i g h t f l i g h t s , t h e p y r o t e c h n i c s ho ck i s not cons idered a prob-l e m for normal e lements of t h e i n s t r u m e n t a t i o n c i r c u i t . F u r t h e r , r ed un -d a n t m ea su re me nts a r e a v a i l a b l e t o p e r mi t d e t e r m i n a ti o n o f t h e r e q u i r e dda ta . Consequen tly, no co r re c t i ve ac t io n i s r e q u i r e d .

7 .6 GUIDANCE, NAVIGATION, AND CONTROL

A t t i t u d e c o n t r o l w a s nomina l th roughout the miss ion inc lud ing a l lp e r i o d s o f p a s s i v e t h er m a l c o n t r o l , c i s l u n a r n a v i g a t i o n , as w e l l asphotography and landmark t ra ck i ng f rom lu na r o rb i t . The s t a b i l i t y oft h e i n e r t i a l m easurement u n i t e r r o r p ar am e te rs w a s exc e l l en t . The on lyanomaly i n th e gu idance , nav iga t ion and con t ro l sys tems w a s f a i l u r e o ft h e e n t r y m o n i t o r s y s t e m O.OSg l i g h t t o i l l um ina te . Th is i s d i s c u s s e di n s e c ti o n 14.1.5.

Because of inclement weather, the l i f t - o f f w a s d el ay ed f o r t h e f i r s tt ime i n th e Apollo program. This r e q u ir e d t h e f l i g h t a zim uth t o b e ch an gedfrom 72 degrees t o 75.56 d e g re e s a n d t h e p l a t f o r m t o b e r e a l i g n e d a cc or d-i n g l y. A comparison of command and service module and s-IVB n a v i g a t i o nd a t a i n d i c a t e d s a t i s f a c t o r y p er fo rm an ce d u r i n g t h e l a u n c h p ha s e.t i o n e r r o r s wer e p l u s 7 . 02 , p l u s 6 1 .0 2, a nd min us 7 . 50 f t / s e c i n t h e X ,Y , and Z a x e s , r e s p e c t i v e l y . T he se e r r o r s were c om pa ra bl e t o t h o s e ob-se rved on o th er Apollo l aunches . The on ly s i gn i f i c an t e r ro r w a s i n t h eY- a x i s ve loc i ty caused by a pre launch az imuth a l ignment e r ro r o f 0.14 de-gr ee due t o one-sigma gyrocompassing ina ccu rac ies . Table 7-1 i s a sum-m a r y o f p r e f l i g h t i n e r t i a l measurement unit error parameters a f t e r i t sin s ta l la t io n i n t h e coxmuand module.w a s performed at approximately 29 hours . The th r ee accelerom eter biaseswere updated t o minus 0.32, p l u s 0.12 and minus 0.13 cm/sec2, and t h eX-gyro n u l l b ia s d r i f t w a s u p da te d t o p l u s 0.4 meru ( m i l l i e a r t h - r a t eu n i t s 1.

I n s e r -

An u pd ate t o t h e i n e r t i a l p ar am et er s

The f i r s t p l at f or m r ea li gn me nt w a s performed a f t e r i n s e r t i o n a n d

agreed w i t h t h e p r e d i c t e d a li gn me nt e r r o r s due t o p r e la u n ch a z i m t he r r o r s .o f t h e p l a t f o r m r e a l ig n m e n t s.

Table 7-11 i s 8 summary o f s i g n i f i c a n t p a ra m e te r s d u r i n g e ac h



7- 5

Sample Standud l o . of Countdown Fl ig htError mean deviation ramplea value load

TABLE 7-1.- INERTIAL COMPONENTPREFLIGHT HISTORY - COMMANDMODULE

In f l igh tperformmce

x . c d e f a ct o r e r r o r , p p . . . . . .M U , d r e c . . . . . . . . . . .

Y . ca le factor error. p p . . . . . .2B i u . oI/rec . . . . . . . . . . .

2 - S c d e fact or er ro r, ppm . . . . . .B i u . m / r e c . . . . . . . . . . .

-144

-0.23

-441

0.05

-218

-0.29

X - lull b i M d r i f t , Y N . . . . . . .Aceeleratian d r i f t . apin reference

Acceleration drift, input

u i r .meru/g . . . . . . . . . .u i r , meru/g . . . . . . . . . .

Y - l u l l b i M d r i f t , .CN . . . . . .Acceleration drift, apin reference

Acceleration d r i f t , input

U i S . m c N / g . * - . .d.. meru/g . . . . . . . . . .

2 - l u l l b i u drift. meru . . . . . . .u i r . meru/g . . . . . . . . . .u i r , meruIg . . . . . . . . . .

Acceleration d ri ft , ,spin reference

Acceleration drift , nput

580.13

49

0.07

L9

0.07 '

0 9

3.0

1. 7

-3.4

3.2

-9.9

1 .6

-3.1

4 3 . 8-

88

88

88

2.0

1.5

0.8

1.5

k.5

0 . 9

1 .0

6.4

Gyror copea

77-p-8

8

8

8

16

8

8

8

-0.31 -0.23

-310

-0.18 -0.29

1.8

4 .9

-1 .6

-4.2

3.8

-9.7

2.5

-2 .4

54.1

-2.5

1.0

0 o

-3 .L

3.0

-5 .O

1. 6

-3 .9

LO .o-

--0 .34

-0.09

--0.18

% l i g h t perfo-ce aver- before update VM minus 2 . 0 .

Sp ace cra f t dynamics during sepa rat ion from t h e S-IVB were very smal l .Sp ac ec ra ft dynamics dur ing each docking attempt were small and comparablet o t ho se seen on previou s Apollo miss ions . Figure 7-1 i s a t i m e h i s t o r yof s i g n i f i c a n t c o n t r o l s y st em p ar am e te rs d u r i n g each docking at tempt .

Performance during each of t h e s e v e n s e r v i c e p r o p u l s i o n s y s t e m ma-neuvers was nominal.on ly a f t e r t h e c i r c u l a r i z a t i o n and t r a n s e a r t h i n j e c t i o n maneuvers.

Table 7-111 i s a summary o f s i g n i f i c a n t c o n t r o l s ys te m p a ra m et er s f o reach of the maneuvers. The second midcourse correct ion was accomplishedw i t h a minimum-impulse s er v ic e pro pul sion system maneuver i n o rd er t o

Trimming o f r e s i d u a l v e l o c i t y e r r o r s w a s performed



7-6

Y

Yr(

a

4.

s

i

K?[p!

I

c)

1

E

I

I

N

1..

irl



7-7

o' 9 9? , F Iw m

J I On

*W4-

m nn n ~N ~ O \e " ?. . .

%?IN. ..m mf t 4

-t-t-

n d w? ' 9 ?" e : !m m o3 %I-t-r l d 3

-r l m N? ? ?2 w.. .. ..d d 0

lnln0 0 r(

7 ! 7 !

-t-m 4

4 T"!N ~ O? - '%

7!7!3%

0-40

r-

0 0 0

..,0 0 0+ $l n N 1. . \ <

;\

a d o

o o n+ I +I

N ? ?

N N ?0 0 0

+ + +

W N ot - m w N N

'91 ? 'u V" '9'90 0 N d 0 0 O r l

I + I + I I I I

? ? 1 ?+ + I N

W O t m W W N V I

0 0 N d 0 0 0 0I + I + I + I I

' 9 N ? ? ' 9 ? ' 9 9N N N

4 4 0+ I 1

f.??n w mN N ?o o m+ I I

W t . N N0 0 0 4+ + + +. .

n t N d . - I N A t -

0 0 4 4 0 0 0 0I + I + I + I +

? ? 4'9 ? ? ? ?mm mN ' 9 "r l o o+ I 1

!;0 0 01 1

V I 2

Z o d d+ +

w m oI ? ?0 0 0 l l

w m o

o o n+ I +

1 1 9

f

0 0 09

l n N d

00 .4 l l

I N ?

Po

8h

hu0aU

ee

.3

E. i Z 2 Bz

m o ~N N ?0 0 0+ + +

w w

0 0 0+ +

? ? ?

0 0 0

'9: N0 0 0 0+ + I

t -w m m t w m n? N f.5 ? ? '9'90 0 0 0 4 0 4 0+ I + + + I + I

? ?0 0 0 0+ I

O'N?A o m

m m mI + +..

4 0 m+ +. . .

N n

0 0 0 0 e 0 0+ I + I + I

?3 ? $ 3 0 ' 11 v \0 0 0 0+ +

o m 0 1 t - o m o w? ? I f . ? ? ? N

2 7 $ 4 $ 40 I

1 ? 10 0 0 0+ I +



7-8 - 4

NASA-S-71-1632

T-X O f f

- L O f fT o r r- L O f f

+X,+P On-X,+P On+x,-P On-X, -P On

L O f f

X O f f- L O f f

l - O f f

+X, +Y On-X,+Y On+X, -Y On

-X, -Y On

F

L-

A A

V '

A.

+Z,+R On

+Z, -R On-Z, -R On

1 0 ,X O f f

+Y,+R On-Y,+R On+Y, -R O n 1-Y, -R O n 1 ff

Off

5

07)

-0

L

eL

W

G OJe

e.-m

rVzn

-55

07U

L.

eW O

La2

'03

cc .m

2>

' -5

1

uwl. - T,a

-0

2 - 0ErV

c.-n

-1

1

WWl1

g:

E

-0

a- 0c

-11

I I

3: 55: 13:50 3: 14:00 3:14:10

Figure 7-1. - Time historyof control system parameters during mu



I 1 4 1 1

3: 14:50 3:15:00 3:16:10: 14:20 3: 14: 30 3: 14:40

Time, hr: min:sec

lti ple dock ing attempts.



7 - 8 e

I I I

1 16: 20 3: 16: 30 3:16:40 3:16:50

IB

II

i

r n

Ya w attitude error

3:23:35 3:23:45 3: 23: 55



7 - 7 4

4:32:40

I I I I

4:56:40 4: 56: 0 4: 57:00 4:57: 10 4:57:20

Time, hr:min:sec



7-9 c

I 1 1 '.. 7 ,, .~ ,. I - . - _ . . .. . -.

. - .._ .. . _ _ .~ _.,_ .

4: 57: 30 4:57:4O 4:57:50 4: 58: 00 4: 58: 10 4:58:M

Figure 7-1. Time history of contr ol system parameters du rin g multiple docking attempts.



7-10

c on se rv e r e a c t i o n c o n t r o l p r o p e l l a n t . T h i s w a s t h e f i r s t s e r v ic e pro-pu ls io n sy stem minimum-impulse maneuver perfo rmed d ur in g a l u n a r m i s s i o n .The t h i r d mi dc ou rs e c o r r e c t i o n w a s p er fo rm ed w i th t h e r e a c t i o n c o n t r o lsystem.

D ur in g t h e t r a n s l u n a r p h a s e, a se r i es of s tar-h orizon measurementswere ta k en t o e s t a b l i s h t h e p r e c i s e l o c a t i o n o f t h e e a r t h ho r iz on . T hisw a s done i n p r e p a r a t i o n f o r a c i s l u n a r n a v i g at i o n e x e r c i s e t o b e p er fo rm edd u r i n g t h e t r a n s e a r t h p h a s e .

The command and s e r v i c e module com bina tion was s e p a r a t e d f ro m t h elu na r module a f t e r t h e descen t or b i t i ns er t i on maneuver. Command andse rv ic e module ci r cu la r i za t i o n and plane-change maneuvers were th en per-form ed, and t h e Command Module P i l o t accomplished a s e r i e s o f p h o t o g r a p h i cand landmark t r ac k i ng opera t io ns . For t h e f i r s t t i m e , r a t e - a i d e d o p t i c sw ere a v a i l a b l e t o a s s i s t t h e c rew i n making o p t i c a l s i g h t i n g s .

The s e x t a n t a n d VHF ranging d a t a were u se d t o t r a c k t h e l u n a r mod-u l e a f t e r t h e v e r n i e r a d ju st m en t maneuver f o l l o w in g a s c e n t fro m t h e l u n a rs u r f a c e . U na cc ep ta bl e VHF r a ng i n g d a t a w er e r e c e i v e d i n t h e i n t e r v a l be-tween l un ar module i ns e r t i on and t h e t e r m in a l p h a s e i n i t i a t i o n man eu ver ;however, th e d a t a rece ived dur ing th e f in a l phase o f rendezvous were good.Fo r a d e t a i l e d d i s c u s s i o n o f r en de zv ou s, see s e c t i o n 6 . 2. 3.c u s s i o n o f t h e VHF rangin g anomaly, see se ct io n 1 4 . 1 . 4 .

For a d i s -

Only one midcourse c o r r e c t i o n w a s r e qu i re d on t h e r e tu r n t r i p t om eet t h e e n t r y i n t e r f a c e c o n d i t i o n s . C i s l u n ar n a v i g a t i o n w a s performedd u r in g t h e t r a n s e a r t h p ha se t o s i mu l at e r e t u r n i n g t o e a r t h w i th no com-munications. Accuracy of the onboard nav iga t ion t echn iques w a s demon-

s t r a te d bu t t h e c rew commented th a t the compute r/crew op era t io na l in te r-f a c e could be improved by incorporat ing a r ec yc le f e a t u r e i n t h e c i s l u n a rn a v i g a t i o n a l s g h t i ng program.

The command module w a s sep ara ted from th e s e r v i ce module a t 215:32:42and t h e normal pitch-down di stu rb an ce w a s observed. The en tr y monitorsys tem 0 .05g l i g h t d i d n o t i l l u m i n a t e w i th i n t h e a ll ow ed 3 s e c o n d s a f t e rt h e p r e d ic t ed t i m e f o r 0 .0 5g . The crew s t a r t e d t h e system manually ac-c or di ng t o t h e c h e c k l i st . R ef er t o s e c t io n 14.1.5 f o r f u r t h e r d i s c u s s i o nof t h i s anomaly. Table 7 - I V i s a summary of en t r y monito r sys tem nu l l -b i a s t e s t s p e rf or me d d u r i n g t h e mi ss io n .performance were excel lent .

A c c e l e r o m e t e r s t a b i l i t y and

The primary guidance syste m guided t h e command module t o a l and ingat 27 degrees 0 minutes 45 seconds sou th l a t i tude and 172 degrees 39 min-utes 30 seconds west longi tude, which i s 0.62 m i l e f r o m t h e t a rg e t e dl a nd i ng p o i n t .



7-11

' h a t s

*in

Btrrmmitorwstarradlnl.t s ta r t O f t a t . n 1 a c

htw a t o r m t n redir

a t end of tat. ft/sac

Diffonotial wlacity b i n .R l a r "

lull b i n . r t / a r 2

TABLE7-1v.- RESUEIS OF ENTRY MONITOR SYSTEM NULL BIAS TESTS

1 2 3 1 5 6 7 8 9

01:50:00 09:34:50 29:11:20 58:28:00 75:59:00 79:45:00 84:31:00 118:20:cO 165:15:00

-100 -100 -100 -100 -100 -100 -100 -100 -100

9 9 . 5 -99.L -99.6 -98.9 -90.L -98.5 -99.4 -98.5 -9.0

W.5 40.6 #.L *1.1 * 1. 6 i 1 . 5 a . 6 * 1. 5 * l. O

4O.005 M.006 t0.004 W.011 a 0 1 6 M.015 KI .006 KI.015 +0.010

.treh test duratim is 100 a w e d . .HColst rg is posit ive b l u .

7.7 REACTION CONTROL SYSTEm

7.7.1 Service Module

Performance of t h e se rv ice module reac t io n c on t ro l w a s normalt h ro u g ho u t t h e m i s s io n . A l l t e lemet ry paramete rs s t ay ed wi th in nomina ll imits t h ro u g ho u t t h e m is s io n w i t h t h e e x c e p t i o n o f t h e quad B o x i d i z e rmani fo ld p ressure . This measurement w a s l o s t when t h e command andse rv ic e module se para ted f rom th e S-IVB.mani fo ld p ressures w e r e used t o ver i fy proper sys tem opera t ion .p r o p e l l a n t c on su mp ti on f o r t h e mission w a s 1 0 2 p oun ds l e s s t h a n p r e d i c t e d ;however, p r op e l l an t consumption dur ing t ra ns po s i t io n , dock ing and ex t r ac -t i o n was about 60 gounds more than p lanned because o f the add i t iona l m a-n e uv er in g a s s o c i a t e d w i th t h e d o ck in g d i f f i c u l t i e s . The prope l lan t m a r -g i n d e f i c i e n c y was r e co v e re d p r i o r t o l u n a r o r b i t i n s e r t i o n , and no min almargins ex is te d dur ing th e remainder o f t h e miss ion . Consumables in f or-mation i s c o n t ai n e d i n s e c t i o n 7 . 10 . 2.

The quad B h e l i u n a n d f u e lTo t a l

7.7.2 Comnand Module

The command module reac t ion co ntr ol systems performed s a t i s f a c t o r i l y .Both systems 1 an d 2 w e r e a c t i v a t e d d u r i n g t h e command module/servicemodule sep ara t io n sequence. Sho rt ly a f t e r s e p a r a t i o n , s ys te m 2 was d i s -abled and system 1 w a s u s e d f o r t h e r em a in d er o f e n t r y.da ta i nd ic a t ed nomina l system performance th roughout t h e miss ion .s m a b l e s i n fo r m at i on is c o n ta i ne d i n s e c t i o n 7 .1 0. 2.

All t e l e m e t r yCon-



7-12

7 .8 SERVICE PROPULSION SYSTEM

Se rv ice p ropuls ion sys tem performance w a s s a t i s f a c t o r y b a se d on t h es t eady- s t a t e performance during a l l f i r i n g s . T h e steady-state p r e s s u r ed a t a , g ag in g s ys te m d a t a , and v e l o c i t i e s g a i n e d i n d i c a t e d e s s e n t i a l l ynominal performance, The engine t rans ien t pe r fo rmance dur ing a l l s t a r t s

and shutdowns w a s s a t i s f a c t o r y.a n a l y s i s i n d i c a t e d c omb ustio n i n s t a b i l i t y o r t h e c au s e o f t h e s l i g h t humo r b uz zi ng n o i s e r e p o r te d by t h e p i l o t ( r e f . 9.13).

Nothing i n t h e f l i g h t d a ta o r p o s t f l i g h t

T h e p r o p e l l a n t u t i l i z a t i o n a n d g a g i n g s y s t e m p r o v i d e d n e a r - i d e a lp r o p e ll a n t u t i l i z a t i o n .j e c t io n f i r i n g w a s repor te d by th e crew t o be 40 lbm, decreas e , whichagrees w e l l wi th t e lemet ry va lues .

The unbalance a t t h e end of t h e t r a n s e a r t h i n -

During t h e Apollo 9 , 1 0 , 11, and 12 m i s s io n s , t h e s e r v i c e p r o p ul s io nsystem xiixture r a t i o w a s l e s s t h an e x p ec te d, b as ed on s t a t i c f i r i n g d a t a .The p r e d i c t e d f l i g h t m i xt ur e r a t i o f o r t h i s m i ss io n w a s based on previousf l i g h t d a t a t o more c l o s e l y s i m u la t e t h e ex pe ct ed mi xt ur e r a t i o . Toa ch ie v e t h e p r e d i c t e d m ix tu r e r a t i o a t t h e end o f t h e m i s si o n , t h e m ajo r-i t y o f t h e m is s io n would h av e t o be flown w i t h t h e p r o pe l l a nt u t i l i z a t i o nv a lv e i n t h e i n cr e as e p o s i t i o n . C on seq uen tly, t h e p r o p e l l a n t u t i l i z a t i o nvalve. w a s i n t h e i n c r e a s e p o s i t i o n a t launch.

F igure 7-2 shows t h e v a r i a n c e i n f u e l a nd o x i d i z e r r em a in in g atany i n s t a n t d u r in g t h e lunar o r b i t i n s e r t i o n a nd t r a n s e a r t h i n j e c t i o nf i r i n g s , as computed from t h e t e le m et r y d a t a , and t h e p r o p e l l a n t u t i l i z a -t i o n valve movements made by t h e crew. The p r e f l ig h t expected val uesa n d p r o p e l l a n t u t i l i z a t i o n m o v e m e n t s are a l s o shown. "he s e r v i c e p ro -p u l s i o n s y s te m p r o p e l l a n t u sa g e f o r t h e mi s si o n i s d i s c u ss e d i n s ec -t i o n 7.10.1.

7.9 ENVIRONMENTAL CONTROL AND CREWSTATION

The env i ronmenta l con t ro l sys tem per formed sa t i s fac to r i ly and pro-v ided a comfor tab le envi ronment f o r t h e crew and adequa te the rmal con t ro lo f t h e sp ace cra f t equ ipment . The crew s t a t io n equ ipment a l s o sa t i s f ac -t o r i l y s u p p o r t e d t h e f l i g h t .

The environmental control system w a s u se d i n c o n ju n c ti o n w i t h t h ecryogen ic oxygen system t o demonst rate t h e c ap ab i l i ty o f p rov id ing oxygena t high f low r a t e s such as t h o s e t h a t w i l l be r e q u i r e d d u r i n g e x t r a v e -

h i c u l a r o p e r a t i o n s on f u t u r e m i ss i on s . A modified hatch overboard dumpnozz le wi th a c a l ib r a te d o r i f i c e w a s us ed t o o b t a in t h e d e s i r e d flow r a t e .The emergency cab in p ressu re re gu la to r main ta ined th e cab in p r ess ur e a t



7-13

E:0. .

%W

WIn

ik4J

alIn

ME:

.ri

k?a

W

kalN

.+

a.dX

0

I

cuI

P-

alk



7-14

approximately 4.45 p s i a .t e r m i n a t e d a f t e r 70 minutes when th e 100-p si ow ge n mani fold pressured ec ay ed t o a bo u t 10 p s i . T h i s w a s caused by open ing of t h e u r in e over-board dump valve which caused an oxygen demand i n e.xcess of tha t .whicht h e o x y g e n r e s t r i c t o r s were capab le o f p rov id ing . However, s u ff i c ie n td a t a w e r e o b t a i n e d d u r i n g t h e t e s t t o d e t er m i ne t h e h ig h- fl ow c a p a b i l i t yof the cryogenic oxygen system.

The t e s t , s c h e d u l ed t o l a s t 2-1/2 hours , w a s

(Also s e e s e c t i o n 7.3 . )

I n f l i g h t cab in p ress ure decay measurements were made f o r th e f i r s tt i m e d u r i n g most o f t h e c rew s l e e p p e r i o d s t o d e te r m in e more p r e c i s e l y

t h e f l i g h t l ea ka ge was approx imate ly 0 .03 lb /h r.i n d es ig n l i m i t s .

t h e ca b in l ea k ag e d u r in g f l i g h t . P r e li m in a r y e s t i m a t e s i n d i c a t e t h a tT h is l e a k r a t e i s with-

P a r t i a l r e p r e s s u r i z a t i o n o f t h e oxygen s t o r a g e b o t t l e s w a s r e q u i r e dt h r e e t i me s i n a d d i ti o n t o t h e n ormal r e p r e s s u r i z a t i o n s d u r i n g t h e m i s -s i on . Th is p rob lem i s d i s c u s s e d i n s e c t i o n 14.1.8.

The crew repor ted se ve ra l ins tan ces o f u r ine dump nozz le b lockage .Apparen tly t h e dump nozzl e w a s c lo gg ed w i t h f r o z e n u r i n e p a r t i c l e s . Theb l oc k ag e c l e a r e d i n a l l i n s t a n c e s w h e n t h e s p a c e c r a f t w a s o r i e n t e d sot h a t t h e n o z z l e w a s i n t h e su n . T h i s ano maly i s d i sc u s se d f u r t h e r i ns e c t i o n 14.1.3.

I n t e r m i t t e n t communications dropouts were ex pe ri en ce d by t h e Com-mander a t 29 ho urs . The problem w a s corrected when the Commander'sc o n s t a n t wear g a r m e n t e l e c t r i c a l a d a p t e r w a s re pl ac ed . The anomaly i sd i s c u ss e d f u r t h e r i n s e c t i o n 1 4 . 3 . 4 .

A vacuum cleaner assembly and cabin fan f i l t e r , u sed f o r t h e f i r s tt i m e , a long wi th t h e normal decon taminat ion p rocedures e l im ina ted p rac -t i c a l l y a l l o f t h e o b j e c ti o n a b l e d u s t s u ch as t h a t p re se n t a f t e r t h e

Apollo 1 2 l u n a r d o c k i n g .a f t e r lunar docking. The fans were opera te d f o r approx imately 4 h o u r s

Sodium n i t ra te w a s a dd ed t o t h e w a t e r b u f f e r am pules t o r ed u ce s y s-tem c o r r o s i o n . T h i s a d d i t i o n a l s o allowed a r e d u c t i o n i n t h e c o n c e n t r a -t i o n o f c h l o r i n e i n t h e c h l o r i n e am pu le s. No o b j e c t i o n a b l e t a s t e w a sn ot ed i n t h e water.b u ff e r am pu le s i n t o t h e i n j e c t o r . The am pules an d i n j e c t o r are b e i n gt e s t e d t o e s t a b l i s h t h e c au se o f t h e p ro ble m.t h a t t h e fo od p r e p a ra t i o n u n i t l ea ke d s l i g h t l y a f t e r d i s p e n s i n g h o t water.This problem i s d is cu ss ed f u r t h e r i n s e c t i o n 14.1 .7 .

The crew r e p o r t e d some d i f f i c u l t y i n i n s e r t i n g t h e

The crew a l s o i n d i c a t e d



7-15

7.10 CONSUMABLES

"he command and service module consumable usage durin g t h e Apollo 1 4mission w a s w e l l w i t h in t h e r e d l i n e l i m i t s a n d, i n a l l sys tems , d i f f e r e dno more than 5 p e r c e n t from t h e p r e d i c t e d l i m i t s .

7 . 10 . 1 S e r v i c e P r o p u l s i on P r o p e l l a n t

Serv ice p ropuls ion p rope l lan t load ings and consumpt ion va lues a rel i s t e d i n t h e f ol lo w in g t a b l e .sys tem read ings and measured de n s i t i e s p r io r t o l i f t - o f f .

The loadings w e r e c a l c u l a t e d f ro m g a g in g

~

Con d i ti on

Loaded

Consumed

Remaining a t command module/se rv ic e module s epara t i on

Usable at command module/se rv ic e module separa t ion

F'ue 1

1 5 695.2

14 953.2

742

596

P r o p e l l a n t , l b

Oxi d i z e r

25 061

23 900

1 161

866

To t a1

40 756.2

38 853.2

1 9 0 3

1 462

7.10.2 React ion Control System Propel lants

S e r v i c e mo du le.- The p r o p e l l a n t u t i l i z a t i o n a nd l o a d i n g da t a f o rt h e s e r v i c e module r e a c t i o n c o n t r o l s y st em were as shown i n t h e fol low-i n g t a b l e . Consumption w a s ca l cu la t ed from te lemet e red he lium tank pres -sure h i s t o r i e s a n d were based on pressure, volume, and temperature re la-t i o n s h i p s .



7-16

110.110 9 99110.4109 7

440.1

i250

I P r o p e l l a n t , l bCondition

Lo ad e dQuad AQuad B

Quad CQuad D

To t a l

%sable loaded

Consumed

Remaining a t command module/s e r v i ce module s e p a r a t i o n

% s a b l e l o a d e d p r o p e l l a n t i s the amount

Oxid ize r

225.3225.2

226.5223.5

900.5

476

To t a l

335.4335.1

336.9333.2

1340.6

1233

726

507

Loaded minus t h e- -amount trapped and w i t h c o r r e c t i o n s made f o r g a gi ng e r r o r s .

Command module.- The lo ad in g and u t i l i z a t i o n o f command module re-a c t i o n c o n t r o l s ys te m p r o p e l l a n t w a s as follows. Consumption w a s calcu-l a t e d f rom pre ssu re , volume and tempera tu re re la t i on sh ip s .

I Con di t i on

b a d e dSystem 1system 2

To t a l

% sa b l e l o a d e d

ConsumedSystem 1System 2I

To t a l

P r o p e l l a n t , l b

Fuel

44.344.5

80.0

Oxi d i z e r

78.6

156.7

78.1

Tot a1

122.9122.6

245 5

210 o

414

45

% s a b l e l o a de d p r o p e l l a n t i s t h e amount load ed minus t h e

b E s ti m a te d q u a n t i t y b a s e d on he l ium source pressure p r o f i l eamount t r app ed and wi th co r r ec t io ns made f o r gag ing e r r o r s .

during e n t r y.



7-17

7.10.3 Cryogenics

The t o t a l c ryogen ic hydrogen and oltygen qu an t i t i e s av a i l ab le a t lift-off and consumed were as fo l lows . Consmpt ion va lue s were b a s e d on quan-t i t y d a t a t r a n s m i t t e d b y telemetry.

Condit ion

Avai lab le a t l i f t - o f f

Tank 1Tank 2Tank 3

To t a l

Cons me d

Tank 1Tank 2Tank 3

To t a l

Remaining a t command module/se rv ic e module sep ara t ion

Tank 1Tank 2Tank 3

To t a l

~~ ~

Hydrogen, l b

Actual

26.9726 55-

53.52

19.1219.14

-

38.26

7.857 . 4 1-

15.26

%dated t o l i f t - o f f v a l u e s .

Planned

a53 52

38.62

7.877 . 0 3-

14.90

Oxygen, l b

Actual

320.2318.9197 .2

836.3

11 9 . 3113 .8163.4

396.5

200 .g205.1

33.8

439.8

~~

Planned

'836.3

412 .1

204.2195.2

24 .8

424.2



7-18

7.10 .4 Wat e r

The water q u a n t i t i e s l o ad e d , p ro d uc ed , an d e x p e l l e d d u ri n g t h e mis-sion are shown i n t h e f o l l o w i n g t a b l e .

Condi t ion

Loaded ( a t l i f t - o f f )

Po tab le water t a n kWaste water t a n k

P r o d u c e d i n f l i g h t

F u e l c e l l sLi thium hydroxide react ionMetabol ic

Dumped overboard

Waste tank dumpingUrine and f l u s h i n g

Eva por ated up t o command module/s e r v i c e module s e p a r a t i o n

Remaining onboard a t command module /s e r v i c e module s e p a r a t i o n

Potable water t ankWaste water t a n k

? *L

?A L- Y

Q u a n t i t y, l b

28.532.4

342.321.021.0

236.9133.2

9 o

29 736.4

. -i



8- 1

8.0 LUNARMODULEPERFORMANCE

8.1 STRUCTURAL ANDMECHANICALSYSTEm

Lunar module s t ruc tu ra l loads were w i t h i n d es i g n v a lu e s f o r a l lp h as es o f t h e m is s io n . T h e s t r u c t u r a l a s s e s s m e n t w a s based on guidanceand co nt ro l dat a , cabin press ure measurements , comand module acce lera -t i o n d at a , photograph s, and crew comments.

Based on measured command module accelerations and on simulationsu s i n g a c t u a l l a u n c h w i n d d a t a , lunar module loads were de termined t o bew i th i n s t r u c t u r a l l im i t s d u r in g e a r t h la u nc h a nd t r a n s l u n a r i n j e c t i o n .The sequence f i lms from t h e onboard camera showed no evidence of s tr u c-t u r a l o s c i l l a t i o n s during l u na r touchdown, and crew comments agree witht h i s a s s e s s m e n t .

L an di ng on t h e l u n a r s u r f a c e o c c u r r e d w i t h es t imated l and ing ve loc-i t i e s o f 3 .1 f t / s e c v e r t i c a l , 1 . 7 f t / s e c i n t h e plu s-Y f o o tp a d d i r e c t i o n ,an d 1.7 f t / s e c i n t h e p lu s- Z f o o t p a d d i r e c t i o n .a n d a t t i t u d e at touchdown are shown i n f i g u re 8-1. The minus-Y fo ot pa dapparen t ly touched f i r s t , followed by t h e minus-Z foo tpa d approxim ately0.4 second l a t e r .onds and t h e ve h ic le came t o res t w i th a t t i t u d e s o f 1.8 d e g r e e s p i t c hdown, 6.9 d eg re es r o l l t o t h e r i g h t and 1 . 4 degr ees yaw t o t h e l e f t o fw e s t . Very l i t t l e , i f any, o f t h e v e h i c l e a t t i t u d e w a s due t o l a n d i ngg e a r s t r o k i n g . The f i n a l r e s t a t t i t u d e o f a p pr o xi m at el y 7 degrees w a sdue a lm os t e n t i r e l y t o l o c a l u n d ul at io n s a t t h e l a n d i n g p o i n t ( f i g . 8 - 2 ) .From a t i m e h i s t o r y o f t h e descent engine chamber pressure, i t appearstha t descen t eng ine shu tdown w a s i n i t i a t e d a f t e r - f i r s t f oo tp a d c o n ta c t

but bef ore plus-Y footpad contact .o f decay a t 108:15:11, and a l l vehicle motion had ceased 1 .6 secondsl a t e r.

T h e s p a c e c r a f t r a t e s

The plus-Y and plus-Z foot pads follo wed w it h in 2 sec-

The chamber pressure w a s i n a s t a t e

Fl ig h t da ta f rom t h e guidance and propuls ion systems were used i nper forming eng in eer ing s imula t ions o f t h e touchdown phase. As i nApollo 11 and Apollo 1 2 , t h e s e si m u l a ti o n s a nd p h o to g ra p hs i n d i c a t e t h a tl a nd i ng g e a r s t r o k i n g w a s minimal i f it occur red a t all.a l s o i n d i c a t e n o s i gn i f i c an t damage t o t h e l a n d i n g g e a r t h e r m a l insula-t i o n .

Photographs

Six teen-mi l l imete r f i lms taken from t h e comand module p r io r t olunar-orbi t docking support a v i s u a l o b s e r v a t i o n b y t h e crew that as t r i p o f mate r i a l about 4 f e e t l o ng w a s h an g in g f ro m t h e a s c e n t s t a g ebase h e a t s h i e l d area. T h e b a s e h e a t s h i e l d area i s d e si gn e d t o p ro -t e c t t h e a s c en t s t a g e f rom t h e pressure and t h e r m a l environment r e s u l t -i n g from asc en t engine plume impingement d uring s ta gi ng . Th e absence



11

8- 2

Tim. hkmir tsc

Figure 8-1.- A t t i t u d e e r r o r s a n d r a t e s d u r i n g lunar lending sequence.



a- 3

I

cuI

a3



8- 4

of abnormal t h e r m a l r es po ns es i n t h e a s c en t s t a g e i n d i c a t e s t h a t t h ehea t s h i e l d w a s f u l l y e f f e c t i v e . S l m i l a r c o n d i t i o n s h av e o c c u r r e d d ur-i n g q u a l i f i c a t i o n t e s t s w h ereb y o ne o r more layers o f t h e heat s h i e l dm at er ia l have become unat tach ed. I n t h e s e c a s e s , t h e t h e r m a l e f f e c t i v e -ness o f t h e heat s h i e l d w a s not reduced.

8.2 ELECTRICAL POWER

The e l e c t r i c a l power d i s t r i b u t i o n s ys te m and ba t te ry per fo rmance w a ss a t i s f a c t o r y w i t h o n e e x c e p t i o n , t h e a s c e n t b a t t e r y 5 o p e n - c i r c u i t v o l t a g edecayed from 37.0 volts at launch t o 36.7 v o l t s a t housekeeping, but w i t hno ef fe c t on op era t iona l pe r fo rmance . A l l power switchovers were accom-p l i s h e d as r e q u i r e d , and p a r a l l e l o p e r a t i o n o f t h e descen t and ascen t b a t -t e r i e s w a s w i t h i n a c c e p t a b l e l i m i t s . The dc bus voltage w a s main ta inedabove 29.0 volts, and maximum observed current w a s 73 amperes du ri ng pow-e r e d d es ce nt i n i t i a t i o n .

The b a t t e ry energy usage th roughout t h e lu nar module f l i g h t i s givenT h e a s c e n t b a t t e r y 5 open -circui t low vo l ta ge i s d i s -n s e c t i o n 8.11.6.

c u s se d i n s e c t i o n 1 4 .2 .1 .

8.3 COMUNICATIONS EQUIPMENT

S-band s t e e r a b l e a nt en n a o p er a t io n p r i o r t o l u n a r l a n d i n g w a s i n t e r -mi t t en t . Although an tenna opera t io n dur ing rev o lu t ion 13 w a s nominal,a c q u i s i t i o n a n d / o r t r a c k i n g pr ob le ms were e x p e r i e n c e d d u r i n g r e v o l u t i o n s11 and 1 2 . A c q u i s i t i o n w a s a t tempted bu t a s i g n a l w a s not acqu i red dur-i n g t h e f i r s t 3 minutes a f t e r ground acq u is i t io n of s ig n a l on revo lu-t i o n 14. Because of t h i s , t h e om n i d i re c t io n a l an te n na s were used f o rl u n a r l a n d i n g . The s t e e r a b l e a n t e nn a w a s u s e d f o r t h e ascent and rendez-vous phase and t h e anten na performed norm ally. The problems w i t h t h es t e e r a b l e a n t e n n a are d i s c u ss e d i n s e c t i o n 1 4 . 2. 3 .

P r i o r t o t h e f i r s t e x t r a v e h i c u l ar p e r i o d , d i f f i c u l t y w a s exper iencedwhen conf ig ur ing t he communicat ion sys tem f o r ex t rav eh i cu la r a c t iv i t y be-c a us e o f a n o pe n a u d io - c en t er c i r c u i t b r e a k e r. E x t r a v e h i c u l a r c o r n m i c a -t i o n s w e r e normal a f t e r t h e c i r c u i t b r ea k er w e s c l o s e d .

D uring t h e l a t t e r p a r t o f t h e f i r s t e x t r a v e h i c u l a r p e r i o d , t h e t e l e -v i s i o n r e s o l u t i o n d e c r e a s e d . The symptoms o f t h e problem were i n d i c a t i v eof an o v e r h e at e d f o cu s c o i l c u r r e n t r e g u l a t o r. T h i s c o n d i t i o n , w h il e n o t

caus ing a c om pl et e f a i l u r e o f t h e c am er a, r e s u l t e d i n d e f o c us i ng o f t h e



8-5

e l e c t r o n r ea do u t beam i n t h e t e l e v i s i o n t ub e a n d , c o ns e qu e n tl y, a degrada-t i o n o f res o lu t io n . The h igh- tempera ture co ndi t ion w a s caused by op erat -i n g t h e c a m e r a f o r a b o u t 1 hour and 20 minutes w h i l e i t w a s w i t h i n t h ethermal environment of t h e clo se d modular equipment stowage assem bly. Thecamera w a s t u r n e d o f f b e tw ee n t h e e x t r a v e h i c u l a r p e r i o d s t o a l l ow c o o l i n g .P i c t u r e r e s o l u t i o n d u r i n g t h e s ec on d e x t r a v e h i c u l a r a c t i v i t y w a s s a t i s f a c -t o r y .

The VHF system performance was p o or f ro m p r i o r t o lunar l i f t - o f ft h r o u g h t e r m i n a l p h a s e i n i t i a t i o n . This problem i s d i s c u s s e d i n d e t a i li n s e c t i o n s 7.4 an d 14 .1 .4 .

8.4 RADAR

The landing radar s e l f - t e s t w a s performed a t 105 hours 44 minutes ,a n d t h e r a d a r w a s tu rn ed on f o r t h e powered descent about 2 hours l a t e r .Four m in ut es f i f t y s ec on ds p r i o r t o powered d e sc e nt i n i t i a t i o n , t h e radarchanged from high- t o low-scale . A t t h a t t i m e , t h e o r b i t a l a l t i t u d e oft h e lunar module w a s about 10.9 milesa. This con di t io n p reven ted acqu i -s i t i o n of r a ng i ng s i g n a l s a t slant r a n g e s g r e a t e r t h a n 3500 fee t , and ve-l o c i t y s i g n a l s a t a l t i t u d e s g r e a t e r t h a n a b o u t 4600 f e e t . The radar w a sr e t u r n e d t o h i g h - sc a l e by r e c y c l i n g t h e c i r c u i t b r e a k e r . A d e t a i l e d d i s -cuss ion o f t h i s p roblem i s g iv en i n s e c t i o n 1 4 .2 .4 .performance from a s l a n t range of about 25 000 f e e t t o touchdown i s showni n f igure 14-22.radar l o ck u p r e s u l t i n g f ro m p a r t i c l e s s c a t t e r e d by t h e e n g i n e e x h au s tplume during lunar l a n d i n g .

Range an d v e l o c i t y

There were no zero Doppler dropouts and no evidence of

Rendezvous radar performance w a s nominal i n all r e s p e c t s , i n c lu d i n g

s e l f - t e s t s , heckout , rendezvous and lunar surface t racking, and tempera-t u re .

8.5 INSTRUMENTATION

The in str um ent at i on system performed normally throughout t h e f l i g h tw i th t h e e x c ep t i o n o f t h r e e of t h e four ascen t he l ium tank pressure m e a s -urements ( two pr imary and two redun dant) . Coincident with prop uls i ons y st em p r e s s b i z a t i o n , t h e s e meas ur em en ts e x h i b i t e d n e g a t i v e s h i f t s ofup t o 4 p e r c e n t . "he l a r g e s t s h i f t s were i n th e redundant measurements.Th es e t r a n s d u c e r s h i f t s were caused by t h e shock induced by t h ep y r o t e c h n i c a l l y o p e r a t e d i s o l a t i o n v a l v e s . S i n c e t h e s e measurements areu se d t o m on it or f o r l e a k s p r i o r t o p r o pu l si o n s y st em p r e s s u r i z a t i o n , a

% e fe re nc ed t o l a n d in g s i t e e l e v a ti o n .



8- 6

s h i f t i n these measurements a t t h e time of s ys te m p r e s s u r i z a t i o n w i l l n o ta f f e c t f u t u r e m i ss i on s .t i o n of changes made su bseq uent t o Apollo 13.)

(See appendix A, s e c t i o n A .2 .3 , f o r a d e s c r i p -

8.6 GUIDANCE, NAVIGATION, AND CONTROL

A t approximately 1 0 2 hou rs , t h e p r imary gu idance sys tem w a s t u r n e don , the compute r d i g i t a l c lock w a s i n i t i a l i z e d , and t h e p l at f or m w a sal ig ne d t o t h e command module pl atf or m.pr imary gu idance p la t fo rm a l ignment d a ta .tu rned on a t 1 0 2 h o ur s 40 mi n ut es a nd t h e a t t i t u d e r e f e r e n c e a l i g n e d t ot h e lunar module platform.ment u n i t component errors m eas ure d p r i o r t o l a un c h an d i n f l i g h t . Theabor t guidance system w a s a l i g n e d t o t h e p r im a ry g u id a nc e s y st em s i xt i m e s , but d a t a were a v a i l a b l e f o r o n l y f i v e , a n d are shown i n t a b l e8-111.. Also shown i n t ab le 8-111 a r e da ta f rom the independent a l ignmento f t h e a b o r t s ystem pe rf or me d i n p r e p a r a t i o n f o r l u n a r l i f t - o f f .abor t g u id a nc e s y st em h ad b ee n a l i g n e d t o t h e g r a v i t y v e c t o r a nd an a z i -

muth an gl e su pp lie d by t h e ground. Twenty-seven minutes l a t e r , j u s t be-f o r e l i f t - o f f , t h e a bo rt system compared wel l with the pr imary systemwhich h ad b ee n i n e r t i a l l y a l ig n e d t o t h e p r e d i c t e d l o c a l v e r t i c a l o r ie n -t a t i o n f o r l i f t - o f f .

Table 8-1 i s a summary of t h eTh e abort guidance system w a s

Table 8-11 i s a sumnary of i n e r t i a l measure-

The

The performance of the abort sensor assembly of t h e abort guidancesystem w a s not as good as on previous missions but w a s w i t h i n a l l o w a b l el i m i t s . The acce le rometers ex h ib i t e d s t ab le pe r fo rmance , but the Z-ax i sgyro d r i f t r a t e change o f 1 . 2 degrees per hour from t h e p re launch va lu ew a s a b ou t 30 p e r c e n t g r e a t e r t h a n t h e ex p e c t ed s h i f t . The e x p ec t ed an dt h e a c t u a l s h i f t s betw een p r e f l i g h t v a l u es a n d t h e f i r s t i n f l i g h t c a l i -b r a t i o n , a nd s h i f t s be tw ee n s u bs eq u en t i n f l i g h t c a l i b r a t i o n s ar e showni n t a b l e &IV.

Table 8-V i s a s eq ue nc e o f e v e n t s p r i o r t o a nd d u r i n g t h e po wer edd es ce nt t o t h e l u n a r s u r f a c e . A command t o abo rt usi ng t h e d escent en-g i n e w a s d e t e c t e d a t a computer input channel a t 104:16:07 (but w a s n o tobserved a t o t h e r telemetry p o i n t s ) a l th o u g h t h e c rew h ad n o t d e p r e ss e dth e abo r t swi tch on t h e pan e l . The c rew execu ted a p r o c e d u r e u s i n g t h ee n g in e s t o p sw it ch a nd t h e a b o r t s w it c h which i s o l a t e d t h e f a i l u r e t oth e ab or t s wi tch . Subsequen t ly, th e command reappeared th re e more t imes ;each t im e, t h e command w a s removed by tapping on the panel nea r t h e a b o rts w i t c h .s e c t i o n 1 4 . 2 . 2 . )

( F o r a d i s c us s i o n o f t h e p ro b a bl e c a u s e o f t h i s f a i l u r e , see

I f t h e a b o r t c o m a n d i s p r e s e n t a f t e r s t a r t i n g t h e p owered d e s c e n tprograms, the computer automatical ly switches t o t h e abor t programs an dt h e lunar module i s guided t o an abort o r b i t . To a vo id t h e p o s s i b i l i t y



fIIP .'d

Yas

I

HI

Q

39I3

.. ..) I



8-8

I

a

I

HH

Ico

32f

PY

I I U N I



TABLE 8-111.- GUIDANCE S Y S T E ~ LIGNMENT COMPARISON

Ti m e of al ignment

103 : 4 : 4.99

10 4 : 4 : 5 .9

104:34:45.2

109 :28 : 6

1 4 1 15 :25.2

I 141:45:29.2

Primary minus abort system

Alignment error ( degrees )X

0.000

0.061

0.000

-0.002

0 .ooo

0.010

Y

0.003

0.030

0.007

0.034

0.002

0.003

Z

0.014

0.002

0.003

0.000

0.001

0.018

aSystems al i gne d independent ly. Actual t i m eo f a b o r t guidance system alignment was141:18:35.2.

TABLE &IV.- ABOKTGUIDANCESYSTEM CALIBRATION COMPARISONS

C a l i b r a t i o n s

F i r s t i n f l i g h t minus p re -i n s a l l a t o n

S ec on d i n f l i g h t minus f i r s t- i n f l i g h t

F i r s t s u r f a c e minus s ec on di n f l i g h t

Second sur face minus f i r s ts u r f a c e

Three-s igmac a p a b i l i t y

e s t i m a t e

20.91

20.63

k0.56

+O. 55

Actual gyro d r i f t r a t e ,deg /h r

~

X a x i s

0.08

-0.01

-0.02

0 .o

~~

Y axis

-0.07

0.23

- 0 . 0 8

-0 - 0 8

-1.2

0.26

-0.43

-0.21



8- 0

108:09:10.66

10 8 : 9 : 5 .80108:11:09.8010 8 : 11 : 0.4210 : 11 : 1 . 6 010 : 11 2 .66108 : 1 3 : 7.86108:1 3 09.801 108:15:09.30108:15 :11.13

108:15:11.40

108 og :12.66

TA B U 8-V.- SaUENCE OF EVENTS D U R I N GPOWERED DESCENT

Elapsed t imefrom l i f t - o f f ,

h r min : e c

107 : 1 ~ 8 . 6 6107 : 2 : 6.66

107 7 : 4.661 0 7 : 8: 13.80

10 8 : 2 : 9.12108:02:26.52108 : 2 : 3.80

10 8 : 4 : 9 .80108: 08 : 7.68108 08: 50.66

Time fromi g n i t i o n ,

min:sec

-11:07.86-9:39.86

-4 5 1 - 8 6-4t12.72

-0:07.400 :oo.oo

+O 2 7 . 2 8

+2 2 3 . 2 8

+6:24.14

+6:44.14+6 : 6 . I 4+7:09.28+8:43.28

+8 : 3.90+9:25.08+9 t26.14

+10 1.34+10:43.28+12:42.78+12 : 4.61

+12 4.88

+6:21.16

v -L

?L.

Event

Landing radar onF a l s e d a t a good indicat ions from

landing radarLanding r ada r s w i tc h e d t o low s c a l eS t a r t l o a d i n g a b o r t b i t work-around

r o u t i n eUllage onI g n i ti onManual th ro t t l e - up t o full t h r o t t l e

Manual target update (N69)Throt t le downLanding radar t o hi gh s c a l e ( c i r c u i t

Landing rada r ve lo c i t y da t a goodLanding radar range d a t a goodE n ab le a l t i t u d e u p d a t esSelect approach phase program ( ~ 6 4 )

S t a r t p i t c h o v erLanding radar redes igna t ion enab leLanding r a d a r a nt en n a t o p o s i t i o n 2Selec t a t t i tude ho ld modeSelect landing phase program ( ~ 6 6 )Left pad touchdownEngine shu tdown (d ecrea s ing th ru s t

chamber pressure)Righ t , fo rvard ,and a f t pad touchdown

p o s i t i o n

b r e a k e r c y c l e )

1 -

i



8-1 1

of an unwanted abor t , a work-around procedure w a s developed by groundpersonne l and w a s re layed t o t h e crew f o r manual e n t r y i n t o t h e l u n a rmodule computer. P a r t one of t h e four-p ar t procedure w a s e n t e re d i n t ot h e c o m p u t e r j u s t a f t e r t h e f i n a l a t t i t u d e maneuver f o r p owered d e s c e n t .The remainder w a s accomplished a f t e r t h e i n c r e a s e t o t h e f u l l - t h r o t t l ep o s i t i o n . P a r t one c o n s i s t e d of loadi ng th e abo rt s t ag e program numberi n t o t h e mode r e g i s t e r i n t h e e r a s a b l e memory wh ic h i s u se d t o m o n i to rt h e program number displ aye d t o t h e crew. T h is d i d n o t c a us e t h e a c t i v eprogram t o change, b ut it d i d i nh i b i t t h e computer f rom checking t h eabo rt command s t a t u s b i t .command t o f u l l - t h r o t t l e p o s i t i o n , a u t om a t ic g ui d an c e s t e e r i n g , a nd i ta f f e c t e d t h e p r o ce s s in g o f t h e l a n di ng r ada r d a t a .t o r e e s t a b l i s h t h e d e s i re d co nf ig ur at io n f o r d e s c en t , t h e i n c r e a s e t of u l l - t h r o t t l e p o s i t i o n w a s accomplished manual ly and th en t h e second ,t h i r d , and f o u r t h p a r t s o f t h e p ro ce du re were e n t e r e d i n t o t h e computer.In o rder, they accompl i shed :

A t t h e same t i m e , i t i n h i b i t e d t h e a ut om at ic

T h e r e f or e , i n o r de r

a . S e t t i n g a s t a tus b i t t o i nf or m t h e d e sc e nt p rogram t h a t t h r o t t l e -up had occur red and t o re -enab le gu idance s t e e r in g

b . R e s e t t i n g a s t a t u s b i t which d i s a b l e d t h e a b o r t program s

c. Replacing t h e a ct iv e program number back i n t o t h e mode regis ters o t h a t l an d in g r a d a r da ta would be processed proper ly a f t e r l a n d i n gradar lock-on

The abort c a p a b i l i t y o f t h e p ri ma ry g u id a nc e s y st e m w a s l o s t by u s e o ft h i s p r o c e d u r e .guidance system i f an a b o r t s i t u a t i o n h ad a r i s e n .

There fo re , i t would have been nec essa ry t o use t h e a b o r t

P r i o r t o p ow ered d e s c e n t m aneuve r i g n i t i o n , t h e l a n d i n g radar s c a l e

f a c t o r s w i t c h ed t o l ow, w hich p r ev e n te d a c q u i s i t i o n o f d a t a through t h ef i r s t 400 seconds of descent .t i o n 14.2.4.)s c a l i n g t o t h e h ig h s c a l e , and l an di ng r ada r lock-on occurred a t 22 486f e e t . Figure 14-22 i s a p l o t of s l a n t r an ge as measured by la nd in g radaran d as computed from primary guidance system s t a t e v e c t o r s . F i g u r e 8-3i s a p l o t of a l t i t u d e s computed by t h e a bo rt and primary guidance systemsand shows a 3400-foot updat e t o t h e abort guidance system a t t h e 1 2 000-f o ot a l t i t u d e .

(F or f u r t h e r d i s c u s s i o n , r e f e r t o sec-The crew cycled the radar c i r c u i t b r e a k e r , which r e s e t

T h r o t t l e o s c i l l a t i o n s t h a t h ad b ee n n o te d on p re v io u s f l i g h t s werenot d e t e c t e d d u r i n g t h e d e s ce n t a l t ho u gh some o s c i l l a t i o n i n t h e auto-mat ic th ro t t l e command w a s d e t e c t e d a f t e r descent engine manual shutdown.

The r e a c t i o n c o n t r o l s y st e m p r o p e l l a n t c on su mp ti on d u r i n g t h e b r a k i n gphase and approach phase programs w a s approximately h a l f t h a t s e e n o np r e v i o u s m i s s i o n s . F u r t h e r d i s c u s s i o n o f t h e s e t wo areas w i l l be pro-.ided i n a s up pl em en t t o t h i s r e p o r t.



8-12

2

0

-1

\'\

---------_I-----

- ---- -7 i E i guidance solufion 1

altitude update P, \ Landing

-I

Figure 8-3.- Comparison of al t i tu d es computed by abort andprimary guidance systems during descent .

While on the lunar s u r f a c e , a t e s t w a s performed t o compute gr av i t yus ing p r imary gu idance sys tem acce le romete r da ta .w a s de te rmined t o be 162.65 cm/sec2.

The va lue o f g rav i ty

P er fo rm an ce d u r i n g t h e a s c e n t fr om t h e l u n a r s u r f a c e w a s nominal.The p r imary and abor t sys tems and t h e powered f l i g h t p rocessor da ta com-p a r e d w e l l th roughout a scen t .d oe s no t i n c l u d e t a r g e t i n g f o r a s p e c i f i c c u t o f f p o s i t i o n v e c to r ; t h e r e-f o r e , a vernier adjustment maneuver of 10 .3 f t / s e c w a s performed t o sa t -i s f y t h e p h a s i n g c o n d i t i o n s f o r a d i r e c t rendezvous wi th t h e command andse rv ice module .

The as ce nt program i n t h e onboard computer

Performance throug hout rendezvous, docking, and t h e deor b i t maneuverw a s a l s o nominal.j e t t i s o n w a s minus 1.94, minus 0.05, an d minus 0 . 1 0 f t / s e c i n t h e X, Y ,an d Z axes, r e s p e c t i v e l y.

The veloci ty change imparted t o t h e l u n ar module a t



8-14

a f t e r i g n i t i o n , a n d w a s m os t p r o ba b l y t r i g g e r e d by t h e p o i n t s e n s o r i no x i d i z e r t a nk 2 . Engine cutoff occurred 53 s ec on ds a f t e r t h e l o w- le ve ls i g n a l , i n d i c a t i n g a remain ing f i r ing- t ime- to -dep le t ion of 68 seconds.Us ing p robe da ta t o c a l c u l a t e r e m a i n i n g f i r i n g t ime gave approximately70 seconds remaining. This i s w i t h i n t h e a c c u r a c y a s s o c i a t e d w i t h t h ep r o p e l l a n t q u a n ti t y g a g i ng s y s e m.

The new p r o p e l l a n t s l o s h b a f f l e s i n s t a l l e d on Ap ol lo 14 a p pe a r t ob e e f f e c t i v e . The p r o p e l l a n t s l o s h l e v e l s p r es e n t on A po ll o 11 and 1 2were n ot observed i n th e sp ec ia l h igh-srunple- ra te gag ing sys tem d a t a o ft h i s m is si on .

8.8 ASCENT PROPULSION

The ascen t p ropu l s ion sys tem du ty cyc l e co ns i s t ed of t w o f i r i n g s -t h e lunar a s c e n t and t h e te rm i na l p has e i n i t i a t i o n .s ys te m f o r b o t h f i r i n g s w a s s a t i s f a c t o r y .

Performance o f t h eTable 8-VI i s a summary of

TABLE 8-VI.- STEADY-STATE PERFORMANCE WRING ASCENT

Paraw t e r

Regulator o u t l e t pressure, p s i a

Oxidizer bulk temperature, O F

Fuel bulk temperature. OF

Oxidizer interface pressure , psia

Fuel interface pressure, p s i a

Engim chamber pressure, psia

Mixture ratio

Thrust. l b

Specific impulse, sec

10 seconds after ignition

Rcdi cteda

184

7 0 O

70 .O

170.5

170.4

123.

1.607

3502.

310.3

bClcasured

182

69.4

69 8

168

169

121

---

~~

bo0 seconds after ignition

Predi teda

184

69 o

69.8

169.7

169.7

123.2

1.598

3468.

309.9

bMeasured

181

69 .I

69.4

167

167

120

---

%reflight prediction based on acceptance te s t data and rcrsming nomlnal system pcrforrance.

bActual f l i & t dr ta w i t h no a d J w t w n t . .



8-15

ac t ua l and p red ic t ed pe rformance d ur ing th e asc en t maneuver. The dura-t i o n of e n g in e f i r i n g f o r lu n a r a s c e n t w a s approximately 432 seconds,and f o r t e r m i n a l ph as e i n i t i a t i o n , 3 t o 4 seconds.mate of t h e t e r m in a l ph as e i n i t i a t i o n f i r i n g t i m e i s n o t a v a i l a b l e be -cause t h e f i r ing occur red behind t h e moon and no t e lemet ry da ta werereceiv ed. System pres sur es were as expec ted bo th be fore and a f t e r t h et e r m i n a l ph a s e i n i t i a t i o n m aneuver a nd crew r e p o r t s i n d i c a t e t h a t t h emaneuver w a s naminal.

A more precise e s t i -

No o s c i l l a t i o n s were no te d d u ri n g f l i g h t i n e i t h e r he l ium r e g u l a t o r

Also, o s c i l l a t i o n sou t l e t p ressure measurement .6 t o 19 p s i ha ve be en n o te d i n p r ev i ou s f l i g h t d a t a .of a s i & l a r na tu re and approx imate ly twice tha t magni tude w e r e n o t e dd u r i n g p r e f l i g h t c he ck ou t of t h e a s c e n t p r o p u ls i o n s y s te m c l a s s I second-ary hel ium regu la to r. However, dur ing f l i g h t , con t ro l i s main ta ined ,normal ly, by t h e c l a s s I pr imary regu la to r.

O s c i ll a t io n s i n t h e o u t l e t p r e ss u re of

8.9 ENVIRONMENTALCONTROL AND CREM STATION

Performance of the environmental control system w a s s a t i s f a c t o r ythroughout t h e mi ss ion . Glycol pump n oi s e, a nuisance exper ienced onp r e v i ou s m i s s i o n s , w a s reduced below the annoyance level by a m u ff l e ron t h e pump sy ste m.expec ted much o f t h e t i m e , the separa to r r emoved w a t e r adequately andthere were no problems w i t h wate r condensat ion o r cab in humid i ty.

Although the water s e p a r a t o r s p ee d w a s h i g h e r t h a n

Because of water i n t h e s u i t loop on Apollo 12 ( r e f . 11, a f l o w re-s t r i c t o r ha d be en i n s t a l l e d i n t h e primary l i t h i u m hydrox ide ca r t r idgest o r e du ce t h e gas fl ow i n t h e s u i t loop and , the reby, r educe water sep-a ra to r speed be low 3600 r p m .mass t o b e s e p a ra t e d and t h e gas f low. )speed w a s above 3600 r p m w hile t h e s u i t w a s o p e r at e d i n t h e cabin mode(helmets and gloves removed). The high speed when i n t h e cabin mode re-s u l t e d from low mois tu re inp u t s f rom th e crew (approx imate ly 0 .14 lb /h r )an d a high gas f low caused by low back p re ssu re which, i n tu rn , developedfrom a low pressure d rop ac ross the s u i t .

(Separa to r speed i s a f u n c t i o n o f t h e waterHowever, t h e wa te r s epa ra t o r

Dur ing p repara t ions f o r t h e f i r s t e x t r a v e h i c u la r a c t i v i t y, t h e t r a n s -The k i n ke r h o se o n - t h e u r i n e c o l l e c t i o n t r a n s f e r as sem bly w a s kinked.

w a s el i mi nat ed by moving th e hose t o a d i f f e r e n t p o s i t i o n.

The c rew re pea t ed ly had t ro ub l e g e t t i ng th e lun ar module fo rwardwindow s h ad e s t o r em ai n i n t h e i r r e t a i n e r s . The shades had been processedt o r ed uc e t h e c u r l and p reven t c rack ing , a problem experienced on previousf l i g h t s .c r e a s e d s o t h a t t h e s h a de s would n o t f i t s e c u r e l y i n t h e r e t a i n e r s .

I n r e du c in g t h e c u r l , t h e d i a me t e r of t h e r o l l e d shades w a s i n -For



8-16

Apollo 1 5 , the shades w i l l be f a b r i c a t ed t o p er mi t them t o be r o l le ds m a l l enough t o be h e l d s e c u r e l y by t h e r e t a i n e r s .

The in te ri m stowage assembly cou ld not be s ecu red a t a l l t i m e s be-This problema u se t h e s t r a p s c o u ld n o t b e drawn t i g h t en oug h t o h o l d .

r e s u l t e d from s t r e t c h i n t h e f a b r i c a nd i n t h e s ew in g t o l e r a n c e s . I n

the future , more emphasis w i l l be placed upon manufactur ing f i t checksand crew compartment f i t c heck s t o a s s u r e t h a t t h e problem does notr e c u r.

8.10 ExTRAMIICUTJd MOBIUTY UNIT

P er fo rm an ce o f t h e e x t r a v e h i c u l a r m o b i l i t y u n i t w a s very good duringt h e e n t i r e lunar s t a y.t i o n 8.11.7) a llowed each ex t rav eh ic u la r p e r io d t o be ex tended approx i -mately. 30 minutes w i t h no dep let ion of cont ingency reserves .t empera tu res were main ta ined us ing t h e di ve r t e r va lve i n t h e minimum pos i -

t i o n t h ro ug ho ut m ost o f b o t h e x t r a v e h i c u l a r a c t i v i t i e s .

Oxygen, feeifwater, and power consumption (sec-

Comfortable

P r ep a ra t io n s f o r t h e f i r s t e x t r a v e h i c u l a r a c t i v i t y p ro ce ed ed onschedule w i t h few exceptions.v e h i c u l a r a c t i v i t y o c cu r r ed w h i le t h e p o r t a b l e l i f e sup por t s ystem powerw a s o n , r e s u l t i n g i n b a t t e r y power b e i n g t h e l i m i t i n g co nsu mab le i n de-t e r m in i n g t h e e x t r a v e h i c u l a r stay t i m e .

The d el ay i n s t a r t i n g t h e f i r s t e x t r a -

Oxygen consumption of t h e Lunar Module P i l o t du rin g t h e f i r s t e x t r a -v e h i c u l a r a c t i v i t y w a s o n e - t hi r d h i g h e r t h a n t h a t o f t h e Commander. Tele-met ry da ta dur ing t h e Lu nar Module P i l o t ' s s u i t i n t e g r i t y ch eck i n d i c a t e da pressure decay rate of approximately 0.27 p s i / m i n ; a r a t e of 0.30 p s i /min i s a ll ow a bl e. I n p r e p a r a t i a n f o r t h e s ec on d e x t r a v e h i c u l a r a c t i v i t y ,

s p e c i a l a t t e n t i o n w a s g i ve n t o c l e an i n g an d r e l u b r i c a t i n g t h e L u n a r ModuleP i l o t ' s pr ess ur e garment assembly neck and w r i s t r i n g sea l s i n an e f f o r tt o l o we r t h e e x t r a v e h i c u l a r m o b i l i t y u n i t leak r a t e . A 0.22 ps i /min p res -sure decay r a t e w a s r e p o r t e d by t h e Lunar Module P i l o t p r i o r t o t h e seconde x t r a v e h i c u l a r a c t i v i t y . P o s t f l i g h t unmanned l e a k r a t e t e s t s on the LunarModule P i l o t ' s p ressu re garment assembly show no s ig n i f i ca n t inc r ease i nleakage.

Just p r i o r t o lunar module cab in depressur iza t ion fo r t h e seconde x t r a v e h i c u l a r a c t i v i t y, t h e h m a r Module P i lo t r epor ted a continuousf o rc e i n h i s r i g h t e x t r a v e h i c u l a r g l o ve w r i s t p u l li n g t o t h e l e f t an ddown. A more d e t a i l e d d i s c u s s i o n i s g iv en i n s e c t i o n 14.3.2.t r a v e h i c u la r a c t i v i t y s t a r t e d a nd w a s completed witho ut any r e p o r t e dd i f f i c u l t y w i t h t h e g lo v e.

The ex-

? -L

t Ti L



8-18

Condition

Loaded

Total consumed

Remaining at lunarmodule j e t t i son

8.11.2 Ascent Propuls ion System

P r e d i c t e dq u a n t i t y , lb

A c t u a l q u a n t i t y, lb

F u e l O x i d i z er To t a l

2007.0 3218.2 5225.2

1879 .O 3014 .O 4893.0 4956 o

128.0 204.2 332 02 265.8

P r o p e l l a n t .- A sc en t p r o p ul s i o n s ys te m t o t a l p r o p e l l a n t u s ag e w a swith in approx imate ly 1 p e r c e n t of t h e p r e d i c t e d v a l u e .t h e f o l l o w i n g t a b l e were d e te r m in e d fro m m ea su re d d e n s i t i e s p r i o r t o '

l aunch and f rom weigh t s o f o ff - loaded p rope l l an t s .

The loa ding s i n

Condi t ion

b e d e d

Cons m e

Remaining at lu na r module impact

Actualq u a n t i t y, lb

13.4

8.8

4.6



8-19

8.11.3 Reaction Control System Propellant

The re act ion con tro l system pro pel lan t consumption w a s calculatedfram telemetered helium tank pressure his tor ies using the re la t ionshipsbetween pressure, volume, and temperature.

Condition

Loaded

System ASystem B

Total

Consumed t o

DockingImpact

Remaining at l una r impact

Actual, lb

Fuel

10 8

216

10

Oxidizer

209209

418

Total

634

260378

256

Predicted, lb

6 3

28339 3

2 0



8-20

8.11.4 Oxygen

The o q g e n t an k w a s n o t l o a d e d t o t h e n om in al 2730 p s i 8 u s e d f o r

Launch p r e s s u r e f o r t h e t a n k wasprev ious miss ions because of a poss ib le hydrogen embr i t t l ement p rob lemw i t h t h e d e s c e n t stage oxygen tank .an i n d i c a t e d 2361 p s i a .

Condi t ionILoaded ( a t lift-off)

Des en t 8 tageAscent s tage

Tank 1Tank 2

Tota l

Cons me dDes c e n t stageAscent stw

Tank 1Tank 2

T o t a l

Remaining i n descen t s t a ge atl u n a r l i f t - o f f

Remaining at docking

Tank 1Tank 2

To t a l

Actualq u a n t i t y , l b

42.3

2.42 .4

47.1

24.9

( a )0

17.4

( a >2.4

P r e d i c te dq u a n t i t y, l b

23.9

1.10

25 .O

18.4

1.32.4

3.7

Consumables data are n o t a v a i l a b l e b ec au s e t h e t a n k 1 p r e s s u r et r a n s d u c e r m a l fu n c ti o ne d b e f o r e l a u n c h .

..L

t '&



8 . U . 5 Water

I n t h e f o ll o w in g t a b l e , t h e a c t u a l q u a n t i t i e s l o ad e d an d consumeda r e b a s e d o n t e l e m e t e r e d d a t a .

Condi t ion

Loaded ( a t lift-off)

Descent s tageAscent s tage

Tank 1Tank 2

To t a l

Consumed

Descent stage (lunar i f t - o f fAscent s tage (docking)

Tank 1Tank 2

To t a l

Ascen t s t age ( impac t )Tank 1Tank 2

% O t al

Remaining i n descen t s t age a tl u n a r l i f t - o f f

Remain ing i n a sce n t s t age atimpact

Tank 1Tank 2

To t a l

Actuall u a n t i t y, lb

255.5

42.542.5

340.5

200.9

6 .o5.8

212.7

14 .414.9

230.2.

54.6

20.127.6

55 - 7

aConsumed du rin g f l i g h t , both stages.

P r e d i c t e dq u a n t i t y, lb



8-2 3

8.11.7 Ext raveh icu la r Mobi l i ty Uni t

Oxygen , feedwater and power consumption of the extravehicular mobil-i t y u n i t f o r bo th e x t r a v e h i c u l a r p e r i o d s a r e shown i n t h e f o l l o w in g t a b l e .

Condi t ion

F i rs t ex t r a v e h i c u l a r a ct i v i y

Ti m e , min

Oxygen, l bLo ade dCons m e dRemaining

Feedwater, l b

LoadedConsumedRemaining

Pow er , W-hI n i t i a l chargeConsumedRemaining

S e c o n d e x t r a v e h i c u l a r a c t i v i t y

T i m e , m i n

Oxygen, l bLoadedCons m e dRemaining

Feedwater, lbLoadedCons ume dR e m a in i ng

Po we r, W-hI n i t i a l c harge

ConsumedR e m a in i ng

Commander

Actual

288

1 . 3 10.700 . 6 1

8.594.853.74

2 82228

5 4

275

1.260.860.40

8.806.432.37

aa

2 82

22557

Pre d i c t e d

25 5

1 . 3 1

0.340 a97

8.557.081.47

2 82223

59

25 5

1 . 3 11.020.29

8.557.551 .0

282

22557

Lunar Module Pi l o t

Actual

288

1.311.020.29

8.665.712.95

2822 37

45

275

1.260.960.30

8.807.131.67

2 82

22 260

P r e d i c t e d

25 5

1 . 3 1

0.340 -9 7

8.55

1 . 4 77.08

2 82223

59

255

1 . 3 11 .020.29

8.557.551 o

282

22557

% s t i n a t e b a s e d on e x t r a v e h i c u l a r m o b i l i t y u n i t s o u r c e h e a t p r e -d i c t i o n s b e c a u s e 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 f e e d w a t e r w e i g h t w a sn o t t a k e n f o l l o w i n g t h e s e c o n d e x t r a v e h i c u l a r a c t i v i t y.



9-1

9 O PILOT'S RF,PORT

The Apollo 14 missio n expanded th e tec hn iq ue s and overcame some oft h e o p e r at i o na l l i m i t a t i o n s o f p r e v i o u s l u n a r l a n d i n g m i s s i o n s .d i f f e r e n c e s i n c l u d e d p e rf o rm in g o nb oa rd c i s l u n a r n a v i g a t i o n t o s i m u l a t ea r e t u r n t o e a r t h w i th n o c o mm un ic ati on s, u s i n g t h e s e r v i c e p r o p u l s i o ns ys te m f o r t h e d e sc e nt o rb i t maneuver, l and in g i n t h e l u n a r h i g h l a n d s ,e x t e n d i n g t h e lunar s u r f a c e e x c u r s i o n t i m e and making a luna r- or bi t ren-d ezv ou s d u r i n g t h e f i r s t r e v o lu t i o n o f t h e s p a c e c r a f t . The d e t a i l e df l i g h t p l a n , e xe cu te d i n i t s e n t i r e t y , w a s used as a r e f e r e n c e f o r t h ea c t i v i t i e s o f t h e p i l o t s d u r in g t h e m is si on ( f i g . 9-1, a t e n d o f s e c t i o n ) .

S p e c i f i c

9.1 TRAINING

. The f o r m al t r a i n i n g f o r t h i s cr ew w a s conducted over a t i m e span of

20 months in gen eral accordance w i t h t h e s c h e d u le s u s e d f o r p r e v io u smiss ions .c e l l e n t a n d are recommended f o r subsequent crews es se n t i a l ly unchanged.Although none o f t h e crew m e m b e r s had completed ac tua l . f l i g h t exper ienc ei n th e Apollo program, each of t h e p i l o t s f e l t t h a t he w a s completelyr e a d y f o r a l l p ha se s o f t h e f l i g h t .

The training equipment and methods were concluded t o be ex -

9.2 LAUNCH

The countdown proceeded on schedule w i t h no problems encounteredi n t h e area o f c rew i n t e g r a t i o n o r i n g r e s s . The g e n e r a l c o n d i t i o n o f

t h e c r e w s t a t i o n a n d d i s p l a y s w a s ex ce l l en t . The crew w a s k e p t w e l lin formed of th e na t u r e o f t h e l aunch de la y and w a s appr i se d o f l aunchazimuth change procedures ; accordingly , h a t phase w e n t smoothly. TheCommander note d no v i s i b l e mo istu re on windows 2 and 3 e i t h e r pre launchor dur ing a tmospher ic f l i g h t . The p r o p r i o c e p t i v e c u es r e p o r t e d bye a r l i e r crews were es se n t ia l l y unchanged dur ing th e l aunch of Apol lo 1 4 .No communica tion d i f f i c u l t i e s were no ted dur in g th e l aunch . A verys l i g h t l o n g i t u d i n a l o s c i l l a t i o n o c c ur re d d u r in g s ec on d s t a g e f l i g h ts t a r t i n g a t 8 minutes 40 seconds and con tin ui ng throu gh shutdown. Thel aunch pr of i l es f lown dur ing p re f l ig h t t r a i n in g on the dynamic crew pro-cedures s imula to r and t h e command module simulator were more than ade-q u a t e f o r crew p r e p a r a t i o n .



9-2

9 . 3 EAKTHORBIT

T h i s c rew ha d p l a c e d s p e c i a l e mp ha si s on s u i t e d t r a i n i n g p e r i o d si n t h e command module s i m u l a t o r f o r t h i s p a r t i c u l a r p h a s e .c r a f t system checks and unsta rage of equipment were performed s lowlya n d p r e c i s e l y c o in c id e n t w i t h t h e p r oc e s s o f f a m i l i a r i z a t i o n w i t h t h ew e i g h t l e s s s t a t e . No a no ma li es o r d i f f i c u l t i e s w ere no t ed .

The space-

The Command Module P i l o t n oted t h a t , although he had hear d t h eo p t i c s c o v e r j e t t i s o n , t h e r e w a s n o d e b r i s , a n d a f i n i t e p e r i o d of s ev -e r a l minutes of dark-adaption w a s r e q u i r e d t o p e rm i t v ie w in g o f s t a r st h r o u g h t h e t e l e s c o p e . The e x t e n s i o n o f t h e docking probe i s mentionedhere o nly t o i n d i c a t e t h a t it w a s extended on sched ule , pe r the check-l i s t , with no p roblems no ted f r m e i t h e r a u d i o o r v i s u a l c u e s .

9.4 TRANSLUNAR INJECTION

The delay i n launch produced off-nominal monitoring parameters witht h e s e c o n d S-IVB f i r i n g . These updates were forwarded smoothly and i na t i m e l y f a s h i o n so t h a t all p r e p a ra t i o n s f o r t h e i n j e c t i o n were n o rm al .A t t i t u d e c o n t r o l of t h e S-IVB was e x c e l l e n t a n d right on sc he du le . Thei g n i t i o n w a s on t i m e , po si t i v e , and without roughness . The guidanceparameters comparison between t h e command module comput er and t h e i n -s t r u m e n t a t i o n u n i t w a s v e r y c l o s e . A v er y l i g h t v i b r a t i o n o r buzz w a snoted toward th e end o f t h e powered phase, and i s mentioned on ly t o in -form future crews as t o a resonance re fe ren ce po i n t . The s t a t e v e c t o rc o n d i t i o n s a t cu to ff were e x c e l l e n t a n d t h e tanks vented on schedule .The Commander and Command Module P i l o t changed couch po s i t i o n s i n a ccor d-ance with t h e f l i g h t p la n.

9 .5 TRANSLUNAR FLIGHT

9.5.1 Transposition and Docking

The p h y s i c a l s e p a r a t i o n f r o m t h e S-IVB c l o se d t wo p r o p e l l a n t i s o -l a t i o n va l v e s on t h e s e r v i c e module r e a c t i o n c o n t r o l s ys te m . T he sewere immediately reset w i t h no problems. The en t r y monito r sys tem wasnot used as a r e f e re n c e d u r i ng a ny p o r t i o n of t h e t r a n s p o s i t i o n anddocking maneuver. The p lus-X th ru s t in g on sepa ra t io n and t h e i n i t i a lt h r u s t i n g t o s e t up a c l o s i n g v e l o c i t y were per fo rmed us ing the even t

t imer.

.-L

. -L

?k

. .Y



9.5.3 Midcourse Correct ion

Two midcourse cor rec t ions were p er fo rm ed d u r i n g t h e t r a n s l u n a r c o a s tphase . The f i r s t midcourse cor re c t i on w a s performed a t t h e s e c o n d o p t i o np o i n t and pl a c e d t h e s p a c e c r a f t on a hybr id t r a je c to ry . The maneuver w a sperfo rmed under c on t ro l o f th e gu idance and con t ro l system wi th re s i du a l s

o f p lus 0 .2 , zero, and minus 0.1 f t / s e c . The second midcourse c or r ec t io nw a s performed a t t h e f o u r t h o p t i o n p o i n t a n d w a s t a r g e t e d f o r a v e l o c i t ychange of 4.8 f ' t /sec. I t w a s a se rv ice p ropu l s ion sys tem maneuver pe r-formed under co n t r o l o f t h e gu idance and co n t ro l sys tem. The r e s i d u a l swere plus 0.3, zer o, and minus 0 .1 f t / s e c .

9.6 LUNARORBIT INSERTION

R e s id u a ls r e s u l t i n g f ro m t h e lunar o r b i t i n s e r t i o n maneuver w erep l u s 0.3; z e r o , a n d z e r o f t / s e c . "h e f i r i n g t i m e w a s w i t h i n 1 secondof t h e pad valuea. The only unexpected i t e m n o t e d d u r i n g t h i s maneuver

w a s t h e o p e r at i on o f t h e p r o p e l l a n t u t i l i z a t i o n a nd ga gi n g s ys te m. Thep r e f l i g h t b r i e f i n g s on t h e s ys te m i n d i c a t e d t h a t , a t c r o s s o v e r, t h e un-b a l an c e m et er would o s c i l l a t e a nd t h e n s e t t l e o u t i n t h e 10 0 t o 150 i n -c r ea s e p o s i t i o n . A t c r o s s o v e r, d u r i n g t h e a c t u a l m an eu ve r, t h e u n ba l an c emeter went from i t s decrease po s i t i on smooth ly up t o approximate ly ze ro .I t w a s c o n t r o l l e d a bo ut t h e z e r o p o i n t u s i n g t h e i n c r e a s e a nd no rm alp o s i t i o n s o f t h e s w i t c h .

9.7 DESCENT ORBIT INSERTION

On Apollo 1 4 , f o r t h e f i r s t t i m e , t h e d es ce nt o r b i t i n s e r t i o n

maneuver w a s made w i t h t h e s e r v i c e p r op u l s i o n s y st em .u le compute r ind ica ted a 10.4- by 58.8-mile o r b i t a f t e r t h e maneuver.The Network indicated a 9.3- by 59.0-mi le o r b i t . The f i r i n g t ime obse rv-ed by the crew w a s 20.6 seconds. Themaneuver w a s c o n t r o l l e d by t h e guidance and control system with commandmodule compute r shutdown. Imm edia tely a f t e r t h e d e sc e nt o r b i t i n s e r t i o nmaneuver, t h e s p a c e c r a f t w a s o r i e n t e d t o a n a t t i t u d e from w hich an a b o r tmaneuver could have been performed i f r e q u i r e d , a n d s h o r t l y a f t e r acqui-s i t i o n o f s i g n a l , Houston ga ve a "go" t o stay i n t h e low o r b i t .f i r i n g t i m e vas the c rew moni to r ing shu tdown c r i t e r i a .v i r t u a l l y e l im i n a t e d t h e p o s s i b i l i t y o f an u na c ce p ta bl e o ve rs pe ed .

"h e command mod-

P a d f i r i n g t i m e w a s 20.8 seconds.

PadThis t echn ique

$ad values me t h e vo ice -upda ted pa ramete r va lues used t o pe r fo rma maneuver.

. -L

3 -

L L- i.-L L L I -



9-5

9.8 LUNAR MODULE CHECKOUT

The checkout of t h e l un ar module w a s conducted i n two phases -t h e f i r s t _ d u r i n g t r a n s l u n a r c o a s t a n d t h e s e c o nd on t h e d ay o f t h e de-s c e n t .t h a t t h e l u n a r m o d u l e h a d a low leakage ra te . P a r e r t r a n s f e r t o t h elunar module occurred a t 61:41:11.vol tage read ing on b a t t e r y 5 .sc rews and washers f l o a t in g a round upon in gr es s . During t h i s p e r i o d ,16-RRUmot ion p ic tu res were made of ' a command module w a s t e water dump.Some a dd i t i on a l housekeep ing and equ ipment t r a n s f e r se rve d t o reduce t h eworkload on descent d a y . Power w a s t r a n s f e r r e d b ac k t o t h e command mod-u l e at 62:20:42.

P r e s s u re r e a d i ng s , p r i o r t o e n t e r i n g t h e l u n a r mo du le , i n d i c a t e d

The only anomaly w a s a s l i g h t l y lowThere w ere a bo ut f i v e o r s i x v e r y small

The second lu n a r module checkout w a s accomplished on t h e same dayas p o w e r e d d e s c e n t i n i t i a t i o n . Two c h e c k l i s t s , o ne f o r e ac h p i l o t , wereu s e d t o s p ee d up t h e a c t i v a t i o n p r o ce s s.

Module P i l o t both s u i t e d i n t he command and se rv ic e module p r io r t o in -t r a v e h i c u l a r t r a n s f e r , b u t all equipment had been lo ca t ed th e n igh t be -f o re t o assure t h a t t h i s w ould b e a t i m e l y a nd s u c c e s s f u l p r o c e s s .e lec t rode p rob lem w i t h t h e Lunar Module P i l o t ' s bio sen sor s made t h i sp e r i o d full w i t h n o e x t r a t i m e a v a i l a b l e . The window heaters were usedt o c l e a r some condensat ion found a f t e r i n g r e s s . The probe and droguew e r e i n s t a l l e d and c he ck ed w i t h no p ro ble m. P r i o r t o r e a c t i o n c o n t r o ls ys te m p r e s s u r i z a t i o n , t h e system A m ain s h u t o f f v a l v e c l i c k e d d u r i n gr e c y c le , i n d i c a t i n g t h a t i t was probab ly c losed a t t h a t t i m e .

The Commander and t h e Lunar

A n

The r e ma in d er o f t h e a c t i v a t i o n p r oc ee d ed w i t h o u t i n c i d e n t u n t i ls e p a r a t i o n . S ub se qu en t t o s e p a r a t i o n , t h e checkout of t h e lunar modulesys tems con t inued wi th on ly t w o ad di t i on a l p rob lems becoming ev ide n t .

a. The S-band anten na beha vior w a s e r r a t i c a t v a r i o u s t i m e s wheni n t h e "auto" t r a c k mode.break er opened wi thou t apparen t reason , b u t func t ioned prop er ly uponbe ing r e se t . On a t l e a s t two o t h e r o c c a s io n s , t h e g ro un d s i g n a l w a sl o s t u n e x p ec t ed l y. The a n te n n a d r ov e t o t h e m e ch a ni ca l s t o p , a t whicht i m e t h e breaker opened (as expec ted) .a t e d w i t h t h e a n t en n a w a s noted. I t was subsequen t ly found , by observ ingthe antenna shadow on the lunar s u r f a ce , t h a t t h e n o i s e w a s c o i n c i d e n twith an o s c i l l a t i o n i n bo th p i t c h and yaw.p i t c h p o s i t i o n i n d i c a t o r d i a l w a s o b se rv e d t o b e f u l l - s c a l e u p , w i th t h ean tenna func t ion in g prop er ly. Th is anomaly cor r ec t ed i t s e l f a s h o r t t i m e

l a t e r and d i d no t re cur .

On two occas ions , t h e S-band an tenna c i r c u i t

An u n u s u a l l y l o u d n o i s e a s s o c i -

Upon one occa sio n, t h e antenn a

b. The ot h er major problem, which occ urr ed be fo re powered des cen ti n i t i a t i o n , was observed by the Mission Contro l Center. The crew w a s



9-6

adv i sed o f an abor t discre te b e i n g s e t i n t h e lu na r module guidance com-p u t e r w i t h t h e a b o r t b u t t o n r e se t .c a n tl y i n s o l v in g t h i s problem excep t t o fo l low t h e i n s t r u c t i o n s givenby the Mission Control Center. The remainder of t h e lunar module check-out w a s n om in al up t o t h e p o i n t o f pow ered d e s c e n t i n i t i a t i o n .

?'he c rew d i d n o t p a r t i c i p a t e s i g n i f i -

9.9 POWERED DESCENT

The primary guidance computer w a s used t o s e l e c t t h e d e sc en t pr o-g r a m f o r an i n i t i a l i g n i t i o n a l g o ri t h m ch ec k8 a bo ut 50 m i nu te s p r i o r t oa c t u a l i g n i t i o n , The computer w a s a l s o t a rg e t e d f o r a n o - i g n i t i o n a b o r ta t t h i s t i m e . Fina l systems checks and swi tch s e t t i ng s were t h e n madeand t h e abort guidance system w a s i n i t i a l i z e d t o t h e ground s t a t e v e ct o r(which had been uplinked 30 m i nu te s p r i o r t o i g n i t i o n ) . The a no m al ie sp r e s e n t a t t h i s t i m e i n c l u d e d t h e computer abort b i t problem and theS-band' s te er ab le antenna malf 'unct ion. To assure continuous communica-t i o n s , a d e c i s i o n w a s made t o use omnid i rec t iona l an tennas dur ing powereddes cen t .

The descent program w a s r e s e l e c te d i n t h e primary computer at i g n i -t i o n minus 10 minutes and a f i n a l a t t i tu d e t r i m w a s completed about 5 min-u t e s l a t e r. The f i r s t compute r en t r y, t o i n h i b i t t h e a bo rt command, w a smade ju s t a f t e r f i n a l t r i m . The remain ing en t r i e s were made a f t e r i g n i -t i o n . Both t h e u l l a g e and t h e i g n i t i o n were automatic and occurred ont i m e .a f t e r i g n i t i o n . The t h r o t t l e w a s r e t ur n e d t o t h e i d l e p o s i t i o n a f t e rt h e compute r en t r i e s ha d been completed, at about 1 minute 25 secondsi n t o t h e f i r i n g .board en t ry, abou t 42 seconds a f t e r i g n i t i o n , A l a n d i n g p o i n t t a r g e tupdate of 2800 feet downrange w a s en te re d manually about 2 minutes 1 5 sec -onds a f t e r i g n i t i o n .o f t h e lunar module simulator are n e ar l y i d e n t i c a l t o t h o se f o r t h e a c t u a lv e h i c l e . T h e r e f o r e , h e p i l o t ' s p r e f l ig h t t r a i n i n g w a s completely ade-q u a t e f o r t h e a c t u a l v e h i c l e r e sp o ns e e x h i b i t e d d u r i n g t h e d e s c e nt p h as e .

The engine w a s throttled-up manually by the Commander 26 seconds

The computer guidance w a s i n i t i a l i z e d , by man ua l k ey -

The s t e e r i n g e q u a t i o n s and t o r q u e - t o - i n e r t i a r a t i o

The t h r o t t l e r e c o ve r y p o i n t o c c u rr e d ab ou t 12 s ec on ds p r i o r t o t h ep r e d i c t e d t i m e . " he a l t i t u d e and v e l o c i t y l i g h t s o f t h e computer d i s -p l e y c o n t i n u o u s l y i n d i c a t e d t h a t l a n d i n g r a d a r d a t a w ere i n v a l i d t o a na l t i t u d e w e l l below th e nominal update l eve l .t h e Miss ion Contro l Cen te r t o "cyc le t he l and ing radar c i r c u i t breaker."This a l lowed a v a l i d u p da t e.e n t r y w a s made t o e na bl e t h i s f u n ct i o n a t an a l t i t u d e of a bo ut2 1 000 f ee t . The Commander d id no t e va lu at e manual co n t r o l a f t e rt h r o t t l e r e c o v e r y, as planned , because t h e t i m e r e q ui r e d f o r t h e l a n di n g

A c a l l w a s r e c e i v e d from

The l i g h t s e x t i n g u i s h e d a n d t h e computer

% e r i f i c a t i o n of computer performance.



9-7

rad r updat precluded uch act ion. The abort guidance system fol lowedt h e p ri ma ry s ys te m v e ry c l o s e l y d u r in g t h e p e r i o d p r i o r t o l a n d i n g r a d a rupdate. There w a s , t h e r e f o r e , o n l y a s i n g l e a l t i t u d e u pd ate t o t h eabort system. This update w a s made a t an a l t i t u d e of 1 2 000 f e e t . T h e r ew a s no abnormal divergence of th e abor t guidance system through t h e re-mainder o f the l and ing phase .

The land in g program of t h e primary computer w a s e n t e r e d 8 minutes44 s ec on ds a f t e r i g n i t i o n and a t an a l t i t u d e o f a b ou t 8000 f e e t .veh ic le p i t ched down, as e x p ec t ed , and t h e l u n a r s u r f a c e w a s r e a d i l yv i s i b l e . The t a r g e t l a nd i n g p o i nt w a s recognized immediately by theCommander without reference t o the compute r l and ing po in t des igna tor.The u niq ue t e r r a i n p a t t e r n c o n t r ib u t ed t o t h i s s u c c e s s f u l r e c o g n i t i o n ,b u t t h e d e te r mi ni n g f a c t o r w a s t h e h ig h f i d e l i t y o f t h e s i m u l a t or v i s u a ld i s p l a y an d t h e t r a i n i n g ti m e a s s o c i a t e d w i th t h e d e v ic e . The f i r s t com-p a r i s o n o f t h e l a n d i n g p o i n t d e s i g n a to r s howed z e r o e r r o r s i n c r o s s r a ng eand down range. A r e d e s i gn a t i o n of t h e t a rg e t p o i n t 350 f e e t t o t h es o u t h w a s made at an a l t i t u d e o f a bo u t 2700 f e e t t o allow a l and ing on

what had appear ed t o be smoother t e r r a i n i n t h e p r e f l i g h t s t u d i e s ofc h a r t s an d maps. S e v e r a l c r o s s r e f e r e n c e s b et we en t h e t a r g e t and t h eland ing po i n t des igna to r were made u n t i l an a l t i tu d e o f about 2000 f e e tw a s reached, and good agreement w a s noted . A t some a l t i t u d e l e s s t h a n1500 feet , two things became apparent - i r s t , t h a t t h e r e d e si g na te d( s o u t h ) l a n di n g p o i n t w a s to o rough and , second , th a t th e au tomatic l a n d -i n g w a s t o o cc ur s h o r t o f t h e t a r g e t .

The

The manual descent program w a s i n i t i a t e d a t an a l t i t u d e o f 360 f e e ta t a range of approximately 2200 f e e t s h o r t o f t h e d e s i r e d t a r g e t . Thelunar module w a s c o n t r o l l e d t o z er o d e s ce n t r a t e a t an a l t i t u d e of a bo ut17 0 f e e t ab ov e t h e t e r r a i n . Tr a n s l a t i o n man eu vers f o rw a rd and t o t h er i g h t were made t o a i m f o r t h e p o i nt o r i g i n a l l y t a r g e t e d . Although t h i sarea appeared t o be g r a d u a l l y s l o p i n g , it w a s , i n genera l , smoother thant h e r i d g e s ou th o f t h e t a r g e t . "he f a c t t h a t n o d u st w a s n o t e d d u r i n gt h e t r a n s l a t io n w a s r e a s s u r i n g b e ca us e i t h e l p e d c o r r o b o r a t e t h e primaryc o m p u t e r a l t i t u d e . Veloc i ty on the c r o s s p o i n t e r w a s about 40 f t / s e cforward a t manual takeover and t h i s w a s g r a d u a l ly r e du c ed t o n e a r - ze r oo v e r t h e l a n d i n g p o i n t . A c r o s s v e l o c i t y o f a bo u t 6 f t / s e c n o r t h w a sa l s o i n i t i a t e d and g r a d u a l ly r ed uc ed t o z er o o ve r t h e l an d i n g p o i n t . Thec r o s s p o i n t e r s ( p ri m ar y g u id a nc e ) w er e s te a d y an d t h e i r i n d i c a t i o n s w erei n good agre.ement wi th v i su a l re fe rence t o t h e ground. Cont ro l o f th ev e h i c l e i n primary guidance atti t ud e- ho ld mode and rate- of-d escen t modew a s e x c e l l e n t a t a l l times. The u s e o f t h e l u n a r l a n d i n g t r a i n i n g ve-h i c l e and t h e lu n ar module s im ulato r had more than ad equately equipped

t h e p i l o t f o r h i s t a s k . I t w a s r e l a t i v e l y e a sy t o pi c k o u t a n ex a ctl an d in g s p o t and f l y t o i t w i t h p r e c i s e c o n t r o l .

Blowing surface dust w a s f i r s t n o te d a t an a l t i t u d e o f 110 f e e t , b u tthis w a s n o t a d e t r i m e n t a l f a c t o r. The d u s t a p pe a re d t o be l e s s t h a n



9-8

6 inches i n dep th and rocks were r ea d i ly v i s ib le th rough i t .descent from 10 0 f e e t w a s made at a descen t r a t e o f 3 f t / s e c , wi t h a de -l i b e r a t e f or wa rd v e l o c i t y o f a bo ut l f t / s e c a nd , e s s e n t i a l l y , z e r o c r o s srange ve l oc i ty. The fo rward ve lo c i ty w a s maintained u n t i l touchdown t oprec lude back ing in to any small c r a t e r s . To provide a s o f t l an d in g , adelay of about 2 seconds w a s a l lowed between a cqu is i t ion o f th e con tac tl i g h t s and ac t iv at io n of th e engine s t op but t on. Touchdown occurred a tshutdown with some s m a l l dust-blowing ac t i on cont inuin g during engineth ru s t t a i l o f f o r decay. The l and ing fo rces were ex tremely l i g h t andth e ve hi cl e came t o r e s t w i t h i n 1 degree of zero i n pi t ch and yaw a t t i -tudes , and w i t h a 7-degree r i g h t r o l l a t t i t u d e ( n o r t h e a s t t i l t ) .t o f i g u r e 8-2.)

A f i n a l

(Refe r

Some li ne at io ns were evi de nt i n t h e a rea of thrust impingement ont h e s u r f a c e along t h e f i n a l t r a c k an d i n t h e l an di ng area. As might beexpec ted , these a reas are genera l ly co inc iden t wi th those i n which b low-i n g s u r f a c e d us t w a s noted a t l o w a l t i t u d e s .o f the descen t eng ine a f t e r touchdown appeared t o have been cr at er edonly t o a depth of about 6 inches and, as photographs show, only i n

a s m a l l , well-defined area .

The area i n t h e v i c i n i ty

T h e r e w e r e n o s p u r i o u s t h r u s t e r f i r i n g s a f t e r touchdown. Thelunar dump valves were recy cled with no anomalies noted and t h e descenteng ine p rope l lan t ven t s were i n i t i a t e d .computer w a s t a rg e t e d w i th a l i f t - o f f t i m e o f 10 8: 24 :3 1, t h i s e a r l yl i f t - o f f t i m e was not requ i red .Mission Control C enter and t h e computer w a s s e t t o i d l e a t 108:21:13.

Although t h e primary guidance

The l u n a r "stay" w a s forwarded by the

The S-band communications were ma in tai ne d on t h e forw ard omn idirec -t i o n a l a nt en na du ri ng t h e d e s ce n t , s w it ch ed t o a f t a t pitchdown, andt h e n s w it c he d t o t h e s t ee rab l e an tenna , i n "slew" mode, af ter t h e l u n a rstay w a s approved.

9.10 LUNARSURFACE ACTIVITY

9.10.1 Cabin Act ivi ty

Operations .- Subsequent t o lunar module touchdown, lunar s u r f a c ea c t i v i t i e s p r og re ss ed i n a cc or da nc e w it h t h e c h e c k l i s t . On the check-l i s t i s an i tem request ing a d e s c r i p t io n of t h e l u n a r s u r f a c e t o t h eMission Cont rol Cente r. Although imp ort ant from a s c i e n t i f i c p o i nt ofv i e w , t h i s t a s k proved t o be most u s e f u l i n a l l uw i n g t h e c rew t o a c c l i -mate t he ms el ve s t o t h e lunar enviror lment and, i n conjunct ion w ith Mis-

s i o n C o n t r o l , t o d e te r mi n e more p r e c i s e l y t h e l o c a t i o n o f t h e lunar mod-u le . I n subsequen t ex t rav eh i cu l a r work, i t w i l l be i m p o r t a n t t h a t t h e



9-9

crewmen have a p r e c i s e knowledge of t h e i r s t a r t i n g p o i n t on t h e t r a v e r s emap.

The preparat ion f o r t h e f i r s t e x tr a ve h ic u la r pe r io d w a s nominal a tall times e x c e p t f o r a communications problem which became evident dur-i n g s w i t ch o v e r t o p o r t a b l e l i f e s u p p or t s y s te m c om mu ni ca ti on s. This

problem subsequ ent ly proved t o be t h e r e s u l t o f c o c k p i t e r r o r, w hichp o i n t s a ga in t o t h e n e c e s s i t y of h av in g c h e c k l i s t s t h a t l e av e no l a t i -t u d e f o r m i s i n t e r p r e t a t i o n . The cue c a rd s u t i l i z e d d u r in g all o f t h ee x t r a v e h i c u l a r p r e p a r a t i o n s an d t h e p o s t - e x t r a v e h i c u l a r a c t i v i t y w er eq u i t e adequate excep t f o r t h e one en t r y. However, t h e cue ca rds needt o b e a t t a c h e d more s e c u r e l y t o t h e i n st r u m en t p a n e l t o p r e v e n t t h e i rb e i n g d i s l o d g e d by i n a d v e r t e n t c o n t a c t .

Very l i t t l e s l e e p w a s obtained. This r e s u l t e d pr im ar i ly f rom be ingu nc om fo rt ab le i n t h e s u i t s , b u t w a s a l s o d ue , i n a l e s se r d e gr ee , t o t h etilt o f t h e c a b i n . "h e t i l t w a s e s p e c i a l l y n o t i c e a b l e d u ri n g t h e s l e e pp e r i o d s and made s l e e p d i f f i c u l t b ec au s e t h e c rew w a s uneasy i n t h i s awk-w a r d p o s i t i o n . I t

i st h e cr ew 's f e e l i n g t h a t an u n s u i te d s l e e p p er i o d

would g r e a t l y c o n t r i b u t e t o s u f f i c i e n t crew s l e e p f o r t h e l o n g e r m is s io n s .

I n g e n e r al , t h e lunar module cabin provided an adequate base of op-e r a t i o n s d u ri ng l u n a r s u r f a ce a c t i v i t i e s i n s p i t e of t h e s m a l l a rea andthe 7 -degree t i l t . However, it i s f e l t t h a t , were t h e lunar module t ol a n d o n t e r r a i n i n c l i n e d more t h a n a b o ut 10 t o 1 2 degrees , some d i ff i -cu l t y would be exper ienced i n moving about t h e cab in .

Equipment.- On t h e l u n a r s u r f a c e , t h e a lig nm en t o p t i c a l t e l e s c o p ew a s s a t i s f a c t o r i l y u sed t o align t h e p l at f o rm . R e f l e c ti o n s i n t h e a l i g n -ment o p t i c a l t e l e s c o p e a p pe a re d t o come from t h e l un ar module rendezvousradar an tenna and th e lu na r module upper su r fa ces . These re f l ec t i on s

e l i m i n a t e t h e l e s s - b r i g h t s t a r s as cand ida tes fo r use . Dur ing a l ignmento p t i c a l t e le s c o p e s i g h t i n g , t h e r a d a r a nt en na h ad d r i f t e d from i t s parkedp o s it io n i n t o t h e f i e l d of view of t h e t e l es co pe . The an tenna w a s re-p o s i t i o n e d b e f o r e c o n t i n u i n g w i t h t h e a l i g n m en t s .

A d i f f i c u l t y w a s exper ienced wi th t h e in te r im s towage assembly i nt h e lunar module cabin. I t s r e t a i n i n g b ra c k et s d i d no t h o ld s a t i s f a c -t o r i l y . The in te r im s towage assembly w a s c o n t i n u a l l y s l i p p i n g o u t oft h e a f t , u pp er r e s t r a i n t a nd i n t e r f e r i n g w it h c a bi n a c t i v i t y.n o a d eq u a te p l a c e t o stow used u r i n e bags; consequen t ly, they w e r e i nt h e way u n t i l such t i m e t h a t t h ey c ou ld b e p l ac e d i n j e t t i s o n bag s f o rd i spo sa l . The d i sp osab l e con ta iners and j e t t i s o n bags which were s towedi n t h e 16- ID^ camera compartment on t h e l e f t -hand s i d e f e l l ou t whi le t h ecamera w a s bei ng removed, cr ea t i ng a s h o r t delay dur ing hard -su i t opera -t i o n s .

"here w a s



9-10

Even though ex t ra veh icu la r p repara t ions an d p o s t - e x t r a v e h i c u l a rp rocedures were qu i t e adequa te , me t iculous e ff o r t i s r e q u i r ed t o p r op e rl ystow a la rg e number of luna r su rf ac e samples . Although t h e re i s adequatestowage sp ac e when samples are proper ly hand led , i t i s i m po s si b le t o e s t i -mate t h e nu mbe r, s i z e and sh ap e o f t h e sa mp le s p r i o r t o f l i g h t . Thus,much t i m e i s r e q ui r e d t o s o r t , weigh and stow a l l o f t h e mater ia l i n t h elunar module cabin i n accordance with stowage a rea w e i g h t c o n s t r a i n t s .Marking of w e i g h bags as they a r e so r t ed and s towed i s impor tan t .

Two hours a f t e r l an d i n g on t h e lunar sur face , the rendezvous radars a t i s f a c to r i l y per fo rmed th e command and se rv ic e module t r ac k i ng ex erc i se .

9 .lO .2 E g r e s s j I n g r e s s

Dur ing cab in depressur iza t ion , a c a b i n p r e s s u r e o f less t h a n 0 . 1 p s i aw a s r e q u i r e d b e f o re t h e c a bi n d oo r c o ul d b e ope ne d e a s i l y . The f i r s t pe r -son out. i s crowded as he egresses because t h e ha tch canno t be f u l l y openedt o t h e L u n a r Module P i lo t ' s s ide w i t h the other crewman s tanding b e h i n d

i t .h i s l e f t d ur in g e gr es s i n o rd er t o a void t h e ha tch s e a l . However, t h eha tch open ing i s adequa te .remember t o m a i n t a i n h o r i z o n t a l c l e ar a nc e i n o r de r n o t t o s c r ap e t h ep o r t a b l e l i f e support system and remote control uni t on t h e upper andlower hatch sea l s . T he se t ec h n i qu e s r e q u i r e p r a c t i c e b u t are worth t h ee f f o r t t o a s su re i n t e g r i t y o f t h e sea l .

The f i r s t person t o egress mus t remember, o r be coached, t o lean t o

Dur ing egress and ingress t h e crew must also

On previous miss ions , dust ca rr ie d i n t o t h e cab in dur ing ingress w a sa problem. However, i t d i d n o t seem t o be a problem on Apollo 1 4 , perhapsb e c a u s e t h e r e w a s l e s s d u s t on t h e lunar s u r f a c e , o r p e r h a ps , b e i n g a wareof t h e problem made th e crew more met iculous i n contaminat ion co nt ro l t h a nthey would have been othe rwi se. Care w a s t a k e n t o remove the dust from

th e p r ess ure garment a ssembly and o th e r equ ipment be fore en t ry i n t o t h ecabin.w a s adequate. The tec hniq ue of stomping t h e boots aga ins t th e lu nar mod-u le l ad der seemed t o he l p t o some ex te n t .

The brush that w a s used fo r p re ssu re ga rment a ssembly c lean ing

During egress a n d i n g r e s s , s t a b i l i t y a nd m o b i li t y w h il e on t h e l u n a rmodule l adde r i s adequate even when gras ping t h e l a d d e r with one hand.This leaves t h e ot he r hand fre e t o car ry equipment . However, one shouldmaneuver slowly and d e l i b e r a t e l y i n o rd e r t o a s s u r e s t a b i l i t y when nego-t i a t i n g t h e ' l u n a r module l a d d e r w i t h o ne ha nd .enced i n pas sing equipment from t he man on th e su r f ac e t o t h e man on thel a d d e r.more e a s i l y than i n one-g s imula t ions .

No d i f f i c u l t y w a s e x p e r i -

The lunar equipment conveyor and equipment transfer bag worked

..L

! -L, Y A,



9-11

9.10.3 Lunar Surface Operat ions

Mobil i ty. - Mobil i ty on t h e l u n a r s u r f a c e i s ex ce l l en t . Each crew-men employs a t e c h n i q u e f o r t r a v e l t h a t i s most s u i t a b l e f o r t h a t i n d i -vi du al . The step-and-hop g a i t a pp ea rs t o r e q u i r e a minimum of e f f o r t .The 1/6g s imula t ion s i n t h e KC-135 a i r c r a f t were a d eq u a te t o g i v e o ne af e e l of t h e l u n a r s u r f a c e g r a v i t a t i o n a l f i e l d . The zero-g experiencedon t h e way t o th e moon ai ded c onsider ably i n co ndi t ion ing f o r good mo-b i l i t y d u r in g o pe r at io n s i n 1 /6 g.over-control or use t o o much force when us ing t o o l s o r wa lking on th elunar s u r f a c e .

There w a s very l i t t l e t endency t o

Vi s i b i l i t y. - Vi s i b i l i t y on t h e lu n a r s u rf a c e i s very good when look-in g cross-sun. Looking up-sun, th e su rf ac e fea tures are obscured whend i r e c t s u n l i g h t i s on th e v i s or , a l though th e sunshades on th e l u n a r ex -t r a v e h i c u l a r v i s o r a ss em bl y h e lp e d i n r e d u c i ng t h e su n glare . Lookingdown-sun, vis ibi l i ty i s accep tab le ; h ow ev er , h o r i z o n t a l t e r r a i n f e a t u r e sare w ash ed o u t i n z e r o p h as e , and v e r t i c a l f e a t u r e s h av e r ed u ce d v i s i -

b i l i t y .A

f a c t o r i n r e d u ci n g down-sun v i s i b i l i t y i s t h a t f e a t u r e s a r ei n t h e l i n e o f s i g h t o f t h e i r shadows, t h u s r e du c in g c o n t r a s t . A crew-man's shadow appears t o have a h e i l i g e n s c h e i n a ro u nd i t . T h e v i s i b i l i t yon t h e l u n a r s u r f a c e a l s o d i s t o r t s ju dg me nt of d i s t a n c e . T he re i s ad e f i n i t e te nd en cy t o u n d er es ti ma te d i s t a n c e t o t e r r a i n f e a t u r e s . A nadequa te range f inder i s e s s e n t i a l .

Naviga tion .- Naviga tion appears t o have been th e most d i f f i c u l t p rob-l e m encounte red dur ing lunar s u r f ac e a c t i v i t i e s . U nex pected t e r r a i n fe a -t u r e s , as compared t o r e l i e f maps, w e r e t h e s o u r c e o f n a v i g a t i o n a l p r o b -l e m s . The r idges and val leys had an average change i n e lev a t i on o f ap-proximately 10 t o 1 5 f e e t . The landmarks that were clear ly apparent ont h e n a v i g a t i o n a l maps were n o t a t all apparen t on t h e su rf ac e. Even when

t h e crewmen climbed t o a r i d g e , t h e l a n d m a r k o f t e n w a s n o t c l e a r l y i ns i g h t . I n t e r p r e t a t i o n o f t h e p ho to gr ap hy c o n t r i b u t e s t o t h e n a v i g at i o nproblem because photographs of small craters make them appear much smallert h a n t h e y do t o t h e e y e . On t h e c o n tr a r y, b o u ld e rs r e f l e c t l i g h t s o t h a ti n t h e o r b i t a l p h o t og r ap h s t h ey a p p ea r much l a rg e r t h a n t h e y d o i n t h en a t u r a l s t a t e . Boulders 2 o r 3 f e e t i n s i z e sometimes a pp ea r i n t h eo r b i t a l ph ot og ra ph y, b u t c r a t e r s of t h a t s i z e a r e c o mp le te ly i n d i s c e r n i b l e

- ust.- Dust on t h e l u n a r sur face seemed t o be l e s s of a problem thanhad been an t ic i pa t ed . The dus t c l ing s t o s o f t , porous mate r ia l s and i seasily removed from m e t a l s .dust; however, most of t h e s u r f a c e d u s t c o u l d be removed. The l i t t l ed u s t t h a t accumulated on th e modular equipment t r an sp or te r could ea s i l ybe removed by brushing.i n g or rubbing with 'a glo ve t o make t h e map usable.

The pressure garments were impregnated w ith

The lunar map co l l ec te d dus t and req uir ed brush-



9-12

Timeline.- Operations o n t h e l u n a r s u r f a c e r e q u i r e d a much longert i m e t h a n h ad be en a n t i c i p a t e d . The p l an n e d a c t i v i t i e s r e q u i r e 25 t o30 perc ent more time than would be r eq uir ed under one-g co nd i t i on s .S ch ed ul in g a d d i t i o n a l a c t i v i t i e s , n t h e e ve nt t h a t c e r t a i n p or t i o n s o ft h e e x t r av e h i cu l a r a c t i v i t y h av e t o b e c a n c e l l e d, i s a d v i s a b l e .

9.10.4 L u n a r Module Interfaces

Modular equipment st ow we assembly.- The re le as e han dle w a s p u l l e dand th e assembly dropped t o a h e i g ht s u i t a b l e f o r op e r a t io n s on t h elu na r su rf ac e. The modular equipment stowage assembly w a s manuallya d ju s te d t o a higher p os i t io n t o remove t h e modula r equ ipment t r a ns -p o r t e r a n d r e a d j u s t e d t o *a l ow e r p o s i t i o n f o r s ub s e qu e n t o p e r a t i o n s .The height adjustments were made wi thou t d i ff i c u l ty . The thermal b l a n -k e t s were more d i f f i c u l t t o t a k e o f f t h a n h ad b ee n a n t i c i p a t e d . S im i-l a r l y, t h e t h e r m a l b l a n k e t s w hi ch p r o t e c t e d t h e m o du la r e qu ip me nt t r a n s -p o r t e r s u p p o r t e d i t s weight and manual removal of t h e bl an ke ts w a s re-qui red dur i ng modular equipment t r an sp or te r deployment.

As on previous f l i g h t s , a l l cab les used on t h e l u n a r s u r f a c e h a ds u f f i c i e n t s e t t o p re ve nt them f rom ly in g f l a t when deployed on th e lunarsu rfa ce . Both crewmen became ent ang led i n th e c able s f rom t i m e t o t im e.The cables emanating from t h e modular equipment stowage assembly areas h o u l d e i t h e r be b u r i e d o r r o u t e d th ro u gh r e s t r a i n i n g c l i p s t o k ee p themfrom bein g unde rfoot dur i ng work around t h e modular equipment stowageassembly.

S c i e n t i f i c e q u i p m e n t bay. - Both t h e d oo rs a nd t h e p a l l e t s were re -

However, t h emoved easily from t h e s c i e n t i f i c e qu ip me nt ba y by u t i l i z i n g t h e booms.The pal le ts could have been removed manual ly i f r e q u i r e d .h e i g ht o f t h e p a l l e t s w a s a t t h e l i m i t f o r eas y manual deployment on

l e v e l t e r r a i n .

The o ff load ing o f the Apol lo lunar su r face exper iment package w a ssomewhat hi nd er ed by a small c r a t e r 8 t o 10 f e e t t o t h e r e a r o f t h e l u n armodule. However, s u f f i c i e n t work ing area w a s a v a i l a b l e i n which t o p l a c ea p a l l e t a nd co nd uc t f u e l i n g o p e r a t i o n s .

S ince t h e l a nd i ng ge a r d i d n o t s t r o k e s i g n i f i c a n t l y d u r i n g t h e land-i n g , a j imp of about 3 f e e t w a s r e q u i r e d from t h e f o ot p ad t o t h e lowes trung o f t h e l a d d e r.a firm landing which would stroke t h e l a nd i ng g e a r a f e w inches wouldf a c i l i t a t e a manua l o ff l o a d i n g o p e r a t i o n as w e l l as egress and i n g r e s s .

T h i s p r o v id e d n o a p p r e c i a b l e d i f f i c u l t y ; h ow ev er,

. -A-

. I

L Y



9-13

9 .lo. L u n a r Surface C r e w Equipment

E x t r a v e h i c u l a r m o b i l i t y u n i t. - Both e x t r a v e h i c u l a r m o b i l i t y u n i t sperformed w e l l d u ri n g b o th o f t h e e x t r a v e h i c u l ar a c t i v i t i e s . There w a ss u f f i c i e n t c oo li ng i n t h e minimum p o s i t i o n f o r n orm al a c t i v i t y . Bothcrewmen were r e q u ir e d t o go t o intermediate, o r between minimum and i n -t e r m e d i a t e, f o r v a r i o u s p e r i o d s o f t i m e d u r i n g t h e c li m b t o C one C r a t e rand th e high-speed r et ur n from Cone Crater t o Weird Crater. However,o ther than dur ing these per iods , min imum cool ing w a s used predominant ly.

The Lunar Module P i l o t ' s pr es su re garment assembly evidenced a h i g h e r-than-usua l l eak r a t e f o r t h e f i r s t e x t r a v e h i c u l a r a c t i v i t y, d ro pp in g 0.25p s i d ur ing th e 1 -minu te check .checkout.

The s u i t s h a r e d no d r op d u r i n g p r e f l i g h t

The Commander's u ri ne co ll ec ti on tr a n s f e r assembly hose had a kinki n it which p r ev e n te d pr o pe r t r a n s f e r of t h e u r i n e t o t h e c o l l e c t i o n b a gs .B ef or e b o th e x t r a v e h i c u l ar a c t i v i t i e s it w a s n e c e ss a r y t o u nz ip t h e s u i t

and s t r a i g h t e n t h i s k in k o ut . I n one i n s t a n c e t h e s u i t w a s removed t ot h e w a i s t t o f a c i l i t a t e a c c e s s . The o nl y o t h e r m in or pr ob le m w i t h t h epr ess ur e garment assembly concerned th e Lunar Module P i l o t ' s r i g ht glove ."he glove developed an anomalous c ond i t ion bef ore th e second ex t rav eh icu-l a r ac t i v i t y which caused i t t o assume a n a t u r a l p o s it i on t o t h e l e f tand down.

I t should be n o t ed t h a t t h e w r i s t - r i n g a nd n e ck - r in g s e a l s on b o t h

A t t h a t t i m e , t h e r e was very l i t t l e evidence of g r i t o r d i r tpressure garment assemblies were lu br ic a t ed between ex t ra ve h ic u la r ac-t i v i t i e s .on the seals . L u b r i ca t i ng t h e s e a l s betw een e x t r a v e h i c u l a r a c t i v i t i e si s a p r o c e d u r e t h a t s h o u l d b e cont inued on subsequent missions.

Modular equipment tr an sp or te r. - The modular equipment tr an sp o r te rd e p l o y e d s a t i s f a c t o r i l y f r o m t h e l u n a r m o d u l e e x c e p t as p r e v i o u s l y n o t e d .The s p r i n g t e n s i o n on t h e r e t a i n i n g c l i p s w a s s u f f i c i e n t t o ho ld a l l t h eequipment on th e modular equipment t r an sp o rt er d urin g lun ar s ur f ace ac-t i v i t i e s . However, wi th th e t r an sp or te r un loaded , t h e re tacining spr ingsh av e s u f f i c i e n t t e n s i o n t o lift it c l e a r o f t h e lunar su rf ac e when plat-

in g equipment i n s towage loc a t i on s .t r a n s p o r t e r w a s f u l l y l o a d e d .

This w a s n o t n o ti c ed a f t e r t h e

The wheels d id not k ick up or s t i r up as much dust as expected be -Very l i t t l e d u s t accumulated on t h e modular equipmento re t h e f l i g h t .

t r a n s p o r t e r .

The modular equipment transporter w a s s t a b l e , eas i ly p u l l e d , a n dp r ov e d t o b e a very handy d ev ic e f o r b o th e x t r a v e h i c u l a r a c t i v i t i e s .Only a t m a x i m u m s pe ed s d i d t h e t r a n s p o r t e r e vi de nc e any i n s t a b i l i t y



9-14

and , then , on ly because o f rough te r ra in . This i n s t a b i l i t y w a s e as y t oc o n t r o l by h a nd mot ion on t h e t r i angu la r- shaped tongue .

Hand too l ca r r i e r. - The h a n d t o o l c a r r i e r mated t o t h e m odular ,

equipment t r anspor te r w e l l , an d w a s a d eq u a te l y r e t a i n e d by t h e ha nd t o o lc a r r i e r r e t a in i n g c l ip . A l l stowage areas excep t the deep pocke t were

a c c e p t a b l e . This pocket w a s v er y d i f f i c u l t t o r e ac h when s t a n d i n g ad ja -cen t t o th e modula r equ ipment t r an sp or te r. I t i s t o o d eep f o r one t oe a s i l y r e t r i e v e small items. With t h i s e x ce p ti o n, t h e h an d t o o l c a r r i e rpe rf orme d s t i s f a c t o r i y .

Cameras .- A l l cameras c a r r i ed in t h e lu n a r module worked we ll . Onlytwo anomalies were not ed. On t h e Commander's cam era, th e screw whichr e t a i n s t h e h a nd le and t h e r em ot e c o n t r o l u n i t c l i p worked l o o s e s e v e r a lt i m e s an d ha d t o b e r e t i g h t e n e d .magazine which Jammed and produced only 30 f e e t o f usable f i l m .

The second anomaly concerned a 16-ITU~

The t e l e v i s i o n camera pe rf or me d s a t i s f a c t o r i l y . I t seems t o be au s e fu l t o o l f o r lunar s u r f a c e e x p l o r a t i o n . A remotely operated camera

w i t h adjustment of focus , zoom, and len s se t t in g con t ro l l ed f rom t h eground would be v er y u s e f u l i n making a v a i l a b l e l u n a r s u r f a c e t i m e p r es -e n t l y r e q u i r e d f o r t h e s e t a s k s .

S-band e re ct ab le antenn a.- The S-band an tenn a was e a s i l y o f f l o a d e dfrom t h e lunar module and pr ese nte d no problems i n deployment e xcep t t h a tt h e n e t t i n g which forms t h e d i s h caught on t h e feed horn and h a d t o ber e l ea sed manual ly. The antenna ob st ru ct s t h e work area immediatelyaround t h e modular equipment stowage assembly. A longer cable wouldallow deplayment at a greater d i s t a n c e from t h e lunar module. Althought h e deployment and er ec ti on of t h e S-band antenna i s a one-man j o b , t h eantenna i s more eas i ly a l igned w i t h t h e two crewmen cooperating.

L u n a r s u r f ac e s c i e n t i f i c eq uip men t .- Off load ing of t h e Apol lo lun arsu rf ac e experiments subpackages w a s normal, and a l l opera t ion s were ad-e q u a te e x c ep t f o r t h e o p e r a t i o n o f t h e dome removal tool.s e v e r a l a t t em p ts t o lock the dome removal tool onto t h e dome. Duringt h e t r a v e r s e t o t h e Apollo lunar surface equipment package deployments i t e , t h e p a l l e t s on e i t h e r e nd of t h e mast o s c i l l a t e d v e r t i c a l l y andt h e m a s t f l e x e d , making t h e assembly d i f f i c u l t t o c a r r y and t o h o l d i nt h e hand s. However, t h e arrangement i s a c c e p t a b l e f o r t r ave r se up t oapproximately 150 ya rd s. '

I t r e q u i r e d

There w a s some d i f f i c u l t y i n f i n d i n g a s u it a bl e s i t e f o r A po ll olunar surface experiments package deplayment because of u n d u l at i o n s i nt h e t e r r a i n .c o n s t r a i n t s t h a t had been placed on Apollo lunar surface experiments

I t w a s n e c e ss a r y t o s p en d seve ra l moments c o n s i d e r i n g t h e

? -

L? -L

PA- Y

. -L



9-15

package deployment and m at ch in g t h o s e t o t h e s i t e i n o r d er t h a t t h e ex-periments could be properly deployed. A f t e r t h e s i t e h a d b ee n s e l e c t e d ,t h e lunar dus t pre sen ted some problems f o r th e remainder of t h e Apollolu na r su rf ac e experiments package deployment . The sup rat her mal . o n de-t e c t o r ex p er im e nt s u b - p a l l e t h a d d u s t p i l e d up a g a i n s t it and i n t o t h eh idden Boyd b o l t , which must be reached b l in d wi th t h e hand to o l .a l minutes were was ted before the supra thermal ion de tec to r exper imentw a s s u c c e s s f u l l y re leased from t h e s u b - p a ll e t . S ub seq ue nt t o t h a t , t h esupra thermal ion de tec to r exper iment w a s c a r r ie d t o i t s deployment s i t ea n d a d d i t i o n a l d i f f i c u l t y w a s exper ienced i n han d l ing t he th re e compo-n e n t s o f t h i s ex p er im e nt s i m u l t an e o u s l y. The s u p r a t h e rm a l i o n d e t e c t o rexperiment w a s n ot s u f f i c i e n t l y s t a b l e t o pr ev en t it f rom tu rn ing overs e v e r a l t i m e s during deployment.

Sever-

No problems were exp eri enc ed du ri ng removal of the mor ta r pack .During dep loyment , however, t h e foo tpads ro ta te d ou t o f th e p roper pos i -t i o n , a nd t h e p ac ka ge h a d t o be p i c ke d up a nd t h e p ad s r o t a t e d t o ap o s i t i o n i n which t h e y would r e s t p r o p e r l y a g a i n s t t h e s u r f a c e .

The thumper deployed as e x p e c t e d , b u t t h e lunar r e g o l i t h w a s s ol o o s e t h a t t h e c e n t e r g e o p h o n e w a s pul led ou t d ur ing dep loyment o f th el a s t ha l f o f th e thumper cab le . Th is w a s conf i rmed dur ing re tu rn a longt h e l i n e . Only 1 3 o f t h e 2 1 thumper ca r t r idges were f i r e d a n d t h e f i r s ts e v e r a l o f t h e s e r e q u i r e d a n e x t r a o r d i n a r y amount o f f o r c e t o f i r e th em( s e c t i o n 1 4 . 4 . 1 ) .i n i t i a t o r s and t h e eq uip men t o p er a te d p r e c i s e l y as expec ted .

The problem seemed t o c le a r up f o r th e l a s t s e v e r a l

L a s e r r a n gi n g r e t r o - r e f l e c t o r e x pe r im e nt .- The l a s e r r e f l e c t o r w a sd e pl o ye d an d l e v e l e d i n t h e n or ma l f a s h i o n and i n t h e p r e s c r i b e d l o c a -t i on . The dus t cover w a s rem oved , t h e l e v e l r e c h e ck e d , a nd t h e u n i tphotographed.

So la r wind composi t ion experiment .- No d i f f i c u l t y w a s exper iencedi n e re c t io n o f th e so la r wind composi t ion exper iment . The on ly anomalyo c c u r r e d d u r i n g t h e r e t r i e v a l o f t h e a p p a r a t u s , at which time i t r o l l e dup only about half way and had t o be manua l ly ro l l ed the remainder o ft h e d i s t an c e .

Lunar portable magnetometer experiment .- T h i s p i e c e of equipmentp er fo rm ed q u i t e s a t i s f a c t o r i l y .r e e l i n g i n of t h e c a b l e s .r e wi n d; c o n s e q u e n t ly, t h e c a b l e was a ll ow ed t o p r o t r u d e i n l o o p s fromt h e r e e l d u r i n g t h e r em ai nd er o f t h e t r a v e r s e ( s e c t i o n 1 4 . b . 3 ) .

The o n l y d i f f i c u l t y e x p e r i e n c e d w a s t h eThe s e t i n t h e c a bl e p re v en t ed a s u c c e s s f u l

Geology.- The geology hand t o o l s are good and, i f t i m e h a d p e r m i t t e d ,they would have all been used. As i n p rev io us miss io ns , th e hammer w a s



9-16

u s ed b y s t r i k i n g w i t h t h e f l a t of th e hammer ra th e r than t he small end.The on ly d i sc repancy as so c ia te d w i t h the geo logy t o o l s w a s t h e use oft h e geology sample bags. I t w a s d i f f i c u l t t o f i n d r ocks small enought o f i t i n t o t h e small s am pl e b a g s. F u rt he r mo re , t h e y a r e h a r d t o r o l lup. The t a bs which shou ld f a c i l i t a t e ro l l in g up th e bags become en-tang led , making i t d i f f i c u l t t o remove them f r o m t h e d i s p e n s e r.

9.10.6 Lunar Sur face Sc ience

Geo10a.- The appearance o f the lunar su r face w a s much as expec ted .A loose g ray mant le o f mater ia l c ov er ed t h e e n t i r e s u r f a c e t o an u n de t e r-mined dep th ; however, co re t ubes d r iven i n t o th e s u r f ace would no t pene-t r a t e more than 1-1/2 t u b e l e n g t h s a n d , i n most c a s e s , c o n s i d e ra b l y l e s st h a n t h a t . A " ra in d rop" pa t t e r n over mos t o f the re go l i th w a s observedand i s c l ea r l y shown i n pho tographs . Also o bs e rv ed , i n c e r t a i n s e c t i o n sof t h e t r a v e r s e , were small l i n e a t i o n s i n t h e r e g o l i t h m a t e r i a l , whichc an b e s e e n i n c e r t a i n p h o t o gr a p hs .

There w a s e v i de n c e o f c r a t e r i n g an d r e c r a t e r i n g on a l l of t h e areat h a t w a s t r a v e r s e d . T h e r e w a s no s u r f a c e e vi d e nc e of m u l t i p l e l a y e r s .Even i n t h e c r a t e r s , t h e l o o s e g r a y m a n t l e c o v e r e d t h e e n t i r e s u r f a c e ,except where rocks prot rud ed through, and concealed any evidence of s t r a -t i g r a p h y.d i f f e r e n t l a y e r s was found. In one o r two pl ac es on t h e flank of ConeCrater t h e crewmen's boots dug through the upper layer exposing a w h i t el a y e r a b o u t 3 inches from t h e s u r f ac e . I t i s i n t e r e s t i ng t o n ot e t h a tv e ry few r oc k s a r e e n t i r e l y on t h e l u n a r s u r f a c e ; most a r e b u r i e d o rp a r t i a l l y b u r i ed . N ea rl y all r oc ks of any s i z e ha ve s o i l f i l l e t s a rou ndthem. The s m a l l rocks are g e n e r a l l y c o a te d w i t h d i r t , b u t some of t h el a r g e r rocks are no t. Many of t h e l a r g e r r o c k s u r f a c e s a r e soft andcrumbly. However, when one us es t h e hammer a nd br ea ks th ro ug h t h i s , i t

i s found t h a t they a re hard undernea th .

I n t h e t r e n c h d u g b y t h e crew, however, evidence of three

S u b t l e v a r i a t i o n s i n r o ck s are n o t e a s i l y d i s c e r n i b l e , p r i m a r i l y be-c a us e o f t h e d u s t . I t must be remembered that t h e c r e w s e l e c t e d c a n d i d a t esamples a f t e r having observed th e rocks f rom a t l e a s t 5 o r 6 f e e t awayi n o r d e r t o p re v en t d i s t u r b i n g t h e s o i l ar ou nd them . F e a t u r es w hich a r eobvious i n a hand-he ld specimen a re no t d i s ce rn ab l e a t i n i t i a l v iewingd i s tanc e . Fur the rmore , once th e rock has been sampled , good u t i l i z a t i o nof t i m e p r e c l ud e s e xa m in in g t h e r o c k e x c ep t t o n o t e i t s more prominentf e a t u r e s . The p o i n t i s t h a t o nl y t h e c h a r a c t e r i s t i c s of a rock t h a t a r ed i s c e r n i b l e at t h e i n i t i a l vie wi ng d is t an c e e n t e r i n t o t h e d e ci s io n t osample.v a r i e t y of samples i s d e s i r e d .

Sampl ing s t ra tegy shou ld allow f o r t h i s l i m i t a t i o n when a wide

The crew did observe, however, t h e evidence of b re cc ia i n some oft h e ro c k ; e n d , on a f e w o c c a s i o n s , c r y s t a l l i n e s t r u c t u r e w a s e v i d e n t . I n

. .I L



9-17

most c a s es , t h e c r y s t a l s were small.seen on the lunar s u r f a c e at Fra Mauro. I n one s m a l l c r a t e r t h e r e seemedt o b e g l a s s - l i k e s p a t t e r on t h e b otto m. I n t h e t r a v e r s e t o t h e r i m ofCone Cr at er , one 3-foot rock was observed t o be wel l coa ted with "glass " .

Only on two occasions w a s g l a s s

The popu lat io n of rocks i n t h e Fr a Mauro area w a s s u r p r i s i n g l y l o w,much l e s s t h a n 0 . 5 percen t o f t h e t o t a l area.i n e v i d e n ce w er e 3 t o 5 c e n t i m e t e r s o r sma l l e r and , be ing covered w i t hd i r t , were i n many c as es i n d i s ti n g u i sh a b l e f rom i r r e g u l a r i t i e s i n t h es u r f a c e o r f rom clumps of s o i l .Cone Cra te r, bould ers became more prominent . In th e bou lde r f i e l d , onth e sou thea s t edge o f Cone, th e bou ld er popu la t ion reached , pe rhaps , 3t o 5 percen t o f t h e en t i r e su r face , wi th many boulders undoubtedly be ingc o n c e a l e d j u s t b e l o w t h e s u r f a c e . Rays were no t d i s ce rn ib le on th e edgeo f t h e c r a t e r s , p o s s i b l y be ca us e o f t h e l ow p o p u l a t i o n a nd a l s o b e c au s e

Predominan t ly, the rocks

A s t h e crew p r og r e ss e d t o t h e c r e s t o f

' t h e n e a r e s t h o r i z o n w a s seldom more th an 150 f e e t away.

. S o i l mechan ics. - Foo tp r in t s on th e l una r su rf ac e were not more than

1 / 2 in c h t o 3/4 i n c h d e ep e xc ep t i n t h e r i m s o f c r a t e r s , w he re , a t t i me s ,they were 3/4 inch t o 1-1/2 inches deep.p o r t e r t r a c k s were seldom more than 1 / 2 inch deep.e a s i l y p ushed i n t o t h e l u n a r s u r f a c e almost t o t h e l i m i t of the penetrom-e t e r r o d . D ur in g t h e t r e n ch i n g o p e r a t i o n , t h e t r e n c h w a l l s would not re-main in tac t and s t a r t e d crumbl ing shor t ly a f t e r t h e t r e n c h w a s i n i t i a t e d .When ob tai nin g one core tub e sample, t h e s o i l d i d n o t compact and s p i l l e dfrom the tube upon withdrawal .

The modular equipment trans-The penetrometer w a s

9.11 ASCENT, RENDEZVOUS, AND DOCKING

Although the ingress a t t h e c o n c l u s i o n o f t h e s e c o n d e x t r a v e h i c u l a rp e r i o d w a s approximately 2 hours a he ad o f t h e t i m e l i n e , an h o ur o f t h i spad w a s used up i n s towing samples and equipment pre par ato ry t o lift-o f f . The remaining hour assured adequate t i m e f o r c r e w r e l a x a t i o n a n da n e a r l y s t a r t on pre-ascent procedures . There were no de vi at i on s fromt h e c h e c k l i s t , a lt ho u gh a standby procedure w a s a v a i l a b l e i n t h e e v e ntof subs eque nt communications problems. Li ft- of f occ urr ed on t i m e . Asi n p r e v i o u s m i s s i o n s, d e b r i s from t h e i n t e r s t a g e area was e v i d e n t a ts t a g i n g . I n a d d i t i o n , a t docking, the Command Module Pilot reported at e a r i n a s c e n t s t a g e ' i n s u l a ti o n on t h e b ot to m r i g h t s i d e o f t h e lunar

module ascent s t age ( s e c t i o n 8.1).

Ascent w a s comple tely nomina l wi th au to ig n i t i on and cu tof f . Bothguidance systems performed wel l .an adjustment maneuver which w a s performed a t 141:56:49.4 u s i n g t h e r e -ac t i on con t ro l sys tem. The ad jus tment d e l t a v e l o c i t y w a s moni to red wi thboth guidance systems.

The Mission Control Center voiced up



9-18

9 . 11 . 1 Rendezvous

F o l l o w i n g t h e a d j u s t m e n t f i r i n g , a manual maneuver w a s made t o t h et r a c k i n g a t t i t u d e a nd re nd ez vo us n a v i g a ti o n p r o c e du r e s w er e i n i t i a t e d .For th e backup char t s , an e lapse d t i m e of 4 minutes 3 seconds w a s a v a i l -able ( f rom th e beg inn ing of th e ad jus tment maneuver u n t i l t h e re qu i redt e r m i n a l p h as e i n i t i a t i o n minus 30 minutes rendezvous ra dar mark) . Thisproved t o b e i n s u f f i c i e n t t i m e t o complete th e r eq uir ed p rocedures com-fo r ta b ly . The backup char t s shou ld be rev i se d t o permi t ample t i m e t oo b ta in t h i s f i r s t mark. The guidance systems were upda ted ind epe nd entl yu si ng t h e i r r e sp e ct iv e i n s e r t i o n s t a t e v e ct o rs as i n i t i a l c o nd i t io n s.Nineteen marks were obt ain ed wit h t h e primary guidance system. The ab or tguidance system updates were commenced a t t e r m i n a l p h a s e i n i t i a t i o n m i n u s27 m i nu te s an d c on t in u ed t o t e r m i n a l p h a se i n i t i a t i o n minus 7 minutes a twhich t i m e the maneuver solut ion w a s compared. E i g h t marks were enteredi n t o th e abort guidance system. The so lu t i on s from both lu na r moduleguidance systems compared extremely w e l l , agree in g on l ine -of - s igh t ang leswi th in 0 .3 degree and o n t o t a l d e l t a v e l o c i t y w i t h i n 1 .6 f t / s e c .o f VHF d i f f i c u l t i e s ( s e c t i o n 1 4 . 1 . 4 ) , t h e command module c om puter w a s

u p da te d w i th s e x t a n t mark s o n ly, p r i o r t o t e r m i n a l ph as e i n i t i a t i o n andproduced a maneuver solution of minus 67.4, p l u s 0 . 5 , minus 69.2 (un-cor rec t ed) compared wi th t h e p r imary gu idance nav iga t ion sys tem so lu t io no f p l u s 6 2 . 1 , p l u s 0 . 1 , p l u s 63.1.pr imary gu idance nav iga t ion sys tem so lu t i on w a s s e l e c t e d f o r t h e m a n e u v e r,a n d t h e c o r r e s p o n d i n g r o t a t e d v e c t o r w a s e n t e r e d i n t o t h e a b o r t g u id an cesystem. The ascen t p ropu ls ion sys tem te rm ina l phase i n i t i a t io n maneuverw a s execu ted wi thou t in c id en t . A s a n t i c i p a t e d , t h e g ui d ed a s c en t pr o -pu ls io n sys tem shutdown re su l t ed i n a s l i g h t u nd er bu rn .

Because

Using a two-out-of- three vo te , t h e

S ub se qu en t t o t e r m i n a l p ha se i n i t i a t i o n , b o t h lunar module naviga-t i o n s o l u t i o n s were r e i n i t i a l i z e d a nd t r a c k i n g w a s resumed. Simultane-o u sl y, t h e command module VHF t r a c k i n g w a s found t o be o p e r a t i n g a n d

b o t h s e x t a n t a n d VHF marks were e nt er ed i n t o th e command module computer.The f i r s t midcourse so lu t ion i n th e p r imary gu idance nav iga t ion sys temw a s used. The abort g ui da nc e s y st em s o l u t i o n f o r t h e f i r s t m id co ur sec o r r e c t i o n was i n e xc es s of 5 f t / s e c ; c o ns eq u en tl y, t h i s s o l u t i o n w a sdiscarded and abor t gu idance sys tem nav iga t io n w a s cont inued wi thou tr e i n i t i a l i z a t i o n . A t th e second midcourse cor rec t io n , th e p r imary gu id-ance nav iga t ion system so lu t i on w a s used , and t h e abor t gu idance sys tems o l u t i o n w a s w i t h i n 2 f ' t / sec .

The l un ar module remained ac t i ve dur ing br ak ing and th e rendezvousw a s completed without in ci de nt . Af te r p a s s in g t hr o ug h t h e f i n a l b r ak i n gga te , th e l un ar module began s t a t io n keeping on th e command and ser vi cemodule. The Command Module Pi lot executed a 360-degree p it c h maneuver.No anomalies were observed durin g t h e i ns pe ct i on of t h e command and



9-19

se rv ic e modules . Consequently, th e Commander p roceed ed w it h t h e pr e-docking maneuver consis t ing of a 90-degree p it ch down and r i g h t yaw t obr in g t h e l un ar module docking ta rg et i n t o th e Command Module P i l o t ' sf i e l d o f v iew. A t t h i s p o i n t i n t h e mi s s io n , t h e a b o r t g ui da nc e dis -p l ay s w ere b la nk an d t h e f l i g h t d i r e c t o r a t t i t u d e i n d i c a t o r , d r i v en bythe abor t gu idance sys tem, w a s s t i l l i n d i c a t i n g 15 0 degrees p i t ch andzero yaw. Eff or t s t o re s to re th e abor t gu idance system t o o p e r a t i o nwere u n s u c c e s s f u l ( s e c t i o n 1 4 . 2 . 5 ).module active w a s completed un eventfu l ly , d e s p i t e e a r l i e r c o n c e r n a b o u tthe docking mechanism.

Docking with the command and service

The t r a n s f e r of crew and equipment t o t h e command and s er vi ce moduleproceeded on schedule but w ith some concern reg ard ing th e t i m e remainingt o comple te ass igned ta sk s . The t i m e a l l o t t e d p r ov ed t o b e a d eq u at e bu tnot ample. The proce dures f o r contam ination co nt ro l i n th e command mod-u l e were q u i t e s a t i s f a c t o r y, a nd p a r t i c l e s w er e n o t o b se rv ed i n t h e com-mand module subseq uent t o hatc h op ening.

9.12 COMMAND AND SERVICE MODULE LUNAR ORBIT ACTIVITIES

9.12.1 Ci rc ul ar iz at io n and Plane Change Maneuvers

Two service propuls ion system f i r ings were made during the commandand se rv ic e module so lo phase. The ci rc ul ar iz at io n maneuver, which plac edt h e command and s e r v i c e module i n approximately a 60-nau t ica l -mi le c i r-c u l a r o r b i t , w a s a 4-second f i r i n g p e rf o rm ed a f t e r s e p a r a t i n g f rom t h elu n a r module. The maneuver w a s con t ro l l ed by th e gu idance and con t ro lsystem an d r e s u l t e d i n a 2.0 f t / sec overspeed , which w a s t rimmed t o1 . 0 f t / s e c . S ub se qu en t t o t h i s m an eu ver, a ch an ge t o t h e c o n s t a n t s i n

th e command module computer sh or t f i r i n g lo g ic w a s uplinked by the M i s -si on Con tro l Center . The pla ne change maneuver w a s nominal with an 18-s ec o nd f i r i n g c o n t r o l l e d by t h e g u i da nc e a nd c o n t r o l s ys te m.

9.12 .2 Landmark Tr ac kin g

A l l t r a ck i ng , wi th th e excep t ion of th e lun ar module on revo l u t io n17, w a s do ne u s i n g t h e t e l e s c o p e w it h t h e 16-1~t1 d a t a a c q u i s i t i o n c a m e r amounted on t h e se xt an t. Fourteen landmarks were tr ac ke d by t h e commandand service module, t w o o f t h e s e n e a r p e r i g e e w h i l e i n t h e 6 0- by 8-naut ica l -m i le o rb i t . The low-a l t i tude l andmark t ra ck i ng w a s accomplishedw i t h no s i g n i f i c a n t d i f f i c u l t i e s . A c q u is i t io n of t h e t a r g e t w a s no prob-l e m and the manual opt ics d r i v e p r o vi d ed c o n s t a n t t r a c k i n g o f t h e l an d -mark through nadir.



9-20

Landmark DE-2 was n ot t r a c k e d s a t i s f a c t o r i l y. The h i gh su n a n g l ea t t h e t im e o f t r a c k i n g p r e v en t e d a c q u i s i t i o n of t h e landmark. Anotherlandmark i n t h e area of DE-2 w a s t r a c k e d a n d i d e n t i f i e d f r o m t h e 16-I-III~photographs.With the except ion of DE-2, a l l o f t h e g r a p h i c s f o r t h e l an dm ar k t a rg e t swere v e r y s a t i s f a c t o r y.

A l l of the o the r l andmarks were t r a c k e d q u i t e e a s i l y.

The l u n a r module, on t h e s u r f a c e , w a s t r acked on revo lu t ion 1 7 .The sun re f l ec t ing f rom the lunar module as w e l l as the long shadow oft h e l u n a r module made i d e n t i f i c a t i o n p o s i t i v e . A c q u i s i t i o n of t h e lunarmodule w a s accomplished by using the s i t e map i n t h e l u n a r g r a p h i c s b o o kand i d e n t i f i c a t i o n of s u r f a c e f e a t u r e s i n t h e l a n d i n g a r e a . A ls o , onr e v o l u t i o n 29, between scheduled landmarks, the lunar module w a s aga inacquired by manual opt ics .i n g o f f t h e A po ll o lunar sur fac e exper iment package s t a t i on .

A t t h a t t i m e , t h e su n c o ul d b e s e e n r e f l e c t -

9.12.3 Bo ots tra p Photography

The lu na r topographic camera w a s used on revolut ion 4 o o b ta i np i c t u r e s of th e p roposed Descar tes l an d ing s i t e from the l o w or b i t . Ap-proximately one- third of t h e way in t o t h e photography pa ss , a l o u d n o i s edeveloped i n th e camera. The camera counter cont inu ed t o count and t hephotography pass w a s completed. One e n t i r e magazine w a s exposed. Sub-s e qu e nt tr o u bl e s h oo t i ng e s t a b l i s h e d t h a t t h e s h u t t e r w a s n o t o p e r a t i n gp r o p e r l y ( s e c t i o n 14.3.1) .topographic camera were of the lunar module landing on the surface.

The o nl y o t h e r p i c t u r e s t a k e n w it h t h e l u n a r

The f l i g h t p l a n w a s changed s o tha t th ree pho tography passes on theDescar tes s i t e were made us ing t h e 500-mm l ens on the 70-mm Hasse lb ladcamera mounted on a bra cke t i n window 4 ( f i g . 9-2) . The Descartes s i t ew a s t r a cke d manual ly wi th th e c rew op t i ca l a l ignment s i gh t and th e camera

manua lly opera ted t o expose a frame every 5 second s. The ground su pp li edi n e r t i a l a ng le s and t im e s t o s t a r t the camera and the spacecraf t maneuver.The spacecra f t was maneuvered i n minimum impuls e t o keep th e crew o p t i c a lalignment s i g h t on t h e t a rg e t .r e v o l u t i o n 34 t o photograph t h e ar ea near Lansburg B where the Apol lo 13S-IVB impacted.

These same procedures w e r e a l s o used on

A v e r t i c a l s t e r e o s t r i p wa s obta ined on revo lu t ion 26 u s i n g t h e70-mm Hasse lb lad a n d 80-mm l e n s .a lm o st t h e e n t i r e g ro un d t r a c k from t e r m i n a t o r t o t e r m i n a t o r.op t i ca l a l ignment s igh t maneuver w a s accomplished a t t h e e n d of t h e s t r i pf o r c a ne r a c a l i b r a t i o n .

T hi s v e r t i c a l s t e r e o s t r i p encompassedA crew

. -L

7 'L



9-21N A S A - S - 7 1 - 1 6 5 2

Figure 9-2.- Lu nar s u r f a c e f e a t u r e s i n D e s c a r te s l a n d i n g s i t e area .

9.12.4 O r b it al Science Hand-Held Photography

A p p r o x i m a t e l y h a l f t h e p l a n n e d t a rg e t s f o r o r b i t a l s c i e n c e h a n d - h e l dphotography were d e le ted because of th e f l i g h t p lan change t o use crewo p t i c a l a l ig n me n t s i g h t t r a c k i n g of t h e D e s c a rt e s s i t e . There were threes t e r e o s t r i p s t ak en w i th t h e 500-mm le ns u sin g th e hand-held mode( f i g . 9-3). The r i n g s i g h t w a s u se d t o i m pr ov e t h e s i g h t i n g a c cu r a cy.U t i l i z a t i o n o f t h e cam era i n t h i s mode w a s q u i t e a c c e p t a b l e as long as



9-22YA S A - S - 7 1 - 1 6 5 3

a. Western p o r t i o n o f King c r a t e r w i t h smaller c r a t e ri n l e f t fo reground hav ing an 0.8-mile diam eter and

l o c a t e d 3 2 . 4 miles f ro m c e n t e r o f K in g c r a t e r .

F i g u r e 9-3.- S e l e ct e d s t e r e o s t r i p ph ot og ra ph s from l u n a r o r b i t .

t h e s p a c e cr a f t a t t i t u d e was s a t i s f a c t o r y f o r t a r g e t a c q u i s i t io n . D uringt h i s f l i g h t , a l l hand-held photography was t a k e n a t t h e s p a c e c r a f t a t t i -t u d e d i c t a t e d b y o t h e r r e q u ir e m en t s. On a few of t h e t a r g e t s , t h e a t t i -tude made it d i f f i c u l t t o s a t i s f a c to r i l y a cq ui re t h e t a r g e t a t t h e p r o pe rtime out of any window.



9-23

During t h e hand-held photography and a l s o d u r i n g t h e crew o p t i c a la li gn m en t s i g h t t r a c k i n g , a v a r i a b l e i n t e r v a l o m e t e r wo ul d c e r t a i n l y h av ebeen an asse t . A s i n g l e - l e n s r e f l e x cam er a w ou ld g r e a t l y s i m p l i f y t h ep o i n ti n g t a s k . Having o r b i t a l s ci en ce t a r g e t s l i s t e d i n t h e f l i g h t p la n ,a t t i m e s t h e y are a v a i l a b l e , i s c e r t a i n l y more p r e f e r a b l e t h a n j u s t l i s t -i ng them as t a r g e t s o f o p p o r tu n i ty. T hi s i s t r u e o f b o t h p h o t o gr a p h i cand v i s u a l t a r g e t s .

NASA-S-71-1654

b . C e n t r a l p o r t i o n o f 4 1-m ile d i a m e t e r K ing c r a t e r .

F i g u r e 9-3.- Continued.



9-24

NASA-S-71-1655

c . Eas t e rn po r t i on o f King c r a t e r pho tographed f rom 178 m i l e s a w a y.

F igure 9-3.- Concluded.

9 . 1 2 . 5 Zero-Phase Observations

The camera conf igurat ion w a s changed f rom t h a t l i s t e d i n t h e f l i g h tp l a n b e c au s e t h e t e l e m e t r y c a b l e w a s no t long enough t o r each t he cameramounted i n t h e hat ch window.t o t h e f l i g h t b ec aus e th e b r ac ke t a r r i ve d l a t e and n o b r a c k e t was a v a i l -a b le f o r t h e s i m u la t or .

T h i s c o n f i g u r a t i o n w a s n o t c h ec k ed p r i o r

A mark w a s g iven ove r t h e i n t e r c o m a n d / o r t h e



9-25

air-to-ground loo p on t h e f i r s t and l a s t camera actuat ion of each pass .I t w a s noted th a t th e camera opera ted c los e t o ze ro phase on each t a r -g e t . E igh t separa te areas were l i s t e d f o r z er o- ph as e o b s e r v a ti o n s b u tonly s i x of th ese were observed.sul t of a f l ig h t p lan change.of t h e moon and two were on t h e f r o n t s i d e . There w a s a s i g n i f i c a n t d i f -f er en ce i n t h e a b i l i t y t o o bser ve t h e t a r g e t s a t zero phase between theback-side and f ron t - s ide t a rg e t s . The two s ign i f i can t pa ramete rs arealbedo and s t r u c t u ra l r e l i e f , o r co nt ra st . Because of th e lack of con-t r a s t i n r e l i e f on the back s i d e , t h e t a r g e t s w e r e d i f f i c u l t o r , i n somecases , imposs ib le t o observe a t ze ro phase .t a r g e t , o n e a t zero phase and one a t low phase, ar e s h a m i n f ig u re 9-4.The two f ro n t - s id e t a rg e t s were c r a t e r s l o c a t e d i n a mare sur face . Thes t r u c t u r a l r e l i e f b etw een t h e f l a t s u r f a c e and t h e c r a t e r r i m made t h et a rg e t s m o r e v i s i b l e a t zero phase.

The other t w g were cancel led as a re -Four of t he t a r ge t s were on the back s i de

Two views of a back-side

9.12.6 Dim-Light Photography

The window shad e f o r th e righ t-han d rendezvous window w a s e as y t oi n s t a l l a nd ap pe ar ed t o f i t proper ly. In add i t ion t o us ing th e windows ha de , t h e f l o o d l i g h t s n e a r t h e right -han d rendezvous window were ta pe d.The green shu t te r ac tua t ion l i g h t on t h e camera w a s t aped and , i n g en -e r a l , all s p a c e c r a f t l i g h t s w ere t u r n ed o f f f o r t h e d i m - l i g h t photog-raphy '

A l l of t h e procedures were completed as l i s t e d i n t h e f l i g h t p la n.The only discrepancy noted w a s on th e ea r t h dark-s ide photography.w a s c o n s i d e r a b l e s c a t t e r e d l i g h t i n th e s ex ta n t when i t w a s p o i n t e d a tt h e d ar k p o r t i o n o f t h e e a r t h .ea r th ' s c r es c en t i n t h e s e xt a nt .

There

There w a s a l s o a double image of t h e

9.12.7 Cammunic a t i o n s

Communications between the command and service module and theManned Space Flight Network were marginal many times w h i le i n l u n a ro r b i t .s m a l l adjustment of the angles w a s the d i ffe rence be tween hav ing a goodccmmunication lockup or no ac qu is it io n a t all ( s e c t i o n 14 .1 .2 ) .

The high-gain antenna poi nt in g an gles were v e r y c r i t i c a l ; a very

The separate communications loop for t h e command and service moduleshou ld be ac ti v at ed soon af te r command module/lunar module se pa ra ti on .The time between separation and touchdown i s an extremely busy time f o rthe lunar module and any pro lon ged communication wi th t h e command ands e r v i c e m o d u l e i s d i f f i c u l t , i f n o t i mp o ss ib le .t h e lunar module were good a t t h e t i m e of separat ion and through touch-down. On rendezvous , th e VHF communica tions from l i f t -o ff t o sho r t l y

VHF communications w i t h



9-26

N A S A - S - 7 1 - 1 6 5 6

(a) High overhead view with no zero phase washou’

Note: Recogiilzable landniarks are iden tified with like numbers on each P h o t o g r a p h .

(b) LOW eievatlori showmg zero p h a s e washout.

F i g u r e 9-4.- Comparison of v i s i b i l i t y of lunar s u r f ac e d e t a i l s look ingw e s t t o e a s t i n t h e P a st eu r c r a t e r a rea .



9-27

b e f o r e t e r m i n a l ph as e i n i t i a t i o n w ere m a rg in a l. A l s o , t h e VHF rangingwould not loc k up o r , when i t d i d , a f a l s e r an ge w a s in di ca te d most oft h e t i m e .in g w a s turn ed of f temporar i ly . However, none of th es e procedures i m -p ro ve d t h e s i t u a t i o n t o any g r ea t d e g re e ( s e c t i o n 14.1.4). A f t e rte r min a l phase i n i t i a t i o n th e vo ice communica tions and VHF ranging weres a t i s f a c t o r y .

Both antennas were t r i e d , t h e squelch w a s adju sted , and rang-

9.13 TRANSEARTH I N J E C T I O N

The t ransear th inje 'c t ion maneuver w a s e s s e n t i a l l y n om in al i n a l las pe ct s. The only it em worthy of comment oc cu rr ed about 20 secondsp r i o r t o t h e e nd of t h e maneuver. There w a s a s l i g h t hum o r buzz i nth e ser vi ce propu ls ion system t h a t cont inued through shutdown. Every-t h i n g was steady, however, and i t w a s no t a matter of great concern.The r e s i d u a l s w e r e p l u s 0.6, plus 0.8, and minus 0 .1 f t / s e c .trimmed t o p lu s 0 .1 , p l u s 0.8, and minus 0.3 f t / s e c .w a s w i t h i n 1 second of t h e pad value.

These wereThe f i r i n g ti m e

9.14 TRANSEARTH COAST

The on ly midcourse c or rec t ion dur ing th e t ra ns ea r t h coas t phase w a sone re ac ti on co nt ro l system maneuver performed approxim ately 17 hoursa f t e r t r a n s e a r t h i n j e c t i o n . The t o t a l d e l t a v e l o c i t y w a s 0 . 7 f t / s e c .Dur ing th e t ra ns ea r t h coas t phase, a sch edu le of no-communications navi -g a t i o n a l s i g h t i n g s w a s completed. The s t a t e v e ct o r from t h e t r a n s e a r t hinject ion maneuver was not updated excep t by nav iga t io na l s igh t in gs .The s t a t e v e c t o r

w a s dawnl inked t o t h e Network p r io r t o th e one mid-c o u r s e c o r r e c t i o n . The midcourse correct ion w a s t h e n i n c o r p o r a t e d a ndu pl in ke d t o t h e s p a c e c r a f t . An updated Network s t a t e ve c to r w a s main-t a i n e d i n t h e l u n a r module s l o t a t a l l t im es . J u s t p r i o r t o e n t r y , t h eonboard s t a t e vector compared qui te w e l l w i th t h e v e c t o r o b t a in e d byNetwork tr a c k in g . I n a d d i ti o n t o t h e n a v i g at i o n al s i g h t i n g s f o r t h eo nb oard s t a t e v e c t o r , a d d i t i o n a l s i g h t i n g s were p er fo rm ed t o o b t a in d a t aon s t a r s o u t s i d e o f t h e p r e s e n t c o n s t r a i n t l imi t s . The updates obtainedo n t h e c o n s t r a i n t s t a r s w er e n ot i n c o r p o r a t e d i n t o t h e s t a t e v e c t o r.The c i s l un ar n av iga t io na l s ig h t i ng p rogram would b e improved i f a re-cycle fe at ur e were incorporated. Recal l ing th e program f o r each mark i sa drawback t o ex ped i t io us n a v i g a t i o n a l s i g h t i n g s .

The r e s t of t h e t r a n s e a r t h c o a s t w a s l i k e t h a t of p r ev io u s l u n a rmissio ns wit h two exce pt ons-nf l i g h t demonstrations were performedt o e v a lu a t e t h e e f f e c t s o f z er o -g r av it y on p h y s i c a l p r o c e s s e s , and acommand and se r v i c e module oxygen f law-ra te tes t w a s performed. Even



9-28

though the metal composites demonstration w a s s t a r t e d d u r i n g t r a n s l u n a rc o a s t , t h e r e was n o t s u f f i c i e n t t im e w h il e o u t of t h e p a s s iv e t h e n n a lco nt ro l mode t o complete a l l of the 18 samples. The o th er t h r e e demon-st ra t i on s were completed.

9.15 ENTRY AND LANDING

A change t o the nominal entry s towage was the addi t ion of t h e dock-in g probe. The docking probe w a s t i e d down fo r en t ry a t t h e f o o t of t h eLunar Module Pilot 's couch using procedures voiced by the Mission ControlCen ter. Three d i sc repan c ies were no ted dur ing en t ry. The en t ry m n i t o rsystem was s t a r t e d manua lly a t 0.05g t i = p l u s 3 seconds.never i l lumina ted ( sec t ion 14 .1 .5 ) .i n g t h e p e g.of steam pres sure pegging was approximately 5 t o 1 0 s e c o n d s l a t e a n doccurred a t an a l t i tu de below 90 000 f e e t .c h e c k l i s t g i v e s a s p e c i f i c ti me a t which the steam pressure gage should

peg h ig h r e l a t i v e t o t h e i l l u m i n a t i o n o f t h e 0.05 g l i g h t as an ind ica t ionof the 90 000-foot a l t i t u d e ; however, t h e steam pre ss ure measurement isonly an approximate indicat ion.e r a l l y . ] Also, p a r e r w a s s t i l l on at l e a s t one of th e main buses af t e rthe main bus t i e swi tches were tu rned o ff a t 800 f e e t .were not completely powered down un t i l t h e c i r c u i t brea kers on panel 275w ere p u l l e d a f t e r l a n d i n g ( s e c t i o n 14.1.6) .

The 0.05g l i g h tThe steam p r e s s u r e w a s l a t e i n r ea ch -

The timeowever, the cabin pressure w a s used as a backup.

[E d i to r ' s no te : The c rew

The crew in te r p re ted t he che ck l i s t l i t -

The main buses

The landing impact w a s milder t h a n a n t i c i p a t e d . The parachuteswere j e t t i soned and the spacecra f t r emained i n t h e s t a b l e I a t t i t u d e .Recovery personnel arrived a t the spacecra f t be fo re the comple t ion o ft h e 1 0-minute w a it i ng p e r i o d re q u i r e d p r i o r t o i n i t i a t i n g i n f l a t i o n oft h e u p r i g h t i n g ba gs f o r a s t a b l e I la nd in g. One pa rac hu te became en-

tang led on the spacecra f t and was cu t loose by t he recovery team. Thecarbon dioxi de bo t t l e on t h e Lunar Module P i l o t ' s l i f e p r e s e r v e r wasloo se and th e ves t would no t i n f l a t e when th e l e ve r was p u l l e d . Theb o t t l e was t i g h t e n e d, and t he n t h e l i f e p r e s e r ve r inf la ted proper ly.

!L



NASA-S-71-1636Revolution counl

CR O

-' HS K

t-

Lilt-off

Iiiscrtioci nd systrms checks

Extcld doeking mbe

Y

D,Nigl

N

MSFN

9-29

S-Lw evasive m m v n

Platlam rcaligmneibl

S-IPB tiwid axyqen h p

C i s l u u navigation

o d i c s ulibratim

tal 0 to 10 hours.

Figure 9-1.- F l i g h t plan a c t i v i t i e s .



9-30

NASA-S-71-1b37El lpvdtim

3

Figure 9-1. - Continued.

I

L



NASA-S-71-1638

MSFN

Each &ride dim-light pho(ayaphy

Initiate parrive thmnal colilml

Cm xercise m ia d

I-m ) * l q * Y

DayNight

N

(cl 3Oto 51 hours.

Figure 9-1.- Continued.

P l a t f a n r ea l iymes

E

Initiate passive themu1 conbol

1

9-31

DWNisht



9 - 3 3NASA-S-71-1640

DayNight

Housekeepin(

Luna iilodile clrckwt

1

11le1 61 to 78 hours.


9

Water nialaprnniiL w a l n cycled

Eresruize lunr nodule

Initiate hnr mduk a s m i battery e s t

NiP

II



9- 34NASA-S-7 1-1641r T ount

~kpsed ime

18 MSFN

74

m

81

0Niy

Terminate liiiia m d i l e ascciitballcry test

Platlomi realigiineiit

Systems checks la liiiia wbitIIIsert loll llJneUVeI

Revolution count

111 ntom hours.

Figure 9-1. Cont h u e d .

P atrain realiqimeiil

L M h W k ( r r h i n q

Systems checks lw descent a b i iinmution n w w u

INII



NASA-S-71-1642Revolution count

Phmograllll Desc r t c s

Initiate e s t attitude

D<Nigl

9-35Revolution count

INs

Plat lmii r ea l i~unen t

Ternittiate rest motu&

Y

lgl I to 105 hours.

F i g u r e 9-1. - Cont inu ed.

Open dockiiq tunnel and baisfmI O l l u u mobbe

Luna moduk activationand r y s t n r

Luna module coascalignment

Undocking nd sep.r*ion

ckout

-



9-36NASA-S-7 1-1643Revolutioncount

MSFN(LI

RevolutioncountElapsed lime

m

t

109

MSFN

110

L.

D*Nig'

Cunniand rid service iiiodiileIUIIU orbit circuIarizatioil

Luna iiiodule descent popilsionsystem and laiidiny rads chechoul

C m a n d a nd s u v ic e moduleIanhak t r ack ing

ConunMdan d service module a.dluna niodule p la tf or m r r a l i p m n t

Command md s u v i c e nodukorbital science phaog.phs

Luna nodule p a r e d descentinitiation

Luu noduk landing

Carnand Md s u v i c e modulep l * h nallqnncnl

C m a i

Modu kLuna module platform e,r r a l i p m n l

1Camund md service module1 backing

i

Ilapsed time

1ll

(h) 1 8 o 115 b u n .


. .L

1 -L

. -L

L,lllaf sinlace i iavigatiwi

0NV J

( ~ i o t i a ~ial i i le)

Colnrnandeiaiid LunarModiilcPilot eat

Cel)cnschein lJlotopapriyby Command ModulePilol

Backwrd-loolring chaseobservalion by CarmindModule Pilol

C ab in a d q ui pn en l p e w a -(ions for Insc emavehlcularaclIvIIy

Don portable life siipporis y s t m s

F m r r d - l o o k i n gz u o phaseo h v a t i o n by C a m a n dModule Pilot

Portable Iile supper( syslmlconnrunic*ims check

Zodiacal Ii+ phologaphy byC m n d Moduk Pilot

Don helmetr/glons

Suit presswe i n t w i t ycheck

F i n a l p e w a l i o n s for ewers

S t r t f irst eatravehtcula activi ty14 hous 48 minuter)

Te k r

C m n d md service modukbut in ) of laded luna module

i -

L A-. -L



9-37WA5A-5-11- 1644Revolution count

Camnd and w v i c e d kp la tf ann r r a l ip nmt

Galactic suvey p h o t o q q h yby Canmiand Yobk Pilot

h a d d ervice mob lep la tf m realigmnent

I

Eathshine p h a o q a d ~ y yC d oduk Pilot

TenninYe first edrarehiwlr

wt iv i tyCam~md d service mobk

COnnlVlp l a t f m mliqmmt

Repessuize knr mobk Yobkcabin nd rchrpc por t lbk P iW ealife w w m sysllcns

Doff W b k if e suppatsystemsInitme VHF b ~ r t a t i c d rtest (11 h a d 1

blution countElapsed time

' +r 1 a M S F N MSFN

liI 115 to 130 hours.

Figure 9-1. - Cont in ue d.

hI

Cainiiaid ModulePilot S I

-

NIcannndnd LunaModuleP i l ~at

1_

CamnMdIn d huodukPlb ( S k

I

1Orbital scnnce photoqaphy byC m m a d Uobk P i b t

Initiate S-band bi-static carndradar e s t



9-38

r a t i o n fa secmid extrave- Modulehicu la ac twi ly P i lo teat

NASA-571-1645Revolution count Revolution count

(CSMI

MSFN

1. 1%

Donportable lif e siipportsysluns and checkcanmunicatiois

Conunamd aiid service iiioduleplrtfrml realiqmieiilFinal prpuat ions la egress

Vertical stweo md orbital sciencephotaq~rphy y C m ~ n dodule P i l o tStart second extravchiciila activily(4 hours 35 niiiules)

Te ,

Galactic s w e y photopraphyby Cd ModuleP i l o t

Luna libation )Ihotopaphyby Camnnd Module P i k u

-137

- MSFN

13 13010 140 hours.

Figure 9-1. Continued.

ISFN

CNic

Te evisior

I

1ontiiigeiicy pliotograpliy01

Dercartes by ColiiiiiridModiileP l l O l

Teniiiiiate second eauavcli ici i l aIcIIvII;l

Repressurize liiiiarmodiile cahii i

Dolt pacable life supporls s I nis

C m n u d a nd s o vi c e oiioduleplat lam realiginwnt

Depressurize lvnu mochilr cabin.JCIIISM equipnnt. a i d r e p e s -sinize cabin

C m n d nd service moduleIandmak tracking

1Rendezvous rdr actiuationand sell test

COlWlndclndLwuYodukP i k t eat

1B.ckwd- looLinp zuo phauObmvalimi nd a b i t a l S C H n C e

photopraphy by Connmd YodukPi lo t

F a w d - W i q zuo. k U U * l o n by CIlUd

W l e i M



9-39NASA-5-71-1646

Revolut on count

r t ime1mMSFN MSFN

I

- 1

-141 MSFN

-14’ MSFN

-141

-145

I

Luna module platlmiirealiqmnent

Pretvincli switcli checks

Lift-off from l i m a surfaceOrbilal inseflimTweak l l l ~ u r n

Tnminal phase Iinalizaim

Telcrisiui

_tDocking

T r n r f n c q u i p ml md s n p k sI O c d odule md s tw Iheill

Revolution count

Platlmii realiyiniieiit

toiitmiinalimi control

INil

Pl l aog lphr .I pollo 1 2 lunar module.4 potlo 13 and 14 S-m mpact points

Initiate pnssiue Ilmmal s a b o t

Ikl 140 to 150 hours.

F i g u r e 9-1. - Continued .



9-40

UASA-S-71-1641

Elapsed time

162

1

S I

-PUtlaiii realiqrmnetit

I

Terminate parrove thnntal control

D<Niql

170

111 -Ill 150 to 171 hours.

F i g u r e 9-1.- Continued.

. -L

?L L-

Tmiioiate oxyqen l lo r rate test altitude

Initiate thnnal attitude

i .L



Initiate passive thcnrul cmml

INil

l c k r i s m u

I

F i g u r e

Im l

9-

171 to

,1. Continued.

" N

Platfani realiqmnent

Entry nonitor system m y heck

Terminate passive thermal CWOI



9-42

NASA-S-71-1649

tCislun

D,Nigl

Q e w eaucise

Initiate parwe thermal conVol

? -

L

1

A-

-

P l r f o m n r l i q m n l

Elapsedtime

Y

1n) 1m to 198 hours.


Robe IlorrW

Television

probe stowaqe

Cir lun r n iv iqYim

I

. . . .A -

, -A.a

DNiq

- _.Li

- "

i



NASA-S-7 1-1650

FN Ni

1

iPal

Initiate p a r i v e Ucrul control

E l a ~ s e dime

(0 ) lpll to 214 hours.


9-43

Ddv

lavigilion

-

C i r l u v l u r ~ i a a



9-44

NASA-S-71-1651Elamd time

L

. -L.

. -L

Da y

Entry monitor system entry check

Command module/scrvice nicdules c w a t i m

Entry mtaface

Elapsed t imev

(PI 14 to 2 l7 hours.

Figure 9-1. Concluded.

1 .IL

.

A-.A.



10-1

10 .O BIOMEDICAL EVALUATION

T h i s s e c t i o n i s a summary of t h e Apollo 1 4 medica l f ind ings basedon a p r e l im i n a ry a n a l y s i s o f t h e biomedical d a t a . A comprehensive eval-u a t i o n w i l l be pub l i shed i n a s e p a r a t e r e p o r t .mulated a t o t a l o f 650 man-hours o f s p a c e f l i g h t e xp e ri e nc e .

Th e three crewmen accu-

The crewmen remained i n e xcel lent he al th throughout t h e miss ion a n dthe i r pe r fo rmance w a s e x c e l l e n t d e s p i t e an a l t e r a t i o n of t h e i r normalwork / res t cyc le .mained wit hin t h e expected ranges dur ing t h e f l i g h t .which could be a t t r i b u t e d t o t h e l u n a r s u r f a c e e xp os ur e h av e b ee n o b s er ve d.

A l l phys iolo gica l parameters obta ined from t h e crew re -No a dv er se e f f e c t s

10 .1 BIOMEDICAL INSTRUMENTATION AND PHYSIOLOGICAL DATA

Problems wi th t h e Comander ' s biomedical instrument a t i on h a r n e s sbegan p r i o r t o l i f t - o f f when t h e s t e r n a l e l e c tr o c a rd i o g ra m s i g n a l becameunreadable 3 m in ut es a f t e r s p a c ec r a ft i n g r e s s . A waiver w a s made t o t h el au nc h mi ss i on r u l e r e q u i r i n g a r eadab le electrocardiogram on all crew-men. During t h e f i r s t orb i t , the Commander ' s s t e rna l e l ec t roca rd iograms i g n a l returned t o n or ma l.

A t about 57 1 / 2 hours, the Commander noted that h i s l o w e r s t e r n a ls e n s o r h ad l e a k ed e l e c t r o d e p a s t e a r ou nd t h e s e a l i n g t a p e . T hi s s i t u -a t i o n w a s c o r r e c t e d by a pp ly in g f r e s h e l e c t r o d e p a s t e a nd t a p e .

When t h e Commander t ra ns fe rr ed t o t h e po r t ab le l i f e support systemin p r e pa r a ti o n f o r t h e e x t r a v e h i c u l a r a c t i v i t y , h i s e l e c tr o ca r di o gr a mw a s s o n o i s y on tw o oc c as i on s t h a t t h e c a r d io t ac h om e te r o u t p u t s i n t h eMission Contro l Ce nter were unusable and manual co unti ng of t h e h e ar tr a t e f o r metabol ic r a t e assessment became necessary. A good e lec t ro -cardiogram signal on t h e Commander w a s r e a c q u i r e d a f t e r c om pl et io n oft h e e x t ra v e hi c u la r a c t i v i t y a n d r e t u r n t o t h e l u n a r m odule.on t h e t o p c o nn ec to r o f t h e s i g n a l c o n d i t i o n e r were a c c i d e n t a l l y s t r i p p e d .However, t h e e lec t roca rd iogram s i gn a l w a s r e s t o r e d f o r t h e r em ai nd er o ft h e f l i g h t by t i g h t e n i n g t h i s connector.

The threads

The q u a l i t y o f t h e Lunar Module P i lo t ' s e l ec t roca rd iogram w a s excel-l e n t f rom spacecra f t ingress u n t i l a p p r o x i m a t e l y t h r e e days i n t o t h e m i s -s i o n . A t t h a t t i m e , i n t e r m i t t e n t n o i s e tr a ns m is s io n s t y p i c a l o f a looses e n s o r were rece ived . The lower s t e r na l sensor w a s r e s e r v i c e d w i th f r e s hp a s t e and t a pe . Th i s happened two add i t i ona l t imes . No a t t empt w a s made

t o c o r re c t t h e s i t u a t i o n on t h e l a s t occurrence.



10-2

"he L u n a r Module P i l o t a l s o l o s t h i s impedance pneumogram a f t e r t h ee i g h t h day o f f l i g h t .d i t i o n e r h ad f a i l e d .

P o s t f l i g h t e x am in a ti on s how ed t h a t t h e s i g n a l con-

Phy sio logi cal measurements were with in expec ted ranges th roughoutt h e m i s s i o n . T h e average crew heart ra tes f o r work an d s l e e p i n t h e

command module and lunar module are l i s t e d i n t h e f ol lo win g t a b l e .

Ic t i v i t y

Command module:

WorkSleep

L u n a r module:

WorkSleep

Average heart r a t e s , bea t s /min

Ccanmand ModuleP i l o tommander

5752

66I 46

L u n a r ModuleP i l o t

Figure 10-1 p r e s e n t s t h e c r e w h e a r t r a t e s a f t e r t r a n s l u n ar i n j e c t i o ndur ing the mul t ip le unsuc cess fu l dock ing a t t empts and t h e f i n a l h a r d dock.

NASA-S-71-1657

160

140

120C.-E>g 100

52

f

80

60

402:20 2:40 3:OO 3 2 0 3 4 0 4:OO 4 2 0 4 4 0 5:OO 5:20

Figure 10-1.- C r e w h e a r t ra tes dur ing mul t ip le dock ing a t t empts .



10-3

During powered descent an d asce nt , t h e Commander's he ar t - ra te averagesranged from 60 t o 107 beats per minute duri ng descent and from 69 t o 83bea t s pe r minu te dur ing ascen t , as s h a m i n f ig u re s 10-2 and 10-3, re-s p e c t i v e l y. These hea r t - ra t e averages fo r descen t and asce n t . were t h elowest observed on a lunar l and ing miss ion .

NASA-S-71-1658

180

160

140

80

60

40107:57 107:59 108:Ol 108:03 108:05 108:07 108:09 108:ll 108:13 108:15 108:17 108:19

l i m e , hrmin

Figure 10-2.- H e a r t ra tes of t h e Commanderduring lunar descen t .



10-5

0

ODrl

0

0

l-??

0

0P-rl

rl

0

9rl

d

‘I!

O

v)drl

‘I!

0

v)d

0

0

0mrl

r(

0

$!Qrl

r(

0

m

4-

xobal

X

I

3

I0r l

aJk



10-6

d

_ .

H U L L

aala?

dVC0

V

I3

I0r l

aJ



10-7



10- 8

aala3

r l0

uI

inI

0r l

al

bo.riR

5



.-

10-9I

TAB= 10-1 -mAB0I ; IC ASSES- OF THE FIRSTMTRAVEHICULAR ACTIVITYPERIOD

(b )712

W 1

l l b l 4 7 I 18

86P

15

92

lz2443

lo8r

15

2P3

3S

ll2

15L

341

l221

35

(b)9553

22535

159b2

2s

30s963n

lo399

6 n275

26301

c65

1%26

235m

P46l2

30962

lob61

'930



10-10

B v r i r n activitr.

-Bb40

6$39

m

Fn53ea

u 313

34855

15

2 l 2P

1279530

l 2 h

3885bln

46135LT60

'1399020

l33:lb133:s

l33:221 3 3 : 1 I 2l33:kl33146l33:52l33:5L

134:wu I : o 2* : G 6

135& 1 2

bi%

-l3lr08u1:ml Y: 2 1lY139l3l:ulY:b613l:5bmi26m : 3 L1P:391P:Q1 P : b h1 9 : U1P:52132:Sll33:m133:lhm : 1 6133:22133x38133:M133:nI 3 3 5 2133:54uL:m13450213b:o6134:wl3b:u

+3k : l134 : 9134:52u4:5513b:ST

13S:25135:35

82 &93

283

3TlwE l 1923969

ulb

3n

121

18S28

P8532IL53

l b26

16266262b32

362332

28

108

ll190

633l

111P 3ll246bS3485

61292

66206304

b3116106

39134

b5918252

596P631841

116

2

%

lon1331l*l1b63l 6Lol S S l

993l% L1p601558l b l 5IO&?U O P996

un

L%7



10-11

10.2 MEDICAL OBSERVATIONS

10.2.1 Adaptat ion t o Weight lessness

Adapta t ion t o t h e w e i g h t l e s s s t a t e w a s re ad i l y accompl ished . Sh or t lya f t e r o r b i t a l i n s e r t i o n , e ac h crewman e xp e ri en c ed t h e t y p i c a l f u l l n e s s -of-the-head sensation t h a t has been repor ted by p rev ious f l i g h t c rews.N o nausea , vomi t ing , ve r t igo , o r d i s o r i e n t a t i o n o c c u r r e d d u r i n g t h e mis-s ion , and the c rew d i d n o t ob se rv e d i s t o r t i o n of f a c i a l f e a t u r e s , suchas r ou nd in g o f t h e f a c e du e t o l a c k o f g r a v i t y , as reported by some pre-vious crewmen.

During the f i r s t two days o f f l i g h t , th e crew repor ted d i scomfortand soreness o f the lower back muscles as has been noted on previous m i s -s i o n s .d u r in g t h e f i r s t day of t h e miss ion , and w a s a t t r i b u t e d t o changes i np o s t u r e d u r i n g w e i g h t le s s n e ss . I n f l i g h t e x e r c i s e p r o vi d e d r e l i e f .

The discomfort w a s s u f f i c i e n t i n m agnitude t o i n t e r f e r e w it h s l e e p

10. 2.2 Vi su al Phenomenon

Each crewman repo r te d see ing t h e s t re ak s , p o i n t s , and f l a sh es o fl i g h t t h a t have been not ed by previous Apollo crews. The frequency oft h e l i g h t f l a s h e s averaged about once every 2 minutes f o r each crewman.The Visual phenomenon w a s observed with t h e eyes both open and clos ed,and the crew w a s more aware of t h e phenomenon imme diate ly upon awakeningt h a n u p o n r e t i r i n g . I n a s p e c i a l o b s e r v a t i o n p e r i o d s e t a s i d e d u r in g t h etr an se ar th coast phase, t h e Cammand Module P i lo t determined th a t darka d a p t a t i o n w a s not a p r e r e q u i s i t e f o r s e e i n g t h e phenomenon i f t h e l e v e lo f s p a c e c r a f t i l l u m i n a t i o n w a s low. F ur th er mo re , s e v e r a l o f t h e l i g h tf l a s h e s were apparen t ly seen by two of t h e crewmen sim ult ane ou sly . Coin-

c idence o f l i g h t f l a s hes f o r two crewmen, i f a t r u e co inc idence , woulds u b s t a n t i a t e t h a t t h e f l a s h e s o r i g i n a t ed from an e x t e r n a l r a d i a t i o n s o u r c eand would ind ic at e t h a t they were generate d by extremely-high-energy par-t i c l e s , presumably of cosmic or i gin . Low-energy highl y- ion izing p a r t ic l e swould not have th e range through t i s s u e t o have reached both crewmen.

10.2.3 Medications

No m ed ic at io ns o t h e r t h a n n os e d r o ps , t o r e l i e v e n a s a l s t u f f i n e s scaused by sp ac ec ra f t a tmosphere, were used during t h e mission. On th eth i rd day o f f l igh t , the Commander and the Lunar Module Pilot used oned ro p i n e ac h n o s t r i l . Rel ie f w a s prompt and l a s t e d fo r approx imate ly

1 2 ho ur s. The Command Module P i l o t used t h e nose drops 3 h o u r s p r i o rt o e nt ry .



10-13

P i l o t . The t o t a l r a d i a t i o n d o se f o r e ac h crewman w a s approximately 1.15r a d s t o t h e s k i n and 0.6 r a d a t a 5 - c en t im e t er t i s s u e d e p th .a re the l a rges t observed on any Apol lo miss ion ; however, they are w e l lb elo w t h e t h r e s h o l d o f d e t e c t a b l e m ed i ca l e f f e c t s .r a d i a t i o n d o s e s w ere a p p a r e n t ly t h e r e s u l t o f two f a c t o r s :l u n a r i n j e c t i o n t r a j e c t o r y l a y c l o s e r t o t h e p l a n e o f t h e g eo ma gn etice q u a t o r t h a n t h a t o f pr e vi ou s f l i g h t s an d , t h e r e f o r e , t h e s p a c e c r a f tt r a v e l e d t h r o u g h t h e h e a r t o f t h e t r a p p e d r a d i a t i o n b e l t s .rad ia t ion background w a s g r e a t e r t h a n p r e v i o u s l y e x p er i en c e d.gamma spectroscopy w a s a l so performed p os t f l i gh t on th e c rew and ind i -ca te d no cosmic ray induced rad io ac t iv i ty .

These doses

The magnitudes of the(1) The t rans -

( 2 ) The spaceWhole-body

10.2.6 Water

The c rew repor ted tha t the t a s t e o f t h e d r i n k i n g wa te r i n b ot h t h ecommand module and t h e l una r module w a s e x c e l l e n t . A l l e igh t scheduledi n f l i g h t c h lo ri na ti on s of t h e command module wat er system were accom-p l i s h e d .

s h ar ed t h a t t h e i o d in e l eve l i n b o t h w a t e r t a n k s w as adequa te f o r bac-t e r i a l p r o t e c t i o n t h r o u g h o u t t h e f l i g h t .

P r e f l i g h t t e s t i n g o f t h e l u n a r module p o t a b l e w a t e r system

10.2.7 Food

T h e i n f l i g h t f o o d w a s similar t o t h a t o f p rev ious Apol lo miss ions .Six new foods were incl uded i n th e menu:

a. Lobs te r b i sque ( f ree ze dehydra ted)

b. Peach embrosia ( f re ez e dehydrated )

c . Beef j e r k y ( r ea d y- to - ea t b i t e - s i z e d )

d. Diced peaches ( the rmos tab i l i zed)

e . Mixed f r u i t ( t h e r m o s t a b i l i z e d )

f. Pudding ( the rmos tab i l i zed)

The l a t t e r t h r e e items were packaged i n aluminum cans with easy-open,f u l l - p a n e l , p u l l - o u t l i d s . The crew di d not r ep or t any d i f f i c u l t i e se i t h e r w i t h rem ov in g t h e p u l l- o u t l i d s o r e a t i n g t h e f oo d c o nt a in e d i nt h e s e c a n s w i t h a spoon.

P r i o r t o t h e m i s si o n , e ac h crewman e v a l u a t e d t h e a v a i l a b l e f oo di tems and se l ec te d h i s ind iv idu a l f l ig h t menu. These menus p rov ided

approximate ly 2100 c a l o r ie s pe r man per day.the c rew main ta ined a food consumption log.Module P i lo t a te a l l t h e food planned f o r each meal, b ut t h e CommandModule Pilot w as s a t i s f i e d w i t h l e s s .

Dur ing mos t o f the f l igh t ,The Commander and t h e Lunar



10-14

Recovery-day ph ys ica l examinations rev eal ed t h a t t h e Commander andt h e L u n a r Module P i lo t had main ta ined t h e i r approximate p r e f l i gh t we igh t ,wh ile t h e Command Module P i l o t l o s t ne ar ly 1 0 po und s. The Command ModuleP i l o t s t a t e d t h a t h e w ou ld h av e p r e f e r r e d a grea t . e r quan t i ty o f food i t emsr e q u i r i n g l i t t l e or no prepara t ion t i m e .

1 0 . 3 PHYSICAL EXAMINATIONS

Each crewman received a comprehensive physical examination a t 27,1 5 , and 6 d ay s p r i o r t o l a u n c h , w i t h b r i e f e x am i n at i on s c o nd u ct ed d a i l yd u r i n g t h e l a s t 5 days before launch.

S h o r t l y a f t e r l a n d i n g , a comprehensive ph ys ic al exam ination showedt h a t t h e c r e w w a s i n good h e a lt h . Both t h e Commander and th e CommandModule Pilot had a small amount o f c l e a r, b ub bl y f l u i d i n t h e l e f t middle-e a r c a v i t y and s l i g h t r ed d e ni n g o f t h e e ar d ru m s. T he se f i n d i n g s d i s a p -pea red i n 24 hou rs wit hou t tre atm en t. The Lunar Module Pi l o t had mode-r a t e e y e l i d i r r i t a t i o n i n a d d it i o n t o s l i g h t r ed n es s of t h e ea rd ru ms .

A l l crewmen showed a m i l d te mp or ar y r e a c t i o n t o t h e m i cr cp o re t a p e cover-i n g t h e i r b io me di ca l s e n s o r s . T h is r e a c t i o n s u b s i d e d w i t h i n 24 h o u r s .

10 .4 FLIGHT CRFW H W T H STABILIZATION

During prev ious Apol lo miss ion s , crew i l ln es se s were respon s ib lef o r numerous me di ca l and o p e r a t i o n a l d i f f i c u l t i e s . T h r ee d ay s b e f o r ethe Apol lo 7 l aunch , the c rew deve loped an upper resp i ra to ry in fec t ionwhich s u b s id e d b e f or e l i f t - o f f , b u t r e c u r r ed i n f l i g h t . E a rl y on t h eApollo 8 mission, one crewman developed symptoms of a 24-hour v i r a l gas-t r o e n t e r i t i s w h i c h w a s epid emic i n t h e Cape Kennedy area around launch

t i m e . About two days p r io r t o t he Apol lo 9 f l i g h t , t h e crew d ev el op edcommon co ld s which ne ce s si ta te d a d e l a y o f t h e l a un c h f o r t h r e e d ay s.Nine days be fo re t h e Apollo 1 3 launch, the backup Lunar Module Pilot de-velo ped German measles ( r u b e l la ) and in ad ve rt en tl y exposed th e prime Com-mand Module P i l o t . The day b ef or e l au nc h, t h e prime Command Module P i l o tw a s rep laced by h i s backup counte rpar t because l abo ra to ry t e s t s i n d i c a t e dt h a t t h e prime crewman w a s not immune t o t h i s h igh ly communicable dis eas ew i t h an incu bat ion p er io d of approximately two weeks.

I n w. a t tempt t o p ro t ec t t h e p r ime and backup f l i g h t crew membersf rom exposure t o communicable d i se ase dur in g th e c r i t i c a l p re launch andf l i g h t p e r io d s , such as e x p e r ie n c e d on p r ev i o u s f l i g h t , a f l i g h t crewh e a l t h s t a b i l i z a t i o n program w a s implemented. This program co ns is te d of

t h e f o l l o w i n g p ha se s :

* - 1 t - . *11 li L: L L t L- L - L L L L L i k - I -



10-15

a. I d e n t i f i c a t i o n , e x a m i n a t i o n , an d immunization of a l l primary con-t a c t s (pe rsonne l who req u i re d d i rec t con tac t wi th t he p rime o r backup c rewd u ri n g t h e l a s t t h r e e weeks p r i o r t o f l i g h t ) .

b . Heal th and epidemiological s ur ve i l la nc e of t h e crew members and

t h e pr im ar y c o n t a c t s , t h e i r f ami l i e s , and th e community.

c . Cer ta i n modi f i ca t ions t o f a c i l i t i e s u se d f o r t r a i n i n g and hous-ing th e c rew, such as t h e i n s t a l l a t i o n o f b io l o g ic a l f i l t e r s i n all a i rcond i t ion ing sys tems .

d. Housing of bot h t h e prime and backup crew members i n t h e crewq u a r t e r s a t the Kennedy Space Center from 2 1 days b ef or e f l i g h t u n t i llaunch.

The f l i g h t crew h e a l t h s t a b i l i z a t i o n p ro gra m w a s a complete success .No i l l n e s s e s o c cu rr e d d ur in g t h e p r e f l i g h t p e r i od i n any of t h e pr im e o rbackup crew members. Th is r e s u l t i s o f p a r t i c u l a r s i g n i f i c a n c e b ec au se

t h e i n c i d e n c e o f i n f e c t i o u s d i s e a s e w i t h i n t h e local community w a s n e a ra seaso na l h igh dur ing t h e p re launch pe r iod .

10.5 QUARANTINE

No change i n quaran t ine procedures were made on t h i s miss ion, excep tas fo l lows :

a. Two m ob il e q u a r an t i n e f a c i l i t i e s were u s e d.

b . Two he l i c op t e r t r a ns fe r s o f th e crew and suppor t pe r sonne l were

performed.

The new procedures were implemented t o r et ur n t h e crew t o t h e LunarRece iv ing Labora tory f i ve days ea r l i e r tha n on p rev ious lun ar l a nd ingmiss ions .

The crew and 1 4 medica l suppor t pe r sonne l were i so la te d beh ind th em i c r o b i o l o g i c a l b a r r i e r i n t h e Lunar R e ce iv i ng L a b o ra to r y a t Houston,Texas, on February 1 2 , 1971 . Daily medical examinat ions and per iodiclabora to ry examina t ions sha red no s i g n s o f i l l n e s s r e l a t e d t o l u n a r ma-t e r i a l exposure.immunological , o r hemato log ica l pa rameter s i n e i th e r th e c rew o r t h emedica l suppor t pe r sonne l .l a t i o n w i t h i n t h e L un ar Re ce iv in g L ab o r at o ry, t h e f l i g h t crew and t h emedica l suppor t pe r sonne l were re l eased f rom quaran t ine .f o r t h e s p a c e c r a ft and samples o f l u n a r mate r i a l w a s t e r m i n a t e d A p r i l 4,1971

No s i g n i f i c a n t t r e n d s w er e n o te d i n any b io c h e m i c al ,

On Feb ru ar y 27, 1971, a f t e r 20 days o f i s o -

Q u a r a n t i n e



---11-1

11.0 MISSION SUPPORT PERFORMANCE

11.1 FLIGHT CONTROL

Fl i gh t co n t r o l pe rformancew a s

s a t i s f a c t o r yi n

prov id ing t i m e l yop er at io na l sup po rt. Same problems were enco unter ed and most are d i s -c us se d i n o t h e r s e c t i o n s o f t h e r e p o r t . Only those problems t h a t a r eo f p a r t i c u l a r c on ce rn t o f l i g h t c o n t r o l o p e r a t i o n s o r a r e not r e p o r t e delsewhere are r e po r te d i n t h i s s e c ti o n .

A l l l au nc h v e h i c l e i n st ru m en t u n i t a n al o g d a t a were l o s t j u s t p r i o rt o l i f t - o f f .c e ss e s t h e a na lo g f l i g h t c o n t r o l d a t a h ad f a i l e d . The f l i g h t c o n t r o l l e r sw ere a b l e t o r e co v e r m o s t of the ana log da ta f rom the S-IVB YHF downlink;however, because of i t s l i m i t e d r a n g e , an e a r l y l o s s of d a t a w a s e x p e r i -enced at 4 hours 27 minutes .

A f au l ty m u l t i p l e x e r w i t h i n t h e i n s t r u m e n t u n i t t h a t p r o -

A l l l aunch veh ic le d i g i t a l computer da ta were los t a t 3 hours and5 minutes a f t e r launch.s i v e v e n t a b o ut 29 m in u te s l a t e r i n d i c a t i n g t h a t t h e com puter w a s oper-a t i n g p r o p er l y. As a result of t h e loss of d i g i t a l computer da ta , com-mands t o t h e S-IVB h ad t o b e t r a n s m i t t e d w it h o u t v e r i f i c a t i o n o f p r o p e rexecut ion.sive maneuver.

The vehicle , however, executed a normal propul-

The c r e w p r o v i d e d v i s u a l a t t i t u d e i n f o r m a t i o n f o r t h e eva-

High-gain ant enn a lock up problems w e r e n o t e d d u r i n g r e v o l u t i o n 1 2l u n a r o r b i t o p e r a t i o n s .ment dump cou ld not b e accolnplished t o ob ta in data f r o m t h e r e v o l u t i o n 1 2low-a l t i tude l andmark t ra ck in g oper a t ion . These data w ere t o be u s e d f o rpowered descen t t a rge t ing .

Because of t h i s problem, a data s t o r a g e e q u i p -

D ur in g r e v o l u t i o n 1 2 , t h e pl an n ed v o i c e u p d a te s f e l l b e hi n d t h e t i m e-l i n e because o f p roblems wi th the lun ar module s t ee ra b l e an tenna . Conse-quen t ly, th e powered desc ent w a s per formed us ing the spacecra f t fo rwardand a f t m n i d i r e c t i o n a l a n t e n n a s and t h e 210-foot ground rec eiv ing an-ten na. Receiving of communications and hi gh -b it- ra te da ta were s a t i s -fac t o ry excep t f o r some s m a l l lo ss es when swi tching to t h e a f t an tennal a t e i n t h e d e s c e n t p h as e.

A n abort command w a s s e t i n t h e lunar module guidance computer andt h e i n d i c a t i o n w a s observed by F l i gh t Cont ro l dur ing lun ar module ac t iv a -t i o n , a b o u t 4 h o ur s p r i o r t o s ch e du l ed p ow ered d e sc e n t i n i t i a t i o n .

procedure w a s uplin ked t o th e crew which r e s e t t he abor t command and l e dt o t h e c on cl us io n t h a t t h e a b o r t swi tch had malfunct ioned. Subsequent ly,th e abor t coxnand reappeared th r ee t i m e s and, each time, the command w a s

A



11-2

re se t by t app ing on th e pane l near t h e a b o r t s w i t c h .h ib i t th e p r imary gu idance sys tem from go ing i n t o an abor t p rogram w a sd ev el op ed i n t h e i n t e r v a l p r i o r t o pow ered d e s c e n t, and w a s u p l in k e d t oth e c rew fo r manual en t ry i n to th e computer. The f i r s t p a r t o f t h e f o u r -p a r t p r o c e d u r e w a s e n t e r ed j u s t p r i o r t o powered d e s ce n t i n i t i a t i o n a n d 't h e o t h e r p a r t s a f t e r t h r o t t l e - u p of t h e d e s c e nt e n gi ne . Had an abor tbeen requ i red , i t would have been accomplished using the abort guidancesystem and would have al lowed rees tab l ish men t of th e pr imary guidancesystem by keyboard entry a f t e r t h e a b o rt .

A p ro ce du re t o i n -

A delay of approximately 50 minutes o ccu rre d i.n th e f i r s t ex t rave-h i c u l a r a c t i v i t y be ca us e o f t h e l a c k o f s a t i s f a c t o r y c om mu ni ca ti on s.The crew were receiving ground communications bu t t h e Mission C o n t r o lCenter w a s no t rec ei vi ng crew communications. The problem w a s c o r r e c t e dby re se t t in g t h e Cammander's aud io c i r c u i t b re ake r which w a s not engaged.

The c o l o r t e l e v i s i o n c am er a r e s o l u t i o n g r a d u a l l y d e g r ad e d d u r i n gt h e l a t t e r p o r t i o n s o f t h e f i r s t e x t r a v e h i c u l a r a c t i v i t y . The d eg ra da -t i o n w a s caused by overhea t ing resu l t ing from 1.5 hours o f opera t ionwhile i n th e modular equipment stowage assembly p r io r t o i t s deployment.The camera w a s t u r n e d o f f b e tw ee n t h e e x t r a v e h i c u l a r p e r i o d s f o r c o o l-i n g , i n s t e a d of l e av i n g it o p e r a t i n g as r e q u i r ed by t h e f l i g h t p l a n .The camera p ic tu re reso lu t ion w a s s a t i s f a c t o r y d u ri ng t h e s ec on d ex t r a -v e h i c u l a r a c t i v i t y.

Three problems developed during the Apollo 1 4 m i s s i o n t h a t , h a d t h ecrew not been present , would have prevented the achievement of the mis-s io n ob jec t ive s . These p rob lems invo lved th e dock ing probe ( s ec t ion 7 .11 ,t h e l a nd i n g r ada r ( s e c t i o n 8.4) a nd t h e lunar module guidance computer,desc r ibed above . In each case , the c rew prov ided ground personne l wi thv i t a l i n fo r m at i on and data f o r f a i l u r e analysis and development of a l t e r -na te p rocedures . The crew performed th e necessa ry ac t i v i t i e s and th e re-

qui red work-around procedures t h a t a l lowed th e miss ion t o be completedas planned.

11.2 NETWORK

The Mission Control Center and t h e Manned Space F li gh t Network pro-vided ex ce l len t suppor t . There were o n l y t w o s i g n i f i c a n t p r o b l e m s . Adef ec t iv e - t ra ns fe r swi tch component caused a power outage a t the GoddardSpace F l i gh t Cen ter dur in g lu na r o r b i t . The power l o s s r e s u l t e d i n a4 1/2-minute d a t a loss. On l u n a r r e v o l u t i o n 1 2 , a power a m p l i f i e r f a i l -u r e o c c u r r e d a t th e Goldstone s t a t io n . The p rob lem w a s c o r r e c t e d b y

s w i t c h i n g t o a redundant system. The Network C o nt ro ll er 's Mission Re-p o r t f o r A p ol lo 1 4 , da ted March 19, 1971, published by the Manned Space-c r a f t C e n t e r, F l i g h t S up p or t D i v i s i o n , c o n t a i n s a summary of all MannedSpace Fl ig ht Network problems which occ urre d du rin g th e mission .

u'L:

. .

L I L L L L L L L L



11-3

11.3 RECOVERY OPERATIONS

The Department of Defense pro vid ed reco ver y s up po rt commensuratewi th miss ion p lann ing f o r Apollo 1 4 . S h i p s up p o r t f o r t h e p r i ma r y l a n d -i n g area i n the Pac i f i c Ocean w a s p r ov id e d by t h e h e l i c o p t e r c a r r i e rUSS New Orleans. Act ive a ir support con si s t ed of f i v e SH-3A h el ic op te rsfrom the New Orleans and two €IC-130 re sc ue a i r c r a f t staged from PagoPago, Samoa.ca r r i ed underwate r demol i t ion team p e r s o n n e l a n d t h e r e q u i r e d r e c o v e r yequipment.contaminat ion swimmer an d t h e f l i g h t s u rg e o n, and w a s u t i l i z e d f o r t h er e t r i e v a l o f th e f l i g h t crew. The f o u r t h h e l i c o p t e r, d e s i g n a t e d " P h o t o " ,s e r v e d as a photograph ic p la t fo rm f o r bo th mot ion-p ictu re photographyand l i v e t e l e v i s i o n c ov er ag e. The f i f t h h e l i c o p t e r , d e s i gn a t e d " Re la y" ,se rved as a communicat ions -relay a i r c r a f t . The sh ip -based a i r c r a f t werei n i t i a l l y p o si ti o ne d r e l a t i v e t o t h e t a r g e t p o i n t; t he y d e pa rt ed s t a t i o nto.commence recovery operations a f t e r t h e command module had been v is u -a l ly acq ui re d. The two HC-130 a i r c r a f t , designated "Samoa Rescue 1" and

Samoa Rescue2",

w e r e po sit io ne d t o t r a c k t h e command modulea f t e r i t

had exited from S-band blackout, as w e l l as p r o v i d e p a r a r e s c u e c a p a b i l i t yhad th e ccaumand module land ed uprange o r darnrange of t h e ta r g e t p o in t.A l l r e co v e ry f o r c e s d e d i c a t e d f o r A p o ll o 1 4 suppor t are l i s t e d i nt a b l e 11-1. Figure 11-1 i l l u s t r a t e s t h e r ec ov e ry f o r c e p o s i t i o n s p r i o rt o p r e d i c t e d S -band a c q u i s i t i o n t i m e .

Two of t h e h e l i c o p t e r s , designated "Swim 1" and "Swim 2",

The t h i r d h e l i c o p t e r, d e s i g n a t e d "R ec ov ery ", c a r r i e d t h e de-

I t

U . 3 . 1 Command M o d u l e Loca t ion and Re t r i eva l

The New Orleans' p o s i t i o n w a s e s t a b l i s h e d u s i n g a n a v i g a t i o n s a t e l -l i t e (SRN-9) f i x o b t a i n e d a t 2118 G.m.t . T h e s h i p ' s p o s i t i o n a t t h et i m e of command module landing w a s de termined t o be 26 degrees 59 min-

utes 30 seconds sou th l a t i tu d e and 172 degrees 4 1 minutes w e s t l o n g i t u d e .The command module l a n d in g po in t w a s c a l c u l a t e d by r e c o v er y f o r c e s t o be27 degrees 0 minutes 45 seconds sou th l a t i tu d e and 172 degrees 39 min-utes 30 seconds w e s t long i tude .

The f i r s t e l e c t r o n i c c o n t a ct r e p o r t e d by t h e r e co v e ry f o r c e s w a san S-band co n ta c t by Samoa Rescue 1. Radar c o n t a c t w a s t h e n r e p o r t e d byt h e New Orleans. A v i s u a l s i g h t i n g w a s re po rt ed by t h e communications-r e l a y h e l i c o p t e r and. t h e n b y t h e New Orleans, Recovery, S w i m 1 andSwim 2. Sh or tl y th e r e a f te r , v oice tra ns mi ssi on s from th e command modulew e r e r e c e i v e d b y t h e New Orleans.

The command module landed February 9 , 1971 , a t

mained i n t h e s t a b l e I f l o t a t i o n a t t i t u d e . The VHFa c t i v a t e d shortly a f t e r landing, and beacon contactcovery a t 2107 G.m.t. The crew then turned off t h et h e r e c o v e r y f o r c e s h a d v i s u a l c o n t a c t .

2105 G.m.t . and re-

recovery beacon w a sw a s r e p o r t e d by R e-beacon as they knew



11-

Type

TA B U l l - I . - AF'OLIX) 14 RECOVERY SUPPORT

Ship name/ Area supp or te dNumber a i r c r a f t staging baae

S h i p s

ATFLCU

DD

LSD

DD

L P H

HH-53c

HC-130

HC- 130

HC- 13 0

HC-130

HC-130

SH-3A

% l U S

3

1

1

1

a

a

1

2

a

a

5

USS P a i u t e

USS Hawkina

USS Spiege l Grove

E S Carpen te r

USS N ew Orleans

A i r c r a f t

P a t r i c k A i r Force B a s e

McCoy A i r Force B a s e

Pease Air Force B a s e

LaJes F ie ld , Azores

Ascens ion I s l and

Hickem A i r Force B a s e

USS N e w Orleans

one backup

. -L

Launch s i t e a re a

Launch abort area an dWest A t l a n t i c e a r t h -o r b i t a l re c ov e ry z o ne

Deep-space seco ndary land-i n g areas on t h e A t l a n t i cOcean l i n e

M i d - P a c i f i c e a r t h - o r b i t a lr ecovery zone

D e e p s p a c e s e c o n d a r y l a n d -i n g areas o n t h e m i d - P a c i fi c

l i n e an d t h e pr imary end-of -m i s s i o n l a n d i n g area

Launch s i t e a r e a

Launch abort a rea , WestA t l a n t i c r e co v e ry z o n e,c o n ti n g en c y l a n d i n g a r e a

Launch abort area, WestA t l a n t i c r e c o v er y z o ne

Launch abort area, e a r t ho r b i t a l co n ti n ge n cy l a n d i n e

areaA t l a n t i c Ocean l i n e a ndcon t ingency l and ing area

M i d- P ac if ic e a r t h o r b i t a lrecovery zone, deep-spaces e c o n d a r y l a n d i n g areaand primary end-of-missionl a n d i n g area

Deep-s pace sec ond ai yl a n d i n g area and primaryend-of -miss ion l and ingarea



NASA-S-71-1664

11-5

26 ' 40 '

26 ' 45 '

26 ' 50'

oy3

- 26 ' 55 '5

.-

8 .v)

27 '

27 ' 05 '

270- 10 '

I I I

-

177 ' 176 ' 175 ' 174 ' 173 ' 172 ' 171 ' 170 'West longitude

-USwim 1

k,l- wPhoto Rclay

S T a r q c t 1)o'tlLanding poi111

=wim

1 7 3 ' 00' 55' 172 ' 50 ' 45 ' 172 ' 40 ' 3 5 ' 1 7 2 ' 30'West longitude

Figure 11-1.- End-of-mission recovery support.

I



11-6

A f t e r confi rming t h & t t h e command module and t h e crew were i n goodcondition, Swim 2 a tt em p te d t o r e t r i e v e t h e m ain p a r a c h u t e s , an d s w i m -mers were deployed t o t h e command module t o i n s t a l l th e f l o t a t i o n c o l l a r .Recovery force s were unable t o re t r ie v e any of t h e .main para chu tes , butd i d r e tr i e v e two drogue par achu te covers and one sa bo t. The decontamin-ation swimmer w a s d ep lo yed t o p as s f l i g h t s u i t s and r e s p i r a t o r s t o t h ecrew and a s s i s t them f r o m th e command module i n t o th e l i f e r a f t . The

f l igh t c rew were onboard the recovery he l i cop te r 7 minutes a f te r theyhad eg r es s ed t h e command module and were aboard t h e New Orleans 5 minutesl a t e r. Command module r e t r i e v a l to ok p la ce a t 27 degrees 2 minutes southl a t i t u d e a n d 1 72 degrees 4 minutes west longi tude a t 2309 G . m . t .

The f l ight crew remained aboardthe New Orleans i n t he mobi le quar-a n t i n e f a c i l i t y u n t i l t h e y were flo wn t o Pago Pago, Samoa, where theyt r a n s f er r e d t o a second mobi le quaran t ine fac i l i ty aboard a C - 1 4 1 a i r -c r a f t. The crew w a s f lo wn t o E l l i n g t o n A i r F or ce B a s e , with a s t o p a tNorton A i r F or ce Base , C a l i f o r n i a , w her e t h e a i r c r a f t w a s r e f u e l e d .

A f t e r a r r i v a l of t h e New Orleans a t H a w a i i , t h e comm nd module w a soff load ed and taken t o Hickam A i r Force B a s e f o r d e a ct i v a !i o n . Upon com-

p l e t i o n of deactivation, the command module w a s t r a n s f er r e d t o E l li n gt o nA i r Force B a s e v i a a C-133 a i r c r a f t , a r r i v i n g on Fe br uar y 2 2 , 1971.

The fo l lowing i s a c h r o n ol o g i ca l l i s t i n g o f e v en t s d u r in g t h e re-covery and quarant ine operat ions.



Event

S-band co nt ac t by Samoa Rescue 1

Radar contact by New OrleansVisua l contact by "Relay" hel ico pte rVoice contact with f l i g h t crewCommand module landingSwimmers dep loyed t o command moduleF l o ta t i on c o l l a r i n s t a l l e d and i n f l a t e dDecontamination s w i m m e r deployedHatch ogened for crew egressF l i g h t crew i n e gr es s r a f tFl ig h t crew aboard he l ic op t e rF l i g h t Crew aboard New OrleansFl ig h t crew i n mobile quarant ine fa c i l i t yCommand module aboard New Orleans

Fi r s t sample f l i . g h t depar ted sh ipFlight crew departed shipF i r s t sample f l i g h t arrived Houston

(via Samoa end H a w a i i )

F l i g h t crew ar r i ve d HoustonF l i g h t crew a r r i v e d at Lunar Receiving

Laboratory

Mobile quarantine facility and commandmodule of floa ded i n H a w a i i

M obile q u a r a nt i n e f a c i l i t y a r r i v e dHouston

Reaction co nt ro l system de ac tiv ati on com-p l e t e d

Command module a r r i v e d HoustonCamnand module de li ve re d t o L u n a r Receiv-

ing Laboratory

,

TimeG . m . t .

Feb. 9, 19 712055

20 62100210 1210521122120212721402141214821532202309

Feb. 11, 1971035517462057

Feb. 12, 197109341135

Feb. 17, 1971- 2130

Feb. 18 , 19710740

Feb . 19, 19712300

Feb. 22, 197121452330

~~

Ti m e r e l a t i v et o l an di ngdays : hr :min

-0 : 0 :10

-0:oo :0 9-o:oo :05

0:oo :070:00:15

-0 :OO :Ob0 oo :oo

0 oo :220 :00 350:00:360:00:430:00:480:00:580:02:04

1:05:001 8 511 22 02

2:10:392 12 : 0

7 :22: 5

8:08:45

10 oo :05

12:22:5013 :00 5



11-8

11 .3 .2 Pos t recovery Insp ec t ion

The docking probe was removed from t h e command module and s ec u re di n t h e m ob ile q u ar an ti ne f a c i l i t y f o r r e t u r n t o Houston.asp ects of t h e command module postrec over y op er at i on s, t h e mobile quar-a n t i n e f a c i l i t y o p e r a t i o n s an d lunar sample re tu rn opera t ions were nor-m a l with t h e excep t ion o f t h e fo l lowing d i sc re pan c ies no ted du r ing com-

m a n d module inspect ion.

Otherwise, a l l

a. There was an appar ent chip (1- inch wide, 3- inches long, and 1/2-inch deep) i n t h e minus Z q ua dr an t o f t h e h e at s h i e l d a d ja c en t t o t h es m a l l h e a t s e n s o r, a bo ut 3 0 -i nc he s i n b o a r d f ro m t h e l i p of t h e h e a t s h i e l d .However, t h e h e a t s h i e l d c a n be c o n s i d e re d t o b e i n n or ma l p o s t - r e e n t r yc o n d i t i o n .

b . There w a s a f i l m l a y e r on a l l windows ranging from approximately10-percen t coverage on th e left s i d e window t o 100-percen t on t h e r ig h ts i d e window.

c. The backup method w a s u se d t o o b ta i n t h e water samples because

t h e d i r e c t o qr gen valve had been l e f t s l i g h t l y o p e n, c a u s i n g t h e p r im a ryp r e s s u r i z a t i o n s ys te m t o lose p r e s s u r e .

d . The c h l o r i n e c o n t e n t o f t h e p o t a b l e w a t e r w a s not analyzed ont h e s h i p b ec au s e of l a c k o f t i m e .

e . The Commander's radiation dosimeter w a s broken and no readingw a s obtai ned. The ot he r two dosimeters w e r e l e f t aboard t h e commandmodule.



1 2 -1

12.0 ASSESSMEI9T OF MISSION OBJXCTIVES

The fou r pr imary obj ect iv es ( r e f . 7 ) a s si g ne d t o t h e A po ll o 14 m i s -s i o n w e r e as fo l lows :

a. Perform se leno log i ca l inspe c t io n , su rvey, and sampling o f m a -t e r i a l s i n a p r e s e l e c t e d region of t h e F r a Mauro formation.

b. Deploy and act ivate th e Apol lo l un ar su r fac e exper iments package.

c. Develop 1 p ~ n ' s c a p a b i l i t y t o work i n t h e lunar environment .

d. Obtain photographs of c a n d i d a t e e x p l o r a t i o n s i t e s .

Eleven d e t a i l e d o b j e c t i v e s ( d e r i v e d from pr imary ob jec t ives ) and

All d e t a i l e d o b j e c t i v e s , w i t h th e fo l lowings i x t e e n e x pe ri m en ts ( l i s t e d in t ab le 12-1 and descr ibed i n r e f . 8) werea s si g n ed t o t h e m i s si on .e x c e p t i o n s , w e r e suc cess fu l l y comple ted :

a . Photographs of a c a n d i d a t e e x p l o r a t i o n s i t e

b. V i s i b i l i t y a t high sun a n g l e s

C. Camand and service module orb i ta l sc ience pho tography

d . Transear th l una r phutography

On t h e basis of p r e f l i g h t p la n ni ng data , these f o u r o b j e c t i v e s were o n l yp a r t i a l l y sa t is f ied .

Two de ta i l ed ob jec t iv es were added and w e r e performed during t rans-

l u n a r c o a s t: S-IVB photography and command and service mdule water-dumpphotography. The S-IW3 could not be i d e n t i f i e d on t h e f i l m dur ing p o s t -f l i g h t a n a l y s i s a nd , a l t h au g h sane p a r t i c l e s w e r e seen on photographs oft h e water dump, there was no ind ic at io n of th e "snow storm" des cr ib ed byt h e c r e w.

In a d d i t i o n t o t h e s p a c ec r a f t an d l u n a r surface o b j e c t i v e s , t h ef o l l o w i n g tw o l au n c h v e h i c l e o b j e c t i v e s w e r e assigned and completed:

Impact the expended S-IVB/instrumentation u n i t on t h e l u n a r.surfsce under nominal f l i g h t p r o f i l e c o n d it io n s .

b.

u n i t p o i n t of i m p a c t w i t h i n 5 kilom eters and th e time of impact with inm e second.

Make a p o s t f l i g h t d e te r m in a ti o n of t h e S-IVB/instrumentation



12-2

TABLE 12.1.- DETAILED OBJECTIVES AND EXPERIMENTS

Description Completed

D e t a i l e d o b j e c t i v e s

Contingency sample c o l l ec t i onPhotographs of 8 c a n d i d a t e e x p l o r a t i o n s i t eVi s i b i l i t y a t high sun anglesaModular equipment t r an sp or te r ev alu at i onS e l e n o d e t i c r e f e r e n c e p o i n t u p d a t eCommand and s er v ic e module o r b i t a l s ci en ce photographyA sse ss men t o f e x t r a v e h i c u l a r a c t i v i t y o p e r a t i o n l i m i t sCommand and se rv ic e module oxygen flow r a t eTranse ar th l un ar photographyThermal coat ing degradat ionD i m - l i ght photography

Experiments

Apollo lunar surface experiments package:M-515 Lunar dus t d e t e c t o rS-031 Lunar passive seismologyS-033 Luner ac t i ve seismologyS-036 S u pr at h er m al i o n d e t e c t o rS-058 Cold cathode gaugeS-038 Charged par t i c le lunar env i ronment

S-059 Lunar geology invest igat ionS-078 Laser rang ing re t ro - re f le c to rS-200 S o i l mechanicsS-198 Portable magnetometerS-170 B is ta t i c radarS-080 Solar wind composi t ionS-178 Gegenschein from lunar orbitS-164 S-band transponders-176 Apollo window meteroidM-078 Bone min er al measurement

YesP a r t i a lP a r t i a lYesYesP a r t i a lYesYesP a r t i a lYesYes

YesYesYesYesYesYesYesYesYesYesYesYesYesYesYesYes

5 r e l i m i n a r y a n a ly s is i n d i c a te s t h a t s u f f i c i e n t d a t a werec o l le c t ed t o v er i f y t h a t t h e v i s i b i l i t y a n a l y t i ca l modelcan be used for Apollo planning purposes .



12-3

Th e impact of th e S-IVB was det c t e d by t h Apoll 12 pas ive seismicexperiment.t e c t e d by both t h e Apollo 12 and Apollo 1 4 passive seismic experiments .

The impact of t h e spent lu na r module ascent sta ge was de-

12.1 PARTIALLY COMPLETED OBJECTIVES

12.1.1 Photographs of a Candidate Explorat ion Si te

Four ph oto qap hic passes t o ob ta i n Descar rtes l and ing da ta w e r e sched-one hig h-r eso luti on sequence w i t h the lunar topograph ic camera a tl e d :

low a l t i tu de , two h igh- reso lu t ion sequences with th e lunar topograph iccamera a t h ig h a l t i t u d e a nd one s t e r e o s t r i p w i t h t h e Hasselblad e l e c t r i cdata camera a t high a l t i t u d e .topographic camera pass, t h e camera malfunctioned and, although 192 frameswere obt ain ed of an area east of Descartes, no usable phutography was ob-ta in ed of Descartes . On th e subsequent hig h-al t i tu de photographic passes ,t h e e l e c t r i c Hasselblad camera with t h e 5OO-mm l e n s w a s used i n s t e a d oft h e lunar topographic camera.t a i n e d d u r in g t h r e e o r b i t s , b ut t h e r e s o l u t i o n was considerably lowert h a n tha t p o s s i b l e w i t h t h e lunar topographic camera.was encounte red dur ing th e s te r eo s t r i p pho tograph ic pass .command and service module S-band high-gain antenna d i d not ope rate prop-e r l y , no u s a b l e high-bi t -rate telem etry , and consequently, no cameras h u t t e r - o p e n da ta were o b t a i n e d f o r p o s t f l i g h t data reduc t ion .

On t h e low a l t i t u d e ( r e v o l u t i o n 4 ) l u n a r

Excellent Descarbes photography w a s ob-

Another problemBecause the

1 2 . 1 . 2 Vi s i b i l i t y a t H i g h Sun Angles

Four se ts of zero-phase observations by t h e Camand Module Pilotwere s ch ed u le d i n o r d e r t o o b t a i n data on l u n ar s u rf ac e v i s i b i l i t y a t

high sun ele va t io n ang les . The l a s t s e t , s ch ed u le d f o r r e v o l u t i o n 30,was de le ted t o provide another oppor tun i ty t o photograph th e Descar tesarea. Good data w e r e obtained fK>m t h e f i r s t t h r ee s e t s .

12.1.3 Command and Service Module O r b i t a l Science Photography

A l l obdec t ives w e r e completed with th e except ion of tho se t h a t spec-i f i e d u s e o f - t h e lunar topographic camera.c r a t e r area was phutographed using t h e e l e c t r i c H a s s e l b l a d 70-mm cameraw i t h t h e 500-mm l e n s as a s u b s t i t u t e f o r t h e i n op e rs b le l u n a r t o po g ra ph iccamera.

The Apollo 13 s-INB impact



12 4

12.1.4 Transear th L u n a r Photography

Excel lent photography of the lunar s u r fa c e w it h t h e e l e c t r i c Hassel-No l u n a r t o p o gr a p hi cl a d data camera using the 80-III~ e n s was obta ined .

camera photography was ob tain ed because of th e camera malfu nct io n.

12.2 INFLIGHT DEMONSTRATIONS

I n a d d i t i o n t o d e t a i l e d o b j e c t i v e s an d e x pe r im e nt s, f o u r z e r o - g r av i t yi n f l i g h t demonstrat io ns were conducted. They w e r e performed on a non-i n t e r f e r e n c e basis a t t h e c r e w' s o p t i o n . The f o u r i n f l i g h t d em o ns tr a-t i o n s and respo ns ib le NASA cen te rs were:

a.

b. . Heat flow an d convect ion - Marsha l l Space F l igh t Cen te r

c.

d. Composite casting - Marsha l l Space F l igh t Cen te r.

E l e c t r o p h o r e t i c s e p a r a t i o n - Marsha l l Space F l igh t Cen te r

L iq u id t r a n s f e r - L e w i s Research Center

1 2 . 3 APPHOVED OPERATIONAL TESTS

The Manned Spacecra f t Cen te r pa r t i c ip a t ed i n two of e i gh t approvedo p e r a t i o n a l t e s t s .j e c t i v e s of t h e m i ss io n , do not a f f e c t t h e nomina l t im el i ne , and addno payload weight. l u n a r g r a v i t y mas-urement (u s in g th e lun ar md ul e p r imary gu idance sys tem) and a hydro-gen maser t e s t ( a Network and u n i f i ed S-band in ve s t i ga t io n sponsored bythe Goddard Spacef l igh t Cen te r ) .su l t s of t h e hydrogen maser t e s t are g iv en i n r e f e r e n c e g .

Opera t iona l t e s t s ar e n o t r e q u i r e d t o m e t t h e o b -

The two operat ional t e s t s were:

Both t e s t s were completed, and t h e re-

The o ther s ix t e s t s were performed for the Department of Defensean d t h e Kennedy Space Ce nte r. These t e s t s are d e s i g n a t e d as fo l lows .

a . Chapel B e l l ( c l as s i f i e d Depar tment o f Defense t e s t )

b . R a d a r Skin Tracking

c. Ionosph eric Disturbance from Missiles

d . Ac ou stic Measurement of M is si le Exhaust Noise

e . Army Acoust ic T e s t

f . Long-Focal-Length Optical System.

fr i

T

L-



13-1

13.0 LAUNCHPHASE SLMARY

13.1 WEATHERCONDITIONS

Cumulus clouds existed i n the launch complex area w i t h t o p s a t15 000 fee t 20 minu tes p r io r t o t h e scheduled launch and w i t h t o p s a t18 000 f e e t 1 0 m i nu te s l a t e r .t r i c f i e l d meters c l e a r l y s h o w e d f l u c t u a t i n g f i e l d s c h a r a c t e r i s t i c ofm i l d l y d i s t u r b e d we a th e r c o n d i t i o n s .a l low a launch through cumulus clouds w i t h t o p s i n e x ce s s of 10 0 0 0 f e e t ,a 40-minute hold w a s r e q u i r e d b e f o r e a p e r m i s s i b l e w e at h er s i t u t a t i o nexis ted . A t l a u n c h , t h e c l o u d bases were a t 4000 f e e t w i t h t o ps t o10 000 f e e t . The l aunch under these cond i t ions d i d not enhance thec l o u d e l e c t r i c f i e l d s enough t o produce a l i g h t n i n g d i s ch a r g e, t h u sp r o v i d i n g f u r t h e r c o n f i d e n c e i n t h e presen t l aunch miss ion ru les .

During t h i s t i m e , t h e ground-based elec-

S i n c e t h e m is s io n r u l e s do n o t

13.2 ATMOSPHERIC ELECTRICITY EXPERIMENTS

As a result of t h e l i g h t n i n g s t r i k e s e x p e r ie n c e d d u r i n g t h eApollo 12 l aunch , seve ra l exper imen t s were pe r fo rmed dur ing t h e launchof Apollo 13 and Apollo 1 4 t o s tu dy t h e e f f e c t s o f t h e space veh ic le ont h e a tm o sp h er ic e l e c t r i c a l f i e l d d ur i n g l a un c h.t h a t t h e e f f e c t s c o u l d be r e l a t e d s im pl y t o t h e e l e c t r i c a l - f i e l d -enhancement factor of t h e veh i c le . However, t h e r e s u l t s o f t h e A p o l l o 1 3measurements showed t h a t t h e space veh ic le p roduced a much s t r on ge r e le c-t r i c a l f i e l d d i s t u r b a n c e t h a n h ad be en e x p e c te d a nd a l s o p ro du ce d somelow-frequency ra d io no ise . This di st ur ba nc e may have been caused by ab u i l du p of e l e c t r o s t a t i c c ha rg es i n t h e exhaust c loud , cha rge bu i ldup on

t h e v e h i c l e , o r a combinat ion of both of these sources . To de f ine t h eo r i g i n a nd t h e c a r r i e r s o f t h e charge , ad d i t io na l experiment s were pe r-formed dur ing the Apol lo 1 4 l au nc h t o s t u d y t h e e l e c t r i c f i e l d phenomenai n m ore d e t a i l , t o m eas ur e r a d i o n o i s e , an d t o m eas ur e t h e t e m pe r at u reo f t h e S a t u r n V ex ha us t plume, which i s an impor tan t pa rameter i n ca lcu -l a t i n g t h e e l e c t r i c a l b r e a k d m c h a r a c te r i s t ic s o f t h e e x h a u s t .l i m i n a r y f i n d i n g s o f t h e se experiments are given here. When a n a l y s e s o fdata have been completed, 8 supp lementa l r epor t w i l l be i s s u e d ( a p p e n d i x E ) .

I n i t i a l l y , i t w a s hoped

The pre -

13.2.1 Elec t r i ca l F ie ld Measurement s

A tm o sp he ri c e l e c t r i c a l f i e l d m ea su re men ts were made by t h e New

M e x i c o I n s t i t u t e of Mining and Technology and the Stanford Research In-s t i t u t e at t h e l o c a t i o n s s h a m i n f i g u r e 1 3- 1. I n a d d i t i o n , a f i e l dmeasur ing ins t rument ( f i e l d m i l l ) w a s i n s t a l l e d on t h e l au nc h u m b i l i ca l



13-2

F i e l d m i l lno .

1234567 .89

1011121314

Distance from launchcomplex A , meters

750377655

1650375300

167514801600

800380400800

On launch umbilicaltower

Azimuth,de9

194970

11614825827034 8270300270210180

0

Fi el d mi ll instruments 1 hrough 8 wereprovided by New Mexico Institute of Miningand Technology. The remainder of theinstruments were provided by StanfordI'Research Institute.

F i g u r e 13-1.- F i e l d mill l o c a t i o n s a t t h e l a u n c h s i t e .

tower t o de t ec t any charge bu i ldup on th e veh ic le dur ing ig n i t io n and th ei n i t i a l s ec on ds a f t e r l i f t - o f f . A cc ur ate t im i n g s i g n a l s , w hich were n otavai lable on Apollo 13 , were p rov ided t o mos t o f t h e f i e l d measurementequipment locations on Apollo 1 4 .cloud were also t ak en t o a i d i n t h e i n t e r p r e t a t i o n o f t h e d at a . L ik eApollo 13 , th e Apollo 1 4 launch produced a s i g n i f i c a n t e l e c t r i c a l dis-t ur ba nc e i n t h e f i e l d m i l l r e c o r d s ( f i g . 13-21, Although t h e dat a a res t i l l being analyzed, some preliminary observations can be made.

W i o r t o t h e Apollo 13 l a u n c h , t h e f i e l d m i l l s i n d i c a t e d s t a b l eBefore the Apol lo 1 4

Time-lapse photographs o f th e launch

f ine-wea ther f i e ld s o f 100 t o 200 v o l t s p e r m e te r.l a u n c h, h o we ve r, t h e f i e l d s w er e f l u c t u a t i n g s e v e r a l h un dr ed v o l t s p e rmeter, po s i t iv e and nega t ive . Th is behav ior w a s e n t i r e l y c o n s i s t e n t w it ht h e d i f f e r e n c e i n weather condi t ions - ood condi t io ns f o r Apollo 13 bu tmi ld d i s tu rbances f o r Apol lo 1 4 .



13-4

During the Apollo 13 l a u n c h , t h e i n s t r u m e n t s a t s i t e s w e s t o f t h elaunch complex regis tered a smooth p o s i t i v e f i e l d i n c r e a s e , s u cc ee d edby a l e s s pronounced ne ga tiv e exc urs ion . For Apollo 1 4 , t h e n e g a t i v eexcurs ion w a s not ev iden t ; h ow ever, t h e f i e l d v a r i a t i o n s o c c u r r e d at ap-p r o x i m a te l y e q u i v a l e n t t i m e s f o r b o t h la u n c h e s. The p o s i t i v e e x c u r s i o nw a s approx imate ly f ive t imes g r e a t e r f o r Ap oll o 13 t h a n f o r A p o l lo 1 4 ,and reached m a x i m u mwhen the space vehicle w a s at a l t i t u d e s g r e a t e r t ha n1000 meters. This observ a t ion , coup led wi th t h e f ac t t h a t t he maximume l e c t r i c f i e l d s were observed downwind on both launches makes it u n l i k e l yt h a t t h e s p a c e v e h i c l e c h a rg e w a s t h e dominant f a c t o r b u t , r a t h e r , t h a tt h e p o s i t i v e l y c ha rg ed c l o u ds were t h e d ominant s o u r c es o f t h e e l e c t r i cf i e l d s .

D ur in g l i f t - o f f , t h e s w i f t l y moving e x h au s t c l o u ds a re channeledboth nor th and sou th th rough th e f lame t roug h . The p r in c i pa l c loud whichmoved through the north end of the flame t rough w a s composed largely ofcondensed spra y water and con tain ed a pos i t ive charge o f approx imate ly50 millicoulombs and a f i e l d o f a p p r o x im a te l y 4000 v o l t s / m e t e r ( S i t e 2o f f i g . 13-2) . The c loud th a t exhaus ted t o t h e so u th had much l e s s w a t e r

and contained about a 5-millicoulomb ne ga tiv e charg e. The cloud a l s o ap-p ea re d t o c o nt ai n s o l i d p a r t i c u l a t e mat te r which r a p i d l y f e l l o u t .

T h e f i e l d mill on th e l aunch umb i l i ca l tower ind ica ted a s m a l l pos i -t i v e v a l u e (<400 v o l t s / m e t e r ) a f e w seconds a f t e r l i f t - o f f . M o d e l m e a s -urements using a l / lbb -sca le model o f th e l aunch umbi l i ca l tower and th eA po ll o/ Sa tu rn v e h ic l e i n d i c a t e d t h a t , i n t h i s c o n f ig u r a ti o n , t h e l au nc hu m b i li c a l to we r f i e l d and t h e v e h i c le p o t e n t i a l are r e l a t e d by v o l t s /f i e l d = 20 meters. Thus, t h e v e h ic l e p o t e n t i a l i s l e s s t h a n 8 0 0 0 v o l t s(400 x 2 0 ) . A comparison of t h e l aunch umbi l i ca l tower recor d wi th th ed a t a f r o m t h e o t h e r s i t e s i n d i c a t e s t h a t t h e c h arg e on t h e v e h i c l e a p-p ea rs t o b e l e s s t h a n 1 mill icoulomb.

13 .2 .2 Radio Noise Measurements

Narrow-band r ad io re ce iv er s oper at i ng a t f r e q u e n c i e s of 1 . 5 , 6 , 2 7 ,5 1 , and 120 kHz were l o c a t e d at camera pad 5 ( f i e l d m i l l s i t e 11) t o -g e t h e r w i th a broadband detector. A s i n t h e case of Apollo 13, s i g n a l swere d e t e c t e d a t s e v e r a l d i f f e r e n t f r eq u e nc i es , b u t t h e t i m e behav ior ofdifferent f requency components w a s n o t t h e same d u r i n g t h e two l aunches .

The loop-antenna d a t a ( f i g . 13-31 i n d i c a t e a l a r g e increase i n n o i seon t h e 1.5-kHz and 6 - k ~ ~ hannels 3 Seconds a f t e r e n g i n e i g n i t i o n , w h i l eth e no ise on th e 51-kHz channel did not beg in u n t i l 2 seconds a f t e r lift-o ff ( a b o u t 11 seconds a f t e r i g n i t i o n ) . I n i t i a l l y , i t a pp ea re d t h a t t h e1 .5 - and 6 - k ~ ~a t a m ig ht n o t r e p r e s e n t r a d i a t e d e l e c t r o m a g n e t i c n o i s e ,ra th er , mic rophonic n o i se genera ted by some component of t h e system suchas t h e l o o p a n te n n a p r e a m p l i f i e r. P r e l im i n a r y d a t a from t h e e l e c t r i c



13-5

NASA-S-71-1667

td

al

5 1.000

.- 0.100

0.300m

E

0.030

8l 0.001al.-

L

1(4:02:54gnition p . i i i . ) A L i i f t - o f f (4:i)3:02 .iii.1I

II I I I-~

0 20 40 60 80 100)

0

2-40 -20.-

Time from l i f t -off , SC C

Fig ure 13-3.- Noise recor ded by loop an tenna sys tem.

d i p o l e a n te n n a a t camera pad 5, however, ind ica te t h e same g e n e r a l be-h a v i o r, a n d as t h e two antenna systems use s e p a r a t e a m p l i f i e r s , it appearst h a t t h e d a t a ar e v a l i d .by b o t h s ys te ms p r i o r t o t h e loss o f t h e 51-kHz n o i s e i s not unders toodand f u r t h e r s t u d i e s o f t h e n oi s e d a t a are present ly being made.

A n a b r up t c e s s a t i o n of t h e 1.5- and 6 - k ~ ~o i s e

13.2.3 Plume Temperature Measurements

The t e mp e r at u re c h a r a c t e r i s t i c s o f t h e S at u r n V exhaust plume weres t u d i e d f r o m a s i t e about 5 miles w e s t of the launch complex using a two-channe l rad iomete r sys tem opera t ing at 1.26 and 1.68 microns. The rad io-meters viewed a n a r r o w h o r i z o n t a l s e c t i o n o f t h e exh aus t plume which, i nt u r n , p r o v i d e d t e m p e r a t u r e as a fu nc t io n of d is ta nc e down th e plume asth e veh i c le ascended ve r t i c a l ly . F igure 13-4 shows th e measured p lumetempera tu re as a f u n c t i o n of d i s t a n c e be h in d t h e v e h i c l e . These r e s u l t sare now being used t o im pr ov e t h e t h e o r e t i c a l c a lc u l a t i o n s of t h e e l e c-t r i c a l c h a ra c te r i s t i cs o f t h e exhaust plume. I t appears t h a t the plumemay be a r e a s o n ab l e e l e c t r i c a l c o n du ct or o v er a length of some 200 f e e t .This result i s c o n s i s t e n t w i t h t h e low v a l u e o f v e h i c l e p o t e n t i a l whent h e v e h i cl e is pass ing the l aunch umbi l i ca l tower f i e l d meter s i n c e , a tt h a t t i m e , t h e v e h i c l e i s probably s t i l l e f f e c t i v e l y c on ne ct ed e l e c t r i c -a l l y t o e a r th . (Refe rence 10 con ta in s a dd i t io na l in format ion concern ingplume temperature measurements. 1



13-6

NASA-S-71-1668

Figure 13-4.- ESrhaust plume temperature character is t ics .

1 3 . 3 LAUNCH VEHICLE SUMMARY

The s ev en th manned Sa tu rn V Apol lo space veh ic le , AS-509, waslaunched on an azimuth 90 degrees eas t of nor th . A r o l l m an eu ver wasi n i t i a t e d a t 1 2. 8 s ec on ds t h a t p l a c e d t h e v e h i c l e on a f l i g h t a z i m t hof 75.558 degrees ea s t of nor th . The t r a j ec to ry paramete rs f rom launcht o t r a n s l u n a r i n j e c t i o n w ere c l o s e t o n om in al w it h t r a n s l u n a r i n j e c t i o nachieved 4 .9 seconds e a r l i e r t h a n nominal.



13-7

All S-IC p r o p u l si o n sy st em s p er fo rm ed s a t i s f a c t o r i l y . To t a l p ro -pe l l an t consumpt ion r a t e w a s 0.42 p e r c e n t h i g h e r t h a n p r e d i c t e d w i t h t h econsumed mixt ure r a t i o 0.94 p e r c e n t h i g h e r t h a n p r e d i c t e d . S p e c i f i c i m -p u l s e w a s 0 .23 pe rcen t h ig her than p red ic ted .

The S-I1 p ropu l s ion system performed sa t i s fa c t o r i l y. To t a l p r o p e l-l a n t f l o w r a t e w a s 0 .12 pe rcen t below pred ic te d and sp ec i f i c impulse w a s0 .1 9 p e r c e n t below p r e d i c t e d . P r o p e l l a n t m i x tu r e r a t i o w a s 0.18 p e r c e n tabove predicted.v a lv e s o p e ra t e d s a t i s f a c t o r i l y . E ngine s t a r t t ank cond i t ions were mar-g i n a l a t s-I1 engine s t a r t command be ca us e of t h e lo wer s t a r t t a n k r e -l i e f valve set t ings caused by warmer- than-usual s t a r t t a n k t e m p e r a t u r e s .These warmer temperatures were a resul t of t h e h o ld p r i o r t o l au nc h.

The pneumatically actuated engine-mixt ure- r a t i o c o n t r o l

The S-IVB s t ag e engine opera ted sa t i s fa c to r i ly th roughout t h e oper-a t i o n a l p h a s e o f f i r s t and second f i r i n g s and had normal shutdowns. TheS-IVB f i r s t f i r i n g t im e w a s 4 . 1 s ec on ds l e s s t h a n p r e d i c t e d .a t t h e f ul l- op en p r o p e l l a n t u t i l i z a t i o n v a lv e p o s i t i o n w a s s u c c e s s f u l .

S-IVB se cond f i r i n g t i m e w a s 5.5 s ec on ds l e s s t h a n p r e d i c t e d . The t o t a lp rope l l an t consumpt ion ra te w a s 1.38 p e r c e n t h i g h e r t h a n p r e d i c t e d f o rt h e f i r s t f i r i n g and 1 .47 p e r ce n t h i g h e r f o r t h e s ec on d f i r i n g .impulses f o r each were p ropo r t iona l ly h i gher.

The r e s t a r t

S p e c i f i c

The s t ru c tu ra l loads exper ienced were be low des ign va lue s .i m u m dynamic pressure period bending moment a t t h e S - I C l iqu id oxygent a n k w a s 45 p e r c e n t o f t h e d es ig n v a l u e .were s i m i l a r t o t ho s e o f p re vi ou s f l i g h t s .l i q u i d oxygen f e e d l i n e a cc um ul at or s u c c e s s f u l l y i n h i b i t e d t h e 14- t o1 6 -h e rt z l o n g i t u d i n d o s c i l l a t i o n s e x p er i e nc e d on p r e vi o u s f l i g h t s . Dur-in g t h e maximum dynamic p ressure reg ion o f f l i g h t , t h e l aunch veh ic le ex-per ienced winds t h a t w er e l e s s t h a n 9 5 - p e r c e n ti l e J a nu a ry w in d s.

The max-

The t h r u s t c u t of f t r a n s i e n t sThe S- I1 s t a g e c e n t e r e n g in e

The S-IVB/instrument un i t lunar impac t w a s accompl i shed success f i l ly .A t 82:37:52.2 elapsed t i m e from l i f t - o f f , th e S-IVB/ins trument un i t i m -p a c t e d t h e lunar s u r f a c e a t approximately 8 degrees 5 minutes 35 secondss ou th l a t i t u d e and 26 degrees 1 minute 23 seconds west lon gi t ude , approx-imate ly 150 miles from t h e t a r g e t of 1 degree 35 minutes 46 seconds southla t i tude and 33 degrees 15 minutes west longi tude. Impac t ve loc i ty w a s,8343 f t l s e c .

The ground systems, supporting countdown and launch , erformed s a t -i s fa c to r i ly . Sys tem component f a i lu re s an d malfunc t ions requ i r ing cor-re c t i ve a ct io n were c orrect ed du r ing countdown without causing unscheduledh o l d s . P r o p e l l a n t t a n k i n g wa s a cc om pl is he d s a t i s f a c t o r i l y . Damage t o t h epad, launch u m b i l i c a l t o w e r, and support equipment w a s minor.



1 4 - 1

14.0 ANOMALYSUMMARY

T h i s s e c t i o n c o n t a i n s a d i s c u s s i o n o f t h e s i g n i f i c a n t a n o m a l i e sThe d i s c u s s i o n o f t h e s eh a t o c c ur r ed d u r i n g t h e A p ol lo 14 m i s s i o n .

items i s d i v i d ed i n t o f o u r m aj or areas : command and s e r v i c e modul es;l u n a r module ; government-furnished equipment ; and Apol lo lunar su r faceexper iments package.

1 4 . 1 C O W D AND SERVICE MODULES

14.1.1 F a i l u r e t o Achieve Docking Probe Capture Latch Engagement

S ix dock ing a t t empts w e r e r e q u ir e d t o s u c c e s s f u l l y a c hi e ve c a p t u rela tc h engagement dur ing t h e t r a nsp os i t ion . and dock ing even t .i n f l i g h t examina t ion o f t h e p robe showed normal ope ra t ion o f th e mecha-nism. The lu na r o r b i t undocking and docking were completely normal. Data

a n a l y s i s o f f i l m , a c c e l e r om e t e r s , a nd r e a c t i o n c o n t r o l s y s t em t h r u s t e ra c t iv i t y ind ic a te s t h a t probe- to -d rogue con ta c t cond i t ions were normalf o r all dock ing a t t em pts , and cap tu re shou ld have been ach ieved fo r th ef i v e u n s u c c e s s f u l attempts ( t a b l e 14-11. The cap tur e-l atc h assembly mustn o t h a ve b ee n i n t h e l o c k e d c o n f i g u ra t i o n d u r i n g t h e f i r s t f i v e a t t e m p t sb a s e d on t h e f o l l o w i n g :

Subsequent

a. The probe s t a t u s t a l k b a c k d i s p l a y s f u n c t i o n e d p r o p e rl y b e f o r ean d a f t e r t h e u n s u c c e s s f ul a t t e m p t s , t h u s i n d i c a t i n g p r o pe r s w i t c h o pe r-a t i o n a nd power t o t h e t a l k b a c k c i r c u i t s . The t a l k b a c k d i s p l a y s a l w a y si n d i c a t e d t h a t t h e c a pt u re l a t c h e s w e r e i n t h e c o c k e d p o s i t i o n d u r i n gt h e u n s u c c e s s f ul a t t em p t s ( f i g . 14-1 ) . ( No te t h- a t n o e l e c t r i c a l p oweri s r e q u i r e d t o c a p t u r e b ec a us e t h e s y st e m i s cocked p r i o r t o f l i g h t and

t h e c a p t u r e o p e r a t i o n i s s t r i c t l y me ch an ic al and t r i g g e r e d by t h e d ro gu eb . Each o f th e s i x marks on t h e d rogue re su l t ed from se pa ra t e con-

t a c t s by t h e p r o be h ea d ( f i g . 1 4 -2 ) . A lt hou gh t h r e e o f t h e m arks a r eapproximately 120 degrees a p a r t , a docking impact wi th locked capturel a t c h e s s h o u l d r e s u l t i n t h r e e d ou bl e mark s ( t o match t h e l a t c h h oo ks )I20 d e g re e s a p a r t , a nd w i t h i n one i n c h o f t h e d ro gu e a pe x o r s o c k e t .A lt ho ug h t h e d r og ue ma rk s c o u l d i n d i c a t e t h a t t h e i n d i v i d u a l c a p t u r e-l a t c h hooks were d i f f i c u l t t o d e p r e ss , s uc h marks a re not abnormal fori m p a c t v e l o c i t i e s g r e a t e r t h a n 0.25 f e e t per second .

S i nc e t h e l a t c h e s w e r e not locked, t h e anomaly w a s apparen t ly causedby f a i l u r e o f t h e c a p t u re - l a t ch p lu n ge r ( f i g . 14-11 t o r e a c h t h e f or wa rd

or locked pos i t ion . Mot ion o f the p lunger cou ld have been re s t r i c t e d by



14-2

aaJIn5

nw

3wp:

I

HI

3d

I

L

d d

ak



Figure 14-1.- Cross s e c t i o n of probe head and captu re-la tch assembly.



con tamina t ion o r d imens ional changes due t o t empera tu re . In t e r n a l dam-age t o t h e cap tur e-l atc h mechanism can be r u l e d o u t b e ca u se t h e s y s t e m -f u n c t io n e d pr o p e r ly i n a l l subsequen t opera t ions f ol lo w in g t h e s i x t hdock ing a t t empt and d ur in g p o s t f l i g h t t e s t i n g . .

Analyses were p er fo rm ed t o i n v e s t i g a t e t o l e r a n c e s and the rmale f f e c t s on m at in g p a r t s a nd s u r f a c es a s s o c i a t e d w i t h t h e o p e r a t i o n o ft h e c a p t u r e l a t c h e s . The r e s u l t s i n d i c a t e t h a t n e i t h e r t e m pe ra t ur e n ort o l e r a n c e s c ou l d h ave c a us ed t h e p ro bl em . I n a d d i t i o n , a thermal analy-s i s snows t h a t n e i t h e r t h e l a t c he s n or t h e s p i de r cou ld have been jammedb y i c e .

Te s t s using q u a l i f i c a t i o n p ro be s t o d e te r mi n e c a p tu r e - l at c h r e sp o ns emeasurements w e r e made and showed no a ging de grada t ion of t h e system.Tension t i e t e s t s produced c le a r ly she ared p in s ; however, i n one t e s t , as h e ar e d p o r t i o n o f t h e p i n d i d l ea ve t h e t e n s i o n t i e with some v e l o c i t ya nd la nd ed o u t s i d e t h e r i n g i t s e l f .

No c o n t a m i n a t i o n , c o r r o s i o n , s i g n i f i c a n t d e b r i s , o r f o r e ig n materi-

a ls were found, and t h e mechanism worked normal ly d ur in g all f u n c t i o n a lt e s t s . The loads an d response t i m e s compared with t h e s p e c i f i c a t i o n sand w i t h t h e pr ob e p r e f l i g h t d a t a .a ss em bl y t o r q u e v a l ue s ( s t a t i c d ra g a nd c a p t u r e - l a t c h r e l e a s e ) c om paref a v o r ab l y w i t h p r e f l i g h t v a l u e s .

Motor torque values and actuator

D uri ng t h e i n s p e c t i o n , s m a l l s c r a t c h e s a nd r e s u l t i n g b u r r s wereThe sc ra tches

A n anomaly report w i l l be i s s u e d un de r s e p a r a t e c o v e rf ou nd on t h e t e n s i o n t i e plug w a l l a d ja c e nt t o t h e p l un ge r.are be ing ana lyzed .when t h e i n v e s t i g a t i o n h a s b e en c om pl et ed .

The m o s t probable cause o f t h e p roblem w a s c o n t a m i n a t i o n o r d e b r i swhich l a t e r became dis lodged.

p ro be t i p f rom f o r e i g n material e n t e r i n g t h e mechanism p r i o r t o f l i g h t .

A cover w i l l be p ro vi de d t o p r o t e c t t h e

This anomaly i s open.

14.1 .2 High-Gain Antenna Tr ac ki ng Problems

D u r i n g t r a n s l u n a r c o a s t an d l u n a r o r b i t o p e r a t i o n s , o c c a s i o n a l pro b-

T h e s p e c i f i c times of high-lems w e r e encoun te red ' i n acqu i r ing good h igh-ga in an tenna t r a ck in g wi the i t h e r t h e p ri ma ry o r s ec on da ry e l e c t r o n i c s .g a i n a n t e n n a a c q u i s i t i o n a n d t r a c k i n g p r o b l e m s were :

a . 76:45:00 t o 76:55:00b . 92:16:00 t o 93:22:00c . 97:58:00 o 98:04:02d. 99:52:00.



14-6

MMode select f

An ins t rumenta t ion p roblem wi th th e an tenna readout occur red f o rabout 3 hours ea r ly i n th e mission when an e r ro r o f about 30 degreesex i s t ed . Subsequen tly, th e read ings were normal. A mechanica l in te r-fe rence i n t h e i n s t r um e n t s e r v o s i s t h e m ost l i k e l y c a u se . The i n s t r u -ment servos a re an independen t loop which d r iv e th e an tenna p i t ch and '

yaw me ter s i n t h e command module.th e servo s do not a f fe c t th e antenna performance f o r any modes of oper-a t i o n .

No c o r r e c t i v e a c t i o n i s planned s ince

A A M A AR A ARJ

The ground data si gn at ur es which show th e f i r s t a c q u i s it i o n andt r a c k i n g problems a r e i l l u s t r a t e d i n f i g u r e 14-3.t r a c k i n g a point approximately 5 t o 8 d eg re es o f f t h e e a r t h p o i n t i n gangle a t 76:45:00 e l a p s e d t i m e and con t inued t rack ing w i t h l o w upl inkand d o w n l i n k s i g n a l l e v e l s f o r 10 minutes a t which t i m e a good narrowbeam lock-up w a s achieved.

The a n t e n n a s t a r t e d

N A S A - S - 7 1 - 1 6 7 1-75 d&n

-9 5 dBm to -93 dBmUplinksignal

Goodtracking

iTracking problem

-103 dBiiiBeani switchiiio M

-120 dBin

Downlink

I I 1 I II I I

1 1 I 4

76:44 7 6 : 4 6 7 6 : 4 8 7 6 : 5 0 7 6 : 5 2 76:54 7 6 : 5 6Elapsed tiiiie froiii lift-off, hr:iiiiti

Figure 14-3.- Data from f i r s t period of anomalous operation.



Th e l o w s i g n a l s c o r r e l a t e w i t h antenna p a t t e r n a n d g a i nThe d- t o S - e g r e e b or es ig ht s h i f t i n t h e wide-beam mode.

f o r a- on of

t h e sp ikes observed on t h e d ownlink d a t a i n f i g u r e 14-3 are c o n s i s t e n twith swit chin g between t h e wide and narrow beams.m a l alignment and a misalignment o f t h e wide and narrow beams a r e showni n f ig u re 14-4. A 5- t o 8 -d eg re e s h i f t i n t h e wide-beam mode boresight

C o n d it io n s f o r a nor-

NASA-S-71-1672

Narrow and wide beam boresight

Nanow beam

Remain in tiarrow beam iftarget is iii f 3 degree shaded

Switch to narrowbeam when target i sin this f l egreeshaded region

Side lobe

-20 -15 -10 -5 0 5 10 15 20Off boresight, degrees

(a) Normal wide beam/narrowbeam antenna alignment patterns.

-Narrow beam boresight

Wide beamboresight

Wide

bores

beam

m > Wide beam,ight shift

d a t arect

-20 -15 -10 -5 0 5 10 15 20Off boresight, degrees

(b) Alignment conditions indicatedby Apollo 1 4 data.

Figure 14-4.- Antenna narrow and wide beam boresight relationship.Figure 14-4. - Antenna narrow- and wide-beam bo re si gh t re la ti o ns hi p .



14-8

w i l l no t a l low narrow-beam loc k s i nc e cont inuous swi tchin g between t h ewide beam and narrow beam w i l l o cc ur wi th t h e t a r g e t o u t s id e t h e 23-degree l i m i t o f t h e narrow-beam b o r e s i g h t . T he se l a r g e e r r o r s i g n a l sw i l l i n i t i a t e cy cl ic s witc hing between t h e wide-beam and narrow-beammodes.

The a c q u i s i t i o n and t r a c k i n g pr ob le ms f o r t h e o t h e r t i m e p e r i o d s

were s imi l a r. As a r e s u l t of t h e 5- t o &degree b o re si gh t s h i f t o f t h ewide beam, t h e antenn a at t im es would lock-up on t h e f i r s t s i d e l o b ei n s t e a d o f t h e main l o b e ( f i g . 1 4 - 4 ) . S i n ce t h e a n t e nn a a r r a y i s n o ts y m m e tr i c al , t h e b o r e s i g h t e r r o r i n t h e wide-beam mode i s a f u n c t i o n o ft h e t a rg e t ap pr oach p a t h .

A number of p ro ble ms c o u l d h av e ca u se d t h e e l e c t r i c a l s h i f t o f t h ewide beam; however, they e f fe c t i ve ly reduce t o an in t e r ru p t io n o f one o ft h e four wide-beam elemen ts which su ppl y s ig n al s t o t h e wide-beam com-pa ra t o r . The most l i ke ly cause i s t h a t a c o nn e ct o r t o one o f t h e c o a x i a lcables which are used t o connect th e wide-beam antennas t o t h e comparatorassembly o f t h e s t r i p l i n e s w a s f a u l t y .

I n s u p p o r t o f t h i s c a u s e , f i v e ba d c o a x i a l c e n t e r c o n d uc t or s h av ebeen found. Also, a c o a x i a l c o n n e c t o r w a s disconnec ted on the an tennaa n d t h e e f f e c t i n t h e beam o c c u r re d . T h er e a re two causes o f t h e p roblemwi th the cen te r conduc tor, bo th o f which occur dur ing cab le - to -connec torassembly ( f ig . 1 4 - 5 ) . The s l e eve i s a ss em bl ed t o t h e c a b l e , a Lexani n s u l a t o r i s t h e n s l i p p e d o v er t h e c e n t e r c o n du c to r , and t h e p i n i s in-s e r t e d o v e r t h e c e n t e r c o n d u ct o r a nd s o l d e r e d . If t h e w i r e g e t s t o o h o tdur ing so ld er in g, t h e Lexan grows and no long er f i t s l o o s e l y t h r o u g h t h eh o l e i n t h e o u t e r bo dy. When t h i s o c c u r s an d t h e o u t e r body i s screwedo n to t h e s l e e v e , t h e w i r e can be t w i s t e d a nd t h e c e n t e r c on d uc to r m a yf a i l .

Another poss ib le fa i l u re occurs when too much s o l de r i s u se d o r t h ew i r e i s n o t c e n t e r e d i n t h e p i n . T hese c o n di t io n s w i l l b i nd t h e p i n t ot h e o u t e r body i n s u l a t i o n a n d , d u r i n g as se m bl y, t h e w i r e i s t w i s t e d t of a i l u r e . T he se c o n d i ti o n s are bein g cor rec ted by reworking a l l connect-ors a n d a p pl y i n g p r o p e r i n s p e c t i o n a nd c o n t r o l p r o ce d u re s d u r i n g t h e re -work.

F a i l u r e s on p re vi ou s f l i g h t s , i n a d d i t io n t o t h e o ne on t h i s m i s s io n ,w e r e o f t h e t y pe t h a t a p p ea r u n d er c e r t a i n th e r m a l c o n d i t i o n s . The m a l -f u n c t i o n c o n d i t i o n s o f e ach o f t h e f a i l u r e s were i s o la t ed t o d i f f e re n tcomponents o f t h e antenna. A l l of t h e s e d e f e c t s were of a ty pe whichc ou ld e sc ap e t h e t e s t s c r ee n i ng p ro c es s .shock which an an tenna exper ien ces dur ing t h e spac ecra f t - lu nar module

a d a p t e r s e p a r a t i o n when t h e p y r o t e c h n i c s f i r e might have caused defects

A n o t h e r p o s s i b i l i t y i s t h a t t h e

i n t h e c i r c u i t r y w hich c o ul d op en up u n de r c e r t a i n t h e r m al c o n d i t i o n s

1 . .1 I L i L ; L L l - Y - - Y A 1- A - L A- L- A- -



14-9

NASA-S-71-1673

Sleeve

Outer body

Lexan insulatorr

p i n J I uter bodyi is 1la t on

Note: A s l ip f i t i s required between the pitiand insulator so that the pin does not rotatewhen turning outer body during assembly of th ethreaded sleeve.

Figure 14-5.- Coaxial cable f a i l u r e s .



14-10

d u r i ng t h e m is si on . The o r i g i n a l q u a l i f i c a t i o n t e s t s c o ns id e re d t h a t t h eshock environment would be low.

To f u r t h e r i n v e s t i g a t e t h e e f f e c t s o f t h e s p a c e c r a f t- l u n a r moduleadap te r pyro techn ic shock on an an tenna , a shock t e s t has been conducted.The r e su l t s show th a t th e an tenna exper iences about an order-of-magnitudeg r e a t e r s ho ck t h an h a d b ee n o r i g i n a l l y a n t i c i p a t e d .t e s t i n g of t h e a n t e nn a h a s s hown no d e t r i m e n t a l e f f e c t s b e c au s e o f t h eshock. To b e t t e r s c r e e n o u t d e f e c t s which p o t e n t i a l l y c ou ld a f f e c t t h ef u n c t i o n i n g o f t h e a n t e n n a , a thermal acceptance t e s t w i l l be performedon all f u t u r e f l i g h t a n t e n n a s w h i l e r a d i a t i n g a n d u n d e r o p e r a t i n g c o n -d i t i o n s .

However , h e r m a l

T h i s anomaly i s c losed .

14.1.3 Urine Nozzle Blockage

After t r a n s p o s i t i o n and docking and p r i o r t o i n i t i a t i n g p as si vet h er m al c o n t r o l , t h e crew i n d i c a t e d t h a t t h e u r i n e n o zz le ( f i g . 14-6)

NASA-S-71-1674

Main Main

Dumpnozzle

Figure 14-6. - Urine recep tac le a n d nozz le .

5



14-11

w a s o b s t r u c t e d . T he same c o n d i ti o n o c c u r r e d s e v e r a l o t h e r t i m e s d u r i n gt h e m is s io n a n d , i n e ac h c a s e , t h e dump nozzl e had no t been exposed t os u n l i g h t f o r p ro lo ng ed p e r i o d s.

The he a te r s and c i rc u i t ry were checked and found t o be normal. Thesys tem des ign has been prev ious ly ve r i f i e d under some, bu t no t a l l , l i k e l yt h e r m a l c o n d i t i o n s w h i l e dumping u r i n e . A lt ho ug h t h e h i s t o r y o f p r e v i o u smissions has shown no indicat ions of f r e e z i n g , t h e dumps d u r i n g t h i sf l i g h t may have c o i n c i d e d w i t h a co lde r nozz le cond i t ion than on any pre -v i o u s f l i g h t . A l s o , t h e p urg e- an d- dr y p r o c ed u r e u s e d d u r i n g t h i s m i s s i o nw a s d i f f e r e n t f rom t h a t u s ed i n pr ev io u s m is s io n s i n t h a t t h e u r i n e re -c e i v e r w a s r i n s e d w i t h water a f t e r e a ch u s e a nd t h e s y s te m w a s purgedwi t h oxygen f o r longer times than i n pa s t miss io ns . These changes mayh av e c o n t r ib u t e d t o t h e f r e e z in g . A t e s t i s p l an n ed t o d e te r mi n e t h ec o n t r i b u t i o n o f t h e p ro c ed u re s t o t h e f r e e z i n g .

I f f r e e z i n g o c cu r s i n t h e f u t u r e , t ha wi ng c an be accomplished veryq u i c k l y by o r i e n t i n g t h e s p a c e c r a f t ' s o t h a t t h e n o zz le i s i n s u n li g ht .Th is w a s demons t ra ted severa l times d ur in g t h i s f l i g h t . The a u x i l i a r y

hat ch nozz le and t h e wat er overboard dump nozzle pro vide backup cap abi l -i t i e s . No hardware change i s i n o r d e r, b u t p r o c e d u r a l c h a n g e s m a y b en e c e s s a r y t h a t w o u l d e i t h e r r e s t r i c t t h e t imes when ur in e m a y be dumpedo r m od if y t h e p u rg i n g t e c h n i q u e s .

This anomaly i s c l o s e d .

14 .1 . 4 Degraded VHF Connnunications

The VHF l i n k between t h e comnand and se rv ic e module and lu n ar mod-u l e w a s degraded from p r i o r t o lunar l i f t - o f f t hr o ug h t e r m i n a l p ha sei n i t i a t i o n . The r e c ei v e d s i g n a l s t r e n g t h m ea su red i n t h e l u n a r modulew a s l o we r t h a n p r e d i c t e d d u r i n g t h e p e r i o d s when VHF performance w a s de-graded . VHF v o i c e w a s poor and, ll m in utes p r i o r t o l u n ar l i f t - o f f , n o i s ew a s r e c e i v e d i n t h e l u n a r module t hr o ug h t h e VHF s y st em . T h e r e f o r e , t h esystem w a s di sa bl ed . When t h e system w a s ag ain ena ble d about 4-1/2 min-u t e s b e f o r e l u n a r l i f t - o f f , t h e n o i s e h ad d is ap p ea re d .

P r i o r t o l u n a r d es ce n t, t h e VHF ranging and rendezvous radar rangemeasurements co r r e l a t ed c lose l y. However, dur ing th e t i m e p e r i o d p r e -c ed in g t e r m in a l ph as e i n i t i a t i o n , t h e VHF r a n g i n g s y s t e m i n d i c a t e d e r r o n -eous measurements. During t h i s same t i m e per iod , numerous range t r ac k i ngd r o p o u t s also occu rred . The range measurements were i n e r r o r by 5 t o15 mil es when compared wi th t h e rendezvous r ad ar rang e measurements

( f i g . 14-7) .a n u m b e r o f d i f f e r e n t a c q u i s i t i o n s . After t e rm i n al p ha se i n i t i a t i o n , t h eThe VHF r an g in g d at a p r e s e n te d i n t h e f i g u r e r e s u l t s from



14-12



14-13

s i g n a l s t r e n g t h , as i n d i c a t e d by t h e lur,ar module rece iver au tomat ic ga inco nt ro l vol ta ge measurement , was adequate and VHF ran gin g op er at i on w a snormal.

These problems would be expected i f t h e s i g n al s t r e n g t h were low.T h e s i g n a l s t r e n g t h w a s determined by measuring t h e a utomatic gai n con-t r o l v o l t a g e i n t h e l u n a r m odule VHF r e c e i v e r .w a s -97.5 t o -32 a m . Figure 14-8 shows t h e p r e d i c t e d s i g n a l s t r e n g t h sand th os e measured dur ing t h e mission a t t h e l u n a r m odule r e c e i v e r.

The measurement range

The m a x i m u mp r e d i c t e d v a l u e s assume t h a t d i r e c t a n d m u l t i p a t h s i g -n a l s a dd . F o r t h e m i n i m u mp r e d i c t e d , t h e m u l t ip a t h s i g n a l i s assumed t os u b t r a c t f ro m t h e d i r e c t s i g n a l . The a n t e n na p a t t e r n m odel u s e d c o n s i s t e dof g a in va lues i n 2-degree increments and d id no t inc l ude a l l the peakst h a t a re known t o occur bec aus e o f a n te n na p o l a r i z a t i o n d i f f e r e n c e s be -tween t h e l u n a r module and command and se r v ic e module. L ine-of- s igh t t ot h e command module pa ss in g throug h one of th es e peaks would ex p la in thep u l s e s shown i n f i g u r e 14-8(a).

Figure 14-8(b) shows t h a t t h e s i g n a l s t r e n g t h s h o u l d h av e be e n ons c a l e s u b se qu e nt t o a bo u t 1 0 minutes a f t e r i n s e r t i o n . F i gu r e 1 4 - 8 ( c)shows that t h e me as ur ed s i g n a l s t r e n g t h w a s below that e xp ec te d f o r t h er i g h t - f o r w a r d a n t e n na , t h e on e which t h e c h e c k l i s t c a l l e d o u t t o be u s e d ,from i n s e r t i o n t o d oc ki ng and above t h a t p r e d i c t e d f o r t h e r i g h t - a f ta n t e n n a f o r t h i s same t i m e p e ri o d. T h is i n d i c a t e s t h a t t h e p r o p e r an-t e n n a w a s s e l e c t e d , b u t some c o n d i ti o n e x i s t e d w hich d e c r e a s e d t h e s i g n a ls t r e n g t h t o t h e l u n a r module receiver.

The lower-than-normal RF l ink performance w a s a two-way problem( v o i c e w a s p o or i n b o t h d i r e c t i o n s ) ; t h e r e f o r e , c e r t a i n p a r t s o f t h e VHFsystem a re p rim e c a n d i d a t e s f o r t h e c a u s e o f th e problem.i s a block d iagram of t h e VHF communications system as conf igured dur ing

t h e rendezvous phase o f t h e miss ion . Also shown a re t h o s e areas i n whicha malf ’unction cou ld have a ff ec te d t h e two-way RF li n k performance. As i n g l e m a l fu n c ti o n i n any o t h e r area would have af f e c te d one-way perform-ance on ly.

F igure 14-9

The VHF ran gin g problems res u lt ed from lower-than-normal s i g n a ls t r e n g t h t o g e t h e r w it h t h e e x i s t i n g r a ng e r a t e . The ranging equipmenti s d e si gn ed t o o p e r a t e w i t h s i g n a l s t r e n g t h s g r e a t e r t h a n -105 dBm.The lu na r module r ece ive d s ignal s t r e n g t h d a t a are e s s e n t i a l l y q u a l i t a -t i v e , s i n c e most o f t h e i n f l i g h t d a t a dur ing t h e p rob lem pe r io d wereo f f - s c a l e l ow. U n f o r t u n a t e l y, t h e s c a l e s e l e c t i o n w a s not chosen fo rf a i l u r e analys is . A s p o t c heck o f r e l a t i v e v e h i c l e a t t i t u d e s , as ev i -denced by normal performance of t h e rendezvous r ada r and by s ex ta n ts i g h t i n g s , i n d ic a te s t h a t t h e a t t i tu d e s were pro per . The crew a l s oi n d i c a t e d t h a t t h e y f o l lo w ed t h e c h e c k l i s t f o r VHF a n te n n a s e l e c t i o n .



14-14NASA-S-7 1- 1676

-6 0

dU - -805cncl

5; 100

. -120

E

In

U l

m.-

0 l

a

-1400 1 2 3 4 5 6 7 8

-

-6 0

-804.B

s; 100c nIn.-U

.f -1200 l

a

-140

sU

5 nEl

3-m

Incn.-

U l

al

alE

.-

Figure

-60

-80

-100

-120

-140. -4 5 6 7 8 9 lo 111 2 3

Time from acquisition of signal, min

(c ) Right forward and aft antennas from acquisition of signal to near docking time.

14-8.- Received signal s t r e n g t h from omnid i rec t iona l an tennas .

- .tl K . L . L

. -L.



14-15

mSSal3 s

z m0.-5 %> >

al

-00

USm

-a

E

EEu

Y0--n

aBI

aJ-I

r l 0E

m

Cm

LLI> EET7

a

ss

v)

U

aJ

U0-aE



14-16

A f l i g h t t e s t w a s p erfo rm ed t o v e r i f y t h a t t h e VHF ranging problemw a s a s s o c i a t e d w it h t h e l ow VHF s i g n a l s t r e n g t h and w a s n ot r e l a t e d t ot h e VHF r a n g i n g elements.c a t e d a nd t h e r e s u l t s showed t h a t , f o r s i g n a l s t r e n g t h s below a b ou t-105 dBm, e r r o r s i n i n d i c a t e d range s imi l a r t o t h o s e e x p er i en c e d onApollo 1 4 w i l l be genera ted .

The Apollo 1 4 range and range r a t e were d u p l i -

The procedures f o r t e s t and checkout of t h e l un ar module and com-mand module elements o f t h e VHF sys tem have been reas ses sed an d foundt o be s u f f i c i e n t , a nd ad d i ti o n a l i ns p ec t io n o r t e s t i n g i s n o t p r a c t i c a lo r n e c e s s a r y. The o n ly a c t i o n t h a t w i l l be t a k e n i s t o add ins t rumen-t a t i o n on b o t h t h e l u n a r m odule an d t h e command and s er vi ce module t op r o v i d e more i n s i g h t i n t o t h e n a tu r e of t h e p roblem i f i t occurs on sub-s e q ue n t f l i g h t s . T h er ef or e , o r s u bs e qu en t v e h i c l e s , r e c e i v e r a u to m a ti cgain control measurements w i l l be added t o bo th t h e lu nar module andt h e command and se rv ic e module. Measurement s c a l e fa c to rs w i l l be se -l e c t e d t o g i v e o n- sc al e data a t t h e low s i g n a l s t r e n g t h r an g e . The l u n a rmodule ' da ta s to rag e and e l ec t r on ic s assembly ( t a pe recor der ) w as r e t a i n e df o r s ub s eq ue n t p o s t f l i g h t e v a l u a t i o n o f vo i c e q u a l i t y a s s o c i a t e d w i t ht h e au tomat ic ga i n co n t ro l measurements .

C r e w t r a i n i n g w i l l be expanded t o i n cl u de r e a l i s t i c s i m ul a ti o ns o fweak s i g n a l s t r e n g t h s a nd t h e e f f e c t s of r a n g i n g on v o i c e q u a l i t y . Thee f f e c t s of t h e modes se le c t ed and o p e r a t i o n a l t e c h n i q u e s s u c h as v o i c eleve l and mic rophone pos i t ion become impor tan t nea r the range l i m i t s oft h e s y s te m .

This anomaly i s c losed .

1 4 . 1 . 5 Entry Monitor System 0.05g Light

The e n t r y m on it or s y s t em 0 .0 5g l i g h t d i d n o t i l l u m i n a t e w i t h i n3 seconds a f t e r an O.O5g condition w a s sensed by t h e p rimary gu idancesys tem. The crew then manua lly swi tch ed t o th e backup pos i t i on .

The e n t r y moni to r sys tem i s d e s ig n e d t o s t a r t automatical ly whenO.O5g i s sens ed by t h e sys tem acce le romete r. When t h i s sen s in g occur s ,t h e 0 .0 5g l i g h t s h ou l d come o n , t h e s c r o l l s h o u l d b e g i n t o d r i v e ( a l -though barely p e r c e p t i b l e ) and t h e range-to-go coun te r shou ld beg in t oc o u nt down. The crew r e p o r t e d t h e l i g h t f a i l u r e b u t w a s u na bl e t o v e r i -f y w h et h er t h e s c r o l l o r c o u n t er re sp on de d b e f o r e t h e s w i tc h w a s manuallychanged t o t h e backup mode. The crew a l s o r e po r te d t h a t t h e n e u t r a ld e n s i t y f i l t e r w a s cover ing t h e 0 .0 5g l i g h t and t h a t t h e r e were s u n l i g h tr e f l e c t i o n s i n t h e c a bi n.



14-17

Analysis o f t h e r a ng e c o u n t er d a t a r e p o r t e d b y t h e crew i n d i c a t e sa l and ing po in t about 5 n a u t i c a l miles s h o r t ; w h e re a s, i f t h e e n t r y mon-i t o r s y s te m h ad n o t s t a r t e d when O.O5g w a s s e n s e d a n d h a d s t a r t e d 3 s e c -onds l a t e r , th e i nd ica ted l and ing po in t would have been on the o rd er o f2 0 n a u t i c a l miles long .

P o s t f l i g h t t e s t s conducted on the system show that the lamp driverc i rcu i t and the redundant l amp f i l aments w e r e oper a t ing p roper ly. Ana ly-s i s o f t h e r an g e c o u n t er d a t a and p o s t f l i g h t t e s t s i n d i c a te t h a t t h ef a i l u r e o f t h e crew t o see t h e l i g h t w a s c au s ed by h av in g t h e f i l t e rp o s i t i o n e d i n f r o n t of t h e l i g h t . R e f l ec t e d l i g h t from t h e s u n and thei o n i z a t i o n l a y e r would make i t very d i f f i c u l t t o see t h e l i g h t . F u r t he r ,a c l ea r gl as s f i l t e r i s used i n t h e s i m u l a to r ; w h e re as , t h e s p a c e c r a f tf i l t e r i s s i l v e r e d .

T h e c o r r e c t i v e a c t i o n i s t o r e pl ac e t h e f i l t e r i n t h e s i mu la to rwi th a f l i g h t u n i t . A ls o, a f l i g h t p r o c e d u r a l c h a n g e w i l l be made t op o s i t i o n t h e f i l t e r s o t h a t it w i l l n o t o b s c u r e t h e l i g h t .

Thisanomaly

i sc losed .

14.1.6 I n a b i l i t y t o D i s co n ne ct Main B u s A

During entry, when the main bus t i e swi tches (motor-dr iven swi tches )were p l ac e d i n t h e o f f p o s i ti o n a t 800 f e e t , main bus A should have de-ener gize d; however, t h e bus remained on u n t i l a f t e r l a n d i n g when t h eb a t t e r y b u s - ti e c i r c u i t b re ak er s were o pen ed . P o s t f l i g h t t e s t i n g s h a r e dt h a t th e main motor switch contact s were c l o s e d ( f i g . 14-10) . Also, t h e

M o r winding open

fI switch

Battery Win bus ti e I

bus A battery AI C

intermittently open

Mtery C

Figure 14-10.- B u s - t i e c i r c u i t r y.



14-18

i n t e r n a l s w i t c h e s which c o n t r o l t h e d r i v e motor were s h o r t e d t o g e t h e r andt h e m o to r w in d in g s w er e op en . T he se c o n d i t i o n s i n d i c a t e t h a t t h e m o to rs w i t c h s t a l l e d .

Main bus B s h o u l d h av e be en p ow er ed b e c au s e o f t h i s f a i l u r e , b u tw a s n o t . P o s t f l i g h t t e s t i n g showed t h a t t h i s o c c ur r ed b e ca u se t h e mainbus B c i r c u i t b r ea k er f o r b a t t e r y C w a s i n t e r m i t t e n t . T h i s p ro bl em i s

d i s c u s se d i n s e c t i o n 1 4 . 1 . 7 .

A s imi la r m o t o r s w i t c h f a i l u r e w a s e x p e r i e n ce d d u r i n g t e s t s o f t h eApollo 1 5 command and service module a t t h e l a u n c h s i t e . A l s o , a seconds i m i l a r motor switch on the Apollo 15 v e h i c l e r e q u i r e d 1 0 0 m i l l i s e c o n d st o t r a n s f e r ; whereas, normal t r a n s f e r t i m e i s 50 m i l l i s e c o n d s . A motorc u r r e n t s i g n a t u r e w a s t a k e n f o r o ne s w i t c h c y c l e o f t h e s l ow - o pe ra ti n gswi tch a n d compared t o a s i m i l a r s i g n a tu r e t ak en p r i o r t o d e l iv e r y . I tshowed t h a t c on tact r es is ta n ce between t h e brus hes and commutator haddegraded and become extre mely e r r a t i c . Torque measurements of t h e f a i l e dmotor swi tch wi thou t the motors were n o rm al . T h i s i s o l a t e s t h e problemt o t h e mo to rs o f t h e s w i t c h a ss e mb l y.

A b l a c k t r a c k o f d e p o s i t s f rom t h e b r u s h e s w a s found on t h e Apollo1 4 commutator, as w e l l as on both of t h e commutators f rom t h e Apollo 1 5mo tor s. One motor had f a i l e d , an d t h e o t h er was runn ing s low. Normally,a commutator should show some d i s c o l o r a t i o n a l o ng t h e br us h t r a c k , b u ta b u i l d u p o f b r u sh m a t e r i a l a lo n g t h e t r a c k i s abnormal. As a r e s u l to f t h e t r a c k b u i l d u p , t h e r e s i s t a n c e betw een t h e brushes and commutatorbecame h i g h e r . The h i g h e r r e s i s t a n c e d ro p s t h e v o l t a g e i n t o t h e a r ma t u rec a u s i n g t h e mo to r t o r un s l o we r. ( Sw it ch t r a n s f e r , o pen t o c l o s e d , o rv i c e v e r s a , r e q u i r es 11 r e v o l u t i o n s o f t h e m o t o r. ) The i n c r e a s e d re -s i s t a n c e a t t h e b rushes g ene ra t es more hea t th an normal. A v i s u a l i n -s p e c t i o n o f t h e Ap o ll o 1 4 motor brush assembly showed high heat ing oft h e b r u s h e s ha d o c cu r r e d , an d t h i s w a s c o n c e n t r a t e d a t t h e b r u s h -

commutator in te r f ac e . The cond i t ion w a s e v i d e n t by t h e m e l t i n g p a t t e r nof a t h i n n y l on d i s h which r e t a i n s t h e b r u sh i n t h e b r u s h h o l d e r.

An a n a l y s i s i s b e i n g made t o d e t er m i n e t h e d e p o s i t b u i l d u p o n t h ec o m u t a t o r. E i t h e r t h e b r u s h c om po si ti on i s i n e r r o r , o r a contaminat ione x i s t s i n t h e b r u s h c o m p o si t io n . X-ray r e f r a c t i o n a n a l y s i s shows t h esame e lements th roughout t h e b rus h . The percen tage o f each o f th e sub-s t a n c e s w i l l be determined an d compared t o t h e s p e c i f i c a t i o n a n a l y s i so f t h e b r us h .

I n s p e c t i o n o f t h e co mm utato r o u t s i d e o f t h e t r a c k shows a c l e a nc o p p er s u r f a c e c om pa rab le t o o t h e r m ach in ed s u r f a c e s w i t h i n t h e m o to r.I t can be i n f e r r e d from t h i s t h a t t h e r e a re no problems as so ci at ed w i t h



14-19

t h g e / l i f e o f t h e l u b r i c a n t s from t h e b e a r in g s o r w i t h o u t g a ss i n g fromo rg a n i c materials which might dep osi t on t h e commutators. The swi tchassemblies are hermet ic a l ly sea led and under a 1 5 - p s i p r e s s u r e o f n i t r o -gen and helium gas.

Each motor i s o p e r a t e d c o n t i n u o u s l y f o r 4 t o 8 h o ur s t o sea t t h e

bru she s. The motors a re the n d i sassembled , inspec ted , and c leaned .Procedures f o r c l ean ing th e motor assembly are n o t e x p l i c i t as t o m ate-r i a l s o r t e ch n iq u e s t o b e u se d. T h i s c o u ld b e t h e c a us e o f t h e p ro ble m.A f u r t h e r s t u dy of t h i s a s p e c t i s being made. An anomaly report w i l l beissued upon completion of t h e i n v e st i g at i o n .

There are 36 motor-dr iven swi tch assemblies i n t h e sp ace cra f t . Someof t h e s w i t c h e s are normal ly no t used i n f l i g h t . Some are used once or,a t most, s e v e r a l t i m e s . T h e i n c r e a s e d r e s i s t a n c e o f bru sh t o t h e commu-t a t o r as a resul t o f d e p o s i t s i s gradual from a l l i n d i c a t i o n s . A checko f t h e s w i t ch o p e r a t i o n t i m e can be r e l a t e d t o t h e d e p o s i t b ui ld u p on t h ecommutator. Consequently, a check of t h e s w i t c h r e sp o n se t i m e can indi-c a t e t h e d e p e n d a b il i ty o f t h e s wi tc h t o p e rf or m on e o r s e v e r a l a d d i t i o n a l

s w i t c h t r a n s f e r s i n f l i g h t . T h i s w i l l be done f o r Apollo 15 on each oft h e s w i t c h e s . Work-around proc edur es have been develop ed i f any o f t h emotor switches are q u e s t i o n a b l e as a r e s u l t o f t h e t i mi n g t e s t .


14 .1 . 7 I n t e r m i t t e n t C i r c u i t B r ea ke r

The m o to r s w i tc h f a i l u r e d i s c u ss e d i n s e c t i o n 14.1 .6 should haver e s u l t e d i n main buses A and B b e in g e n e rg iz e d a f t e r t h e m ot or s w i tc hw a s commanded open ( f i g . 14-10) . Po st f l ig ht co nt i nu i ty checks, however,showed tha t the re w a s an open c i r cu i t be tween ba t t e ry C and main bus Band tha t the main bus B c i r c u i t br ea ke r f o r b a t t e r y C w a s i n t e r m i t t e n t .

Disassembly and inspect ion of t h e c i r c u i t b r e ak e r showed t h a t t h ec o n t a c t s are c r a t e r e d ( f i g . 14-11) .s t a n c e w hich h e l d t h e c o n t a c t s a p a r t when t h e c i r c u i t b r e a k e r w a s actu-a t e d .

The c r a t e r c o n t a i n s a white sub-

The whi te subs tance w i l l be ana lyzed t o de te rmine i t s compositionCi rc ui t break ers which have been used i n s i m i l a r appl ica -nd source .

t i o n s i n A p ol lo 1 4 w i l l a l s o be examined.i s sued under separa te cover when t h e analysis has been completed.

An anomaly report w i l l be




14-20

NASA-S-71-1679

c

F i g u r e 14-11.- C i r c u i t b r e a k e r c o n t a c t .

t ' I

LTL-



14-22

NASA-S-71-1680

Repressur ita tion bottles

Re efva 1ve

urization valve

II

i r

Recharge pva Ive

Fac e masks

4 - r ' 9 0 0 p s i aTo mainw u ators

Figure 14-12.- Rapid repressurization system.

. -L

B nutconnector



14-23

I! rVa lve closed /Repressurization;

-I L(

II

NASA-S-71-1681

Surge tank pressure

.-Inn-E

h

3Inu)aJ

9

Oxygen flow rate

4-

i1

caJu9

' X0

.aJ

Y

h

5 '

-fIn

Cabin pressure

~.In

x0

9 0 0

800

700

600

I fi ll valve open ;I 1

I I L,I I

I V 1 lsurge tank only'being refilled

500

1.0

0 . 5

0

Figure 14-13.- Rapid repr es su riz ati on package data.



14-24

Data a re n o t a v a i l a b l e from t h e lunar o r b i t r e p r e s s u r i z a t io n as t h es p a c e c r a f t w a s on t h e b ack s i d e o f t h e moon d u r in g t h e o p e r a t i o n .eve r, t h e g e n e r a l pr o ce d ur e u s e d d u r i n g t h e t r a n s e a r t h c o a s t p h a s e w ou ldo nl y p a r t i a l l y r ec ha rg e t h e s ys te m.

How-

P o s t f l i g h t checks of t h e 900-psi sys tem showed t h a t t h e l eakage r a t ew a s about 40 standard cc/min as co mp ared w i t h t h e p r e f l i g h t v a l u e o f

1 4 s ta nd ard cc/min. This change i n l eakage r a t e i s not considered ab-normal. A leakage r a t e of t h i s magni tude would lower t h e system pre ssu reabout 100 p s i every 3 d a y s. T h e r e fo r e , t h e lunar o r b i t r ec h ar g in g o f t h es y st em p r ob a b ly r e s u l t e d frcxn normal leakage.

Fu ture crews w i l l b e b r i e f e d on t h e r e c h arg i n g t e ch n iq u e s f o r o t h e rt h a n n or mal r ec h arg in g s t o i n s u r e t h a t t h e s y st em i s f u l l y r e c h a rg e d .


1 4 . 2 LUNAR MODULF:

14.2.1 Ascent Bat tery 5 Low Voltage

A t 62 h o u rs , t h e a s ce n t b a t t e r y 5 open- c i rcu i t vo l ta ge had decreasedfrom a l i f t - o f f v al ue o f 37.0 v o l t s t o 36.7 v o l t s in s t ea d o f remain ing a ta c o ns t an t l e v e l ( f i g . 14-14( a ) ) . Figure 14-14(b) shows charac te r i s t i copen-c i rcu i t vo l tages f o r a f u l l y c h a rg e d b a t t e r y ( p er o x id e l e v e l o f allc e l l s ) and a l l c e l l s o p e r a t i n g on t h e monoxide l e v e l o f t h e s i l v e r p l a t e .Note tha t one ce l l at t h e monoxide le v e l and t h e remaining 19 a t t h e p er -ox ide l ev e l would have caused t h e observed op en-c i rcu i t vo l ta ge o f 36.7v o l t s . Any one of t h e f o ll o w in g c o n d i ti o n s c o u ld h av e c a u se d t h e v o l t -age drop.

a. B a t te r y c e l l s h o r t

b. C e l l s h o rt - to - ca s e t h ro u g h an e l e c t r o l y t e p a t h

c . E x te r n al b a t t e r y l o a d .

A s i n g l e - c e l l s h o r t c o u l d b e c au s ed by i n c l u s i o n o f c o n du c ti v ef o r e i g n mate r i a l i n t h e c e l l - p l a t e pack a t t h e t i m e of manufactu re o re x c e s s i v e b r a z e mater ia l a t t h e b r az e d j o i n t b etw een t h e p l a t e t a b andp l a t e g r i d , e i t h e r of which c o ul d p i e r c e t h e c el lo p ha n e p l a t e s e p a r a t o rdur ing th e launch powered- fl igh t phase , p rov id ing a conduct ive path be-t w e e n p o s i t i v e a n d n e g a t i v e p l a t e s ( f i g . 14 -15 ) .



14-25

37.0Y,

0>

4-..-5 36.0

1 L.

0

ti0

3 5 . 0

NASA-S-7 1-1602

attery 5 (flight)

-Battery 5 voltage for aconstant external load

I 1 I 1 1

(a) Open-circuit voltage variation during miss ion.

Al l cells fully charged(peroxide level of thesilver cell plate)

One cell out of the 20 cells at the monoxide level

3 7 O

UI43 36.7 -

31.0

ir {All cells discharged to monoxide levelc).-.-0

K0

O +400 0

Ampere hours

(b) Characteristic open-circuit voltage of a battery,

Figure 14-14.- Ascent b a t t e r y v o lt a ge c h a r a c t e r i s t i c s .



14-26

NASA-S-71-1683

(a) 20 -c el l ascent battery.

(b) Pl ate assembly. (c ) Case plugs.

(d) Cross section of plug.

Figure 14-15. Ascent b a t t e r y cell s t r u c t u r e .



14-27

D ur in g b a t t e r y a c t i v a t i o n , one o f t h e d e s ce n t b a t t e r i e s h ad a c e l ls h o r t t o t h e c as e th ro ug h an e l e c t r o l y t e p a t h a ro un d a c e l l plu g j o i n t( f i g . 14-15). The c e l l p l u g w as n o t p r o p e r l y s e a l e d t o t h e b otto m o ft h e p l a s t i c c e l l ca se . I f t h i s c o n di ti o n e x i s t e d i n a s ce n t b a t t e r y 5i n f l i g h t , it c o u ld h av e d e cr e as e d t h e b a t t e r y o p e n - c i r cu i t v o l t a g e .

An e x t e r n a l b a t t e r y l o a d c o u ld ha ve ex i s t ed from l i f t - o f f t o 6 2 h ou rson t h e c i r c u i t shown i n f i g u r e 14-16 i n w hich t y p i c a l t y p e s o f h i g h r e s i s t -a n c e s h o r t s are a l s o shown. For t h i s c o n d i t i o n , t h e c u r r e n t d r a i n w ou ldhave occurred on all c e l l s . F i g u r e 14-14 shows t h e ti m e h i s t o r y of t h e

NASA-S-7 1-1684

Vo 1tage monitorscent

400kohms

PI* Battery 5

On normal switch

POSSIBLE HIGHRESISTANCE GROUNDS

Battery 5On backup switc h

F i g u r e 14-16.- Ascent ba t t e ry 5 c o n fi g u re d f o r o p en - c i r cu i t l o a d s .



14-28

o p e n- c ir c ui t b us v o l t ag e f o r b a t t e r y 5 .t h e b a t t e ry 5 open-c i rcu i t bus vol tage would have been lower th an t h ef l i g h t d a t a a t 141 hours .t o change with time.

Fo r a c o n st a nt e x t e r n a l l o a d ,

T h e r e fo r e , t h e e x t e r n a l l o a d wou ld h a ve h a d

To r ed u ce t h e p o s s i b i l i t y o f r e c u r r e n ce , c o r r e c t i v e a c t i o n ha s be enS t r i c t e r i n s p e c t i o n a nd imp rov eda k e n f o r e ac h o f t h e p o s s i b l e c au s es .

p r o ce d u re s h av e b een i n c o r p o r a t e d f o r i n s t a l l a t i o n of t h e plugs. P a r t l c -c u l a r a t t e n t i o n w i l l b e g i v e n t o t h e a ss em bl y of t h e c e l l p l a t e s on f u t u r eu n i t s .l u n ar module p a r a s i t i c l oa ds p r i o r t o b a t t e r y i n s t a l l a t i o n t o i n s u r e t h a tno abnormal loads are p r e s e n t .

I n a d d i t i o n , a t e s t has been added a t t h e l au nc h s i t e t o m easure


14.2.2 Abort Signal S e t In Computer

P r i o r t o descen t , t h e p r imary gu idance computer rece iv ed an abortcommand four d i f f e r e n t t imes . The computer would have reacted i f t h edescen t p rogram had been in i t i a ted . T h e f a i l u r e w a s i s o l a t e d t o one

NASA-S-71-1685Abart switch

Lunar+28

4 1T I

ground bus !

ILunar ModulePilol's + P iground bus Clelemetry)

bikve l discrete

o scent engine

Commander's F

Engine arm switch

DescentDescent y [ ontrolngine logic I, A

engine

Commander's+28 V dc bus

enginecontrol

n

Did nota c u r

ar/l Telemetry)Abort bilevelA i c r r a h

. __... __ .wnlink)ogram I Start abort program

!Problem isohtedto these contacts

I

guidance computer

Did ac ur

&(Computer downlink)Start abort program

Figure 14-17.- Abor t swi tch log ic .



14-30

NASA-S-7 1-1686

Most likely sourceof sliver

7

Me ta l contamination up to 0.0 30 -i nc h long slivers found in several switches

(a) Simplified sketch of internal switch parts.

(b) X-rays of switch showing metallic contamination.

Figure 14-18.- Abort switch contamination.

1 -

L-

1Y - - L L

, -LA i



14-31

c . The p lus-X t ra ns la t i on swi tch w a s rewi red so t h a t two se r i e sc o n t a c t c l o s u r e s are r e q u i re d t o f i r e t h e plus-X r e a c t i o n c o n t r o l sys-t e m t h r u s t e r s . This removed t h e f o u r - t h r u s t e r t r a n s l a t i o n c a p a b i l i t y,l e a v i n g o n l y a t w o -t h r us t er t r a n s l a t i o n c a p a b i l i t y.

d. The e n g i n e - s t a r t s w i tc h a nd c i r c u i t r y were not changed becauseo f t h i s p r ob le m s i n c e i n a d v e r t e n t c l o s u r e wou ld o n l y g i v e t h e ma nu al s t a r tcommand, and t h e e ng in e a r m comnand i s a l s o r e q u i r e d t o f i r e t h e e n gi ne .However, because of a s w i t c h f a i l u r e i n a n o t h e r s p a c e c r a f t d u r i n g gr ou ndt e s t s , t h e s w i t c h w a s rewi red so t h a t a s e r i e s - p a r a l l e l c om bi na ti on o ff o u r s w i t c h c o n t a c t s are u s ed f o r t h e f u n c t i o n . T ha t f a i l u r e w a s causedby nonmeta l l i c con tamina t ion ( ru s t ) p r e v e n t i n g s w it c h c o n t a c t c l o s u r e .This con tamina t ion i s unde tec tab le by x - rays .

e . The two m a s t e r a l a r m switches were n o t rewired s i n c e i n a d v e r t -e n t c o n t a c t c l o s u r e w ou ld o n l y rese t t h e m a s t e r alarm, and t h i s wouldn o t a f f e c t t h e m is si o n or c r e w s a f e t y.

f . The abor t and abor t stage s w it ch c i r c u i t r y t o the compute r w a s

n o t m o d i fi e d . I n s t e a d , t h e primary guidance computer sof tware w a s modi-f i e d t o a l lo w t h e crew t o l o c k o u t t h e c om pu te r ab o r t and a b o r t s t a g eprogram. I f t h e crew e x e r c i s e s t h i s o p t i o n , any r e q u i r e d a b o r t w ou ldhave t o be per fo rmed us ing t h e abort guidance system.


1 4 . 2 . 3 I n t e r m i t t e n t S t e e r a b l e A nt en na O p e r at i on

P r i o r t o t h e d e s ce n t ph ase o f t h e mi s si o n , t h e S-band s t e e r a b l ea n t e n n a o p e r a t i o n w a s i n t e r m i t t e n t . T h er e w e r e - n i n e i n s t a n c e s o f un-s c h e d u l e d i n t e r r u p t i o n o f a n te n na t r a c k i n g . T h re e of t h e s e have beenexplained. One w a s caused by th e c rew sw i tch in g t o an omn id i rec t iona la n t e n n a b e c au s e o f an e rr o ne o us r e a d i n g o f t h e p i t c h p o s i t i o n i n d i c a t o ra t f u l l sc a l e o f 255 degrees when t h e an tenna w a s a c t u a l l y a t 122 degrees.Another o ccur r ed because t h e antenna w a s i n t h e manual s l e w mode andn o t i n a u to m a ti c -t r ac k . After u n d oc k in g , t h e l u n a r m od ule a t t i t u d e w a schanged and, as a r e su l t , t h e a n t e n n a w a s p o i n t e d away f r o m t h e e a r t hr e s u l t i n g i n a l o s s o f s i g n a l . The t h i r d i n t e r r u p t i o n w hich h a s b e e ne x p l a i n e d w a s caused by a f a i lu re i n t h e g ro un d s t a t i o n pow er a m p l i f i e rr e s u l t i n g i n ' a t e m p o r a r y l o s s of u p li nk s i g n a l .

The r e m ai n in g u n ex p la in e d t r a c k i n g i n t e r r u p t i o n s ( f i g . 14-19) haves i m i l a r c h a r a c t e r i s t i c s . F iv e t r a c k i n g i n t e r r u p t i o n s o c cu r re d d u r in gGoldstone coverage and f i g ur e 14-20 i s a p l o t

ofground-s ta t ion- rece ived

s i g n a l s t r e n g th s a t t h e s e t i m e s . D u ri ng t h e Ma dr id g ro u nd s t a t i o n c o v er-age o f r e v o l u t i o n 3 2 , a n o t h e r i n c i d e n t w a s n o t ed w i t h t h e same t y p e of



14-32

NASA-S-71-1687

Revolution 11 Revolution 12 Revolution 13 Revolution 14

(Froill side only) (Front side only) (Front sidc oiily)

Steerable anleiiiia selected

. rl miiidirectional aiiteiiiia selcckd

Unscheduled losses of lock, h:min

a - 101:55

b - 103:42

d - 104:36

e - 107:31

c - 104i26 f - 144:ll

I Revolution 31 I Revolution 32 I(Front side only) (Front si& only)

F i g u r e 14-19 .- S-band s t ee ra b l e an tenna ope ra t i on .

an tenna response . I t i n d i c a t e s t h a t t h e a n t e n n a b eg an t o e x p er i en c e amechanica l osc i l l a t ion o f approx imate ly 2 t o 3 hertz, which became in-c r e a s i n g l y l a rg e r i n a m pl it u de u n t i l t h e a n te n n a l o s t l o c k . When an t e nn ao s c i l l a t i o n s e xc ee d p l u s o r minus 5 degr ees , e xcess ive motor d r ive cur-r e n t c a u s e s t h e 28 -v oi t d c c i r c u i t b r e a k e r t o o pen and t h e a n t e n n a c e a s e st o t r a c k . The crew r e s e t t h i s c i r c u i t b r e a k e r s e v e r a l t i m es . The an-t e n n a w a s a l s o r e p or t ed t o be n o i s y, i n d i c a t i n g t h e c o n t i n u a l d r i v i n gt h a t would h av e oc cu r re d d u r in g t h e o s c i l l a t i o n s . The o s c i l l a t i o n s o c-curred randomly at o t h e r t i m e s durin g th e problem pe rio d, bu t damped outand d i d n ot c au s e t r a c k i n g i n t e r r u p t i o n s .

The two mos t p robab le causes o f these osc i l l a t ions a re an unwantedv a r i a t i o n i n t h e u p li nk s i g n a l o r a c o nd it io n of i n s t a b i l i t y i n t h eantenna/S-band t ra ns ce i ve r t r a ck in g loop sys tem. The cond i t ions whichcan c a us e t h e f i r s t i t e m a r e v e h i c l e b lo c ka g e, r e f l e c t i o n s from t h es p a c e c r a f t s t r u c t u r e , m u l t i p at h s i g n a l r e f l e c t i o n s from t h e l u n a r s u r -f a c e , n o i s e t r a n s i e n t s i n du c ed on t h e u p l in k s i g n a l , o r i n c i d e n t a l am-pl i tude modula t ion on t h e c a r r i e r a t t h e c r i t i c a l a n te nn a l o b in g f re-quency ( 50 t o 10 0 her tz o r odd harmonics ) .

L oo k- an gle d a t a i n d i c a t e t h a t t h e a n t en n a w a s n o t p o i n t e d a t orn ea r t h e v e h i c l e s t r u c t u r e d u r i ng t h e t i m e per iod s when an tenn a loc kw a s l o s t .



14-33

-120

NASA-S-71-1688

--

-100

-120

-140

-

-100

-120

(a) 10155 .

----I

- -1005

5 -120s3 -140

m

L

01v).- (c) 104:26.

-100

-120

-140(d) 104:36.

0 2 4 6 8 10

Relat ive time, se c

(e) 107:31.

Figure 14-20 .- Signa l s t r eng th osc i l l a t ions a s soc ia t edwith five unexplained losses of lock.



14-34

Mult i path normally accur s when t h e spa ce cra f t i s n e ar t h e l u n a rhor izo n. However, antenna loss-of- lock di d no t occur a t t h e s e t i m e s .

N ois e t r a n s i e n t s on t h e u p l in k a r e h e l d t o a minimum be ca us e t h eg ro un d s t a t i o n power a m p l i f i e r o p e r a t e s i n s a t u r a t i o n . Also , t h e v e r i -f i c a t i o n r e c e i v e r w hich m o n it or s t h e u p l i n k s i g n a l a t t h e g rou nd s t a t i o nd i s p l a y e d no rm al o u t pu t d u r i n g t h e p r o b l e a t i m e p e r i o d s . A lt ho ug h t h e

incidental ampli tude modulst ion has not been recent ly measured a t Gold-s to ne and Madr id , p roduc t ion sub -car r i e r os c i l l a t o r s have been checked.These t e s t s s h o v e d t h a t t h e i n c i d e n t a l a m p l i t u d e m o d u l a t i o n a t t h e c r i t i -c a l f r e q u e n c i e s w a s n o t d e t e c t a b l e ( l e s s t h an 0.1 p e r c e n t ) . A t e s t w a sa l s o p e rf or me d which showed t h a t t h e s t e e r a b l e a n t e n n a r es p o n s e t o i n -cidental amplitude modulation became worse with t h e a d d i t i o n o f v o i c eon t h e s u b - c a r r i e r an d t h e p r e s e n c e of p u l s e r e p e t i t i m r a n g i n g . How-e v e r , t h e r e i s no c o r r e l a t i o n b etw ee n e i t h e r o f t h e s e a nd l o s s e s o f an-t e n n a l o c k . The most p r o b a b l e c au s es f o r t r a c k i n g lo o p i n s t a b i l i t y areh i g h l o o p g a i n , low g im b al f r i c t i o n , a nd low r e c e i v e d s i g n a l s t r e n g t hr e s u l t i n g i n low si gn a l- to - no is e r a t i o i n t h e t r a c k i n g l o o p .l i n k and downlink s i g n a l s t r e n g t h s i n d i c a t e d t h a t t h e RF l e v e l s werenominal and were w i th i n t h e a n te nn a 's c a p a b i l i t y t o t r a c k .

Both up-

The l oop g a i n as measured du r ing t h e accep tance t e s t o f t h eApollo 1 4 equipment indicated a lower-than-nominal v alu e in di ca t i ngt h a t th e s t a b i l i t y s h o u l d have been g re a t e r than nominal .

There are n o l i k e l y f a i l u r e s i n t h e a nt en n a ; ha t w ou ld c a us e a g a i nc h a n g e s u f f i c i e n t t o p ro du ce i n s t a b i l i t y w it h o u t c o mp le te loss o f t h ean tenna . There a re many component f a i lu re s i n t h e t r an sc e i ve r whichmight p roduce th e r ig h t amount o f ga in change f o r os c i l l a t io ns .t h e s e f a i l u r e s would a l s o a f f e c t t h e r e c e i v e r a u to m at ic g a i n c o n t r o lrea din g which appeared normal througho ut t h e problem t i m e .

However,

The g imbal f r i c t i o n on th e Apol lo 1 4 an tenna w a s measured duringground t e s t s and found t o be h igh er than nominal . Th is would inc re as et h e an t en n a s t a b i l i t y . For gim bal f r i c t i o n t o c au s e t h e p ro bl em , av a r i a t i o n i n f r i c t i o n which c h a r a c t e r i s t i c a l l y chang ed from n orm al t olow, o r no f r i c t i o n , a t s h o r t i n t e r v a l s a n d a t random t i m e s c o n s i s t e n tw i t h t h e a n t e n n a o s c i l l a t i o n s w ou ld h av e had t o o c c u r.

There w a s no o bv io us v a r i a t i o n i n u p l i n k s i g n a l a n d n o o bv i ou sch ang e i n t h e a n t e n n a / t r m s c e i v e r t r a c k i n g l o o p wh ich w ould c a u s e t h ean tenna t o o sc i l l a te . There mus t have been some in te rm i t t e n t co ndi t io nt h a t e x i s t e d i n t h e s p a c ec r a f t /g r o u n d s t a t i o n s y s t em , which h a s n o t y e tb ee n i d e n t i f i e d . The i n v e s t i g a t i o n i s c o n t i n u i n g a nd an anomaly reportw i l l be i s s u e d when t h e i n v e s t i g a t i o n is completed.



14-35

!

An addi t iona l p rob lem occur red one t i m e d u r i n g r e v o l u t i o n ll whent h e a nt en n a p i t c h - p o s i t i o n i n d i c a t o r s t u c k a t t h e f u l l - s c a l e r ea d in gof 255 degrees. However, it became ope ra t i ve aga in and con t inued t of u n c t i o n p r o p e r l y. T h i s m a y have been caused,by a f a i l u r e i n t h ep o s i t i o n - s e n s i n g c i r c u i t s i n t h e a nt en na or i n t h e meter i t s e l f . Thismeter hung u p t w i c e d u r i n g a c ce p t an c e t e s t i n g . A malfunc t ion w a s found,

c o r r e c t e d , a n d a r e t e s t w a s s u c c e s s f u l . Th e i n d i c a t o r i s used on ly asa gros s ind ica t io n o f an tenna movement. Consequen tly, no fu r t he r ac t i onw i l l b e t a k e n .

Pulse to switch


14.2 .4 Landing Radar Ac qu isi tio n

Two c o n d i t i o n s o c c u r r e d d ur i n g t h e l a n d i n g r ada r opera t ion whichw e r e no t exp ecte d; however, they were no t abnormal. The f i r s t c o n d i t i o noccurred approximately 6 minutes a f t e r i n i t i a l a c t u a t io n of t h e la n di ngradar. The s y s te m sw i t ch e d t o t h e l ow -rang e s c a l e , f o r c i n g t h e t r a c k e r si n t o th e narrow-band mode o f o p e r a t i o n . T h i s w a s c o r r e c t e d b y r e c y c l i n gt h e m ain pow er c i r c u i t breaker which sw i tched t h e radar t o h ig h s c a l e .Fig ure 14-21 shows t h e radar s c a l e s w i t c h i n g l o g i c .on and "velocity-data-good" and "range-data-good" in di ca ti on s were tr an s-f e r r e d t o t h e computer. The "veloci ty-data-good" s i gn al i s g e n e r a t e dwhen t h e Doppler t r ac ke rs lock on and t h e "range-data-good" s i gn al i sgener a ted when t h e range t ra ck er a l s o locks on .

The radar t h e n l o ck e d

NASA-S-71-1689

Velocity circuit GatingData s t re m

I

T 2 = Doppler tracker 2

TR = Range Gacker

Figure 14-21.- Landing ra da r sc a l e swi tch ing log ic .



14-37

The s c a l e s w i t c h i n g o c c u r r e d at a e l a n t r an ge of 63 000 feet w i t ha beam 4 v e l o c i t y of 3000 f t /sec at an inc idence ang le of 35.4 degrees .O p e r a t in g t h e l a n d i n g r a d a r u nd er t h e s e c o n d i t i o n s e x ce ed s t h e maximumrange measurement design l i m i t ( f i g . 14-23). ,Under th es e cond i t ions ,t h e r e c e i v e r i s sweeping w i t h maximum g a i n a n d t h e system w i l l be sen-s i t i v e t o any r e c e i v e d n o i s e . A t e s t w a s performed with a radar oper-

a t i n g u n d e r t h e A p o l l o 14 condi t ions ( two range -rate beams l ocked upand the range beam unlocked). By i n s e r t i n g l ow -l ev el n o i s e f o r a f r a c -t i o n of a s e co n d i n t o t h e r e c e i v e r, r a ng e s c a l e s w it c h i n g o c cu r r e d .

NASA-S-71-1691

80 )

70

60

5:

i3 50m

Hfs

40

30

200 1 2 3 4 5 x lo3

Ve hi ck velocity component along r a w bcm, f t / e c

Figure 14-23. - Landing radar range measurement design l imita t ionas a f ’unct ion of vehicle veloci ty component a long range beam.



14-38

The h i g h s l a n t r a n g e i n d i c a t e d at lock-cm by t h e landi ng radar w a s

B ased on t h e p r e f l i g h t t e r r a i n p r o f i l e a nd t h e p r e-most l i k e l y c au se d by t h e r a d a r l o c k i n g o n t o en ergy r e t u r n e d i n t o t h ea n te n n a s i d e l o b e .f l i g h t o p e r a t i o n a l t r a j e c t o r y , s i d e l o b e lo ck -o n can b e e x pe c te d .l i s t p ro ce du re s e x i s t t o c o r r e c t a s u s t a i n e d s i d e l o b e l oc k- on . Oncet h e r a d a r i s locked on t h e main lob e , s i d e lo be lock-on cannot occur.

Check-

On fu tu re sp ace cra f t , a w i r i n g m o d i f i c a t i o n w i l l be made t o enab leh o l d i n g t h e s ys te m i n hi gh s c a l e w h i le i n a n t en n a p o s i t i o n 1.w i l l o nl y be e na b le d i n p o s i t i o n 2 . P o s i t i o n 2 o f t h e an tenna i s auto-m a t i c a l l y s e l e c t e d by t h e c o mp ute r at h i g h g a t e (7500 f e e t a l t i t u d e ) .The manua l se l ec t i on o f an tenna po s i t io ns 1 and 2 w i l l a l s o c o n t r o l h ig hs c a l e an d e n a b l e low s c a l e s w i t c h i n g , r e s p e c t i v e l y.

b w s c a l e

This anomaly i s closed.

1 4 . 2 . 5 Loss of t h e 'Abort Guidance System

The abor t gu idance sys tem fa i l e d dur ing t h e brak ing phase o f ren-dezvous.w a s n o i n d i c a t i o n o f an a b o r t g u id a nc e s ys te m w ar ni ng l i g h t o r maste ra l a r m . The crew w a s u n ab le t o a c ce s s t h e d a t a e n t r y a nd d i s p l a y assemblyand depressing any of t h e pushbut tons had no e ffec t . The s t a t u s switchw a s c y c l e d f rom o p e r a t e t o s t a n d b y t o o p e r a t e w i t h n o e f f e c t .t h e 28 -v olt c i r c u i t b r e ak e r s l i k e w i s e h ad n o e f f e c t . The system re-mained inopera t ive fo r t h e r em ai nd er o f t h e m i s s i o n .

Telemetry data were s u d d e n l y l o s t a t 143:58:16; however, t h e r e

Cycl ing

The system w a s de termined t o have been i n t h e s tandby mode af'tert h e fa i lu r e by compar ing expec ted and ac tu a l bus cu r re n t changes t h a twere observed at t h e t i m e o f t h e f a i l u r e and t h e subsequen t c yc l ing o ft h e c i r c u i t b r e a k e r s. F u r t h e r e v id e nc e o f t h e sy st em h a vi n g b ee n i n

s tandby w a s t h e a bs en ce o f t h e w a rn i ng l i g h t a nd m as t er alarm a t t h et ime of t h e f a i l u r e . If s t an d b y power i n t h e e l e c t r o n i c s a ss em bl y werenot main ta ined , c lock pu l ses t o th e abor t senso r assembly would haveb ee n l o s t a nd t h e w a rn i ng l i g h t wou ld ha ve i l l u m i n a t e d and t h e mastera l a r m sounded. A w a r n i n g l i g h t a n d a master alarm would a l s o have oc-c u r r e d i f t h e f a i l u r e h ad b ee n i n t h e a b o r t g u id an ce s t a t u s s w i tc h o rt h e a s s o c i a t ed e x t e r n a l w i ri n g. Th ese co n di ti on s i s o l a t e t h e f a i lu ret o t h e p ower s up ply s e c t i o n o r t h e s eq ue nc er o f t h e a b o r t e l e c t r o n i c sassembly ( f ig . 14-24) .



14- 9

NASA-S-71-1692

28 voltsAbort guidancestatus switch

Control

Ii-?ZI Operate

I 0 tandby

o--c

Power to abortC , lectronics assembly

memory and downlink

I Off - ower to data entryand display assembly

dI

J - tandby power28 volts'ham telemetry I

,

-o telemetry

Figure 14-24 .- P a r t i a l abor t gu idance system fun c t ion a l d iagram.

The f a i lu re has been i so la t ed t o one o f seven modules i n t h e p l us

There a re a t o t a l o f 27 com-b-volt lo g ic power su pp ly, one module i n t h e sequencer, o r one o f27 inter con nect ions between t he modules .ponent par t ty.pes ; t we lv e r e s i s t o r , two c a p a c it o r , f o u r t r a n s i s t o r ,f o u r d i o d e , f o u r t r a n s f o r m e r, a nd o ne s a t u r a b l e r e a c t o r t h a t could havecaused t h e f a i l u r e .

A c o m p l e t e f a i l u r e h i s t o r y review of t h e component p ar t typ es re-vealed no evidence of a generic par t problem.sis an d a the rmal ana lys i s o f m a x i m u mc a se te m p e r at u r e f o r e ac h o f t h esuspect par ts showed adequate design margins.

A power di ss ip at io n analy-

Manufactur ing procedures were r ev ie we d an d fo un d t o b e s a t i s f a c t o r y .F i n a l l y, a review w a s conducted of t h e t e s t i n g t h a t i s performed a t t h ecomponent le v e l , module le v e l , and power supply l ev el . T e s t proceduresw ere f o u n d - t o b e a d e qu a te f o r d e t e c t i o n o f f a i l e d u n i t s a nd n o t s o s e v e r et h a t t h e y w ould e x po se t h e u n i t s t o u n a c ce p ta b le o r h a za rd o us t e s t con-d i t i o n s .

A component o r so lder jo in t f a i l u r e c o u ld ha ve b ee n d ue t o e i t h e r

an abnormal the rmal s t re ss o r a non-gener ic de f ic iency o r qua l i t y de f ec tt h a t w a s unable t o w i ths tand a normal env ironment. A n abnormal thermal



s t r e s s c o u ld h av e b een c au se d by i mp ro pe r i n s t a l l a t i o n o f t h e e q u i p e n to n t h e c o l d r a i l s . I f t h i s o c c u r r e d , t h e f i r s t component which s ho ul df a i l i s in t h e p a r t i c u l a r p ower s u p p ly t o w hich t h e f a i l u r e w a s i s o l a t e d .

I n any e v e n t , t h e meth od s a n d t e c h n i q u e s u s e d t o v e r i f y s y st emperformance show no a p p a r e n t areas which require improvement. F u r t h e rstress a n a l y s i s o f co mpo nents a nd s o l d e r j o i n t s shows t h a t t h e d e s i g n i s

ade qu ate. The methods , e c h ni q u es e nd p r oc e du r es u s e d i n i n s t a l l a t i o nof the equ ipment on t h e c o l d r a i l s are a l s o a d e q u a t e , p r o v i d i n g t h e s eprocedures are fo l lowed . Consequen t ly, no co r r ec t iv e ac t io n i s i n o r de r .


14.2.6 Cracked G l a s s on Data Entry and Display Assembly

The crew reported a c ra ck i n t h e g l a s s a cr o ss t h e a d dr es s r e g i s t e ro f t h e d a t a e n t r y a nd d i s p l a y assembly.e n d t h e l o c a t i o n of t h e c ra c k.t h e g l a s s a n d a s s o c i a t e d e l e c t r o l u m i n e s c e n t s e gm e nt s.

F i g u r e 14-25 s h a r s t h e a s s e m b l yFigure 14-26 i s an enlarged drawing of

NASl 5-71-1693r

Crack 7

.Tapelocations

F i g u r e 14-25.- Loca t ions o f c rack and tape on da taen t ry and d i sp lay assembly.



NASA-S-7 1-1694Room temperaturevu lcanizinq material

K o v a frane

-Commonelectrode

--Glass

Void

Glass

Figure 14-26.- Cross sec t io n o f da ta en t r y and d i sp lay assembly g l a s s .

The cause o f the c rack i s unknown. Glass cracks have no t occur reds i n c e a r e v i s i o n w a s made t o the p rocedure used t o mount t h e glass t o t h ef a c e p l a t e of th e d at a en tr y and dis pla y assembly. The assembly i s qual-i f i e d f o r an e nv ir on me nt i n ex c e ss o f t h e f l i g h t c o n d i t io n s . T h e r e f o r e ,e i t h e r e xc e ss i ve i n t e r n a l s t r e s s e s ( un d er normal condi t ions ) were b u i l ti n t o t h e g l a s s , o r t h e mounting w a s improper (not as d e s i g n e d ) , o r t h eglass w a s i n a d v e r t e n t l y h i t .

C o r r e c t i v e a c t i o n c o n s i s t s o f a p p l y i n g a c l e a r p l a s t i c t a p e p r i o rt o f l i g h t on t h e glass of t h e e lectro lum ines cen t windows above t h e key-b o a r d ( f i g . 1 4 - 2 5 ) , l i k e t h a t p r e v io u s l y u s e d on t h e m is si on t i m e r win-

dows. The t a p e i s t o p r e v e nt d i s l o d g in g o f any glass p a r t i c l e s i f c rac ksoccur i n t h e f u t u r e, as w e l l as h e l p p r e v e n t m o i s t u r e f r o m p e n e t r a t i n g



14-42

2

Datapint

,

t h e electroluminescent segments should a crack occur.m o i s tu r e w ou ld c au se t h e d i g i t s eg me nt s t o t u r n d a rk i n a b ou t 2 h o u r s i fv o l t a g e were a p pl ie d t o a cracked un i t , making t h e assembly unreadab le .

The presence of

Shutterdrive


1 4 . 3 GOVERNMEWT FURNISHED EQUIPMENT

14.3.1 Noisy Lunar Topographic Camera Operat ion

The lunar topographic camera e x h i b i t e d n o i s y o p e r a t i o n f r om t h e t i m eof the Descar tes s i t e photography pass a t about 90 h o u r s .operate and standby modes w i t h power on t h e c am er a, t h e s h u t t e r o p e r a t io nw a s cont inuous.

I n b o th t h e

The developed f i l m i n d i c a t e s t h a t t h e camera w a s f u n c t i o n i n g p r o p e r l ya t t h e t ime of camera checkout a t about 34 hours . On t h e fou rth lu na rr e v o l u t i o n , good imagery of t h e l u n a r s u r f a c e w a s obta ined on 19 2 frames,s t a r t i n g a t Theophilus C rat er and ending about 40 seconds bef or e pas sin gt h e D e sc a rt es s i t e . The r e s t of t h e f i l m c o n s i s t s o f m u l t i p l e - e x p o s e dand f u l l y over-exposed f i l m.

P o s t f l i g h t t e s t s w i t h t h e f l i g h t camera showed sat isfactory opera-t i o n i n a l l s imula ted env ironments (p r ess ur e , t h e r m a l , a nd v i b r a t i o n ) a tone-g. An i n t e r m it t e n t f a i l u r e w a s found i n a t r a n s i s t o r i n t h e s h u t t e rc o n t r o l c i r c u i t (fig. 1 4 -2 7 ). The t r a n s i s t o r w a s contaminated wit h a

NASA-S-71-1695

12 voltslntcrvalaneterI supply I

Figure 14-27.- Lunar topograph ic camera s h u t t e r c o n tr o l .

L? .A- -



14-43

lo o se p ie ce of aluminum 0.130 i nc h .By 0.008 inch, which ws8 f o r e i g n t ot h e t r a n s i s t o r mater ia l .c o nt in u ou sl y t o t h e s h u t t e r d r i v e c i r c u i t , c au s in g c o nt in uo us s h u t t e ro p e r a t i o n , ndependen t o f the in te rva lomete r and independen t o f thes i n g l e , auto, or standby mode se le c t io ns . The sprock e t ho les i n t h e1/200 s l o t i n t h e s h u t t e r c ur ta in were t o r n as 8 r e su l t o f t h e p r o lo n g ed ,

cont inuous , h ig h- sp ee d s h u t t e r o p e r a t i o n ( f i g . 1 4 - 2 8) .

With a s ho rt ed t r a n s i s t o r , 28 v o l t s i s a p p l i e d

NASA-S-7 1-1696

Normal stopped positionof 1/200 s l i t With torn sprocket holes,

stow position of a l l s l i t sis variable

Figure 14-28.- Lunar topographic camera f i lm t r a c k .



14-44

The t r a n s i s t o r h ad b e en p a s se d by n orm al h i gh r e l i a b i l i t y s c r e e n i n gand by premis sion and pos tmiss ion sys tem accep tance t e s t s o p e r a t i n g u n d e rv i b r a t i o n , t h e r m a l , p r e s s u r e , and humidi ty c on di t i on s; none of which de-t e c t e d t h e p i e ce of aluminum. A d d i t i o na l s c r e e n i n g b e i n g c o n s i d e r e d f o rf u t u r e a p p l i c a t i o n s i n c l u d e s t h e u s e o f N-ray a nd a c o u s t i c i n s p e c t i o n .A n occur rence o f t h i s n a t u r e i s r a r e , but i t i s even r a re r f o r such ac o n d it i o n t o pass t h e hi gh r e l i a b i l i t y s c re e ni ng .

The anomaly occurred only a f t e r a p e r i o d of o p e r a t i o n a t zero-g i nf l i g h t , and when t h e c a se o f t h e t r a n s i s t o r i t s e l f w a s t a p p e d p o s t f l i g h t .


1 4 . 3 . 2 Extravehicular Glove Control

Af t e r s u i t p r es s ur i za t io n f o r t h e s eco nd e x t r a v e h i c u l a r a c t i v i t y,t h e Lunar Module P i l o t r e p o r t e d t h a t h i s r i g h t g l o ve h ad p u l l e d h i s h andt o t h e l e f t and down and t h a t he had no t had t h i s t r ou b l e dur ing th ef i r s t e x t r a v e h i c u l a r a c t i v i t y p e r i o d. The c o n d i ti o n w a s a nuisance

t hr ou g ho ut t h e s ec on d e x t r a v e h i c u l a r a c t i v i t y p e ri o d . I n i t i a l i n d i c a -t ions f rom the Lunar Module Pi lot were t h a t a c a b l e h ad b r ok e n i n t h eg love ( f i g . 14-29).

Cable guides (2 )

Figure 14-29.- E x t r a v e h i c u l a r g l o v e w r i s t c o n t r o l .



14-45

A d e t a i l e d e x am i na ti o n o f t h e re tu rned g love , toge ther wi th chambert e s t s , h av e shown t h a t t h e r e a r e no br ok en c a b l e s a n d t h a t t h e r e i s f r e eopera t io n o f t h e g love wr i sz -con t ro l cab le system. However, wi th th eLunar Module P i l o t i n t h e p r es s u r i ze d f l i g h t s u i t , t h e g l ov e to o k t h epos i t ion which w a s r e p o r t e d d u r i n g t h e m i s s i o n .

The w r i s t c o n t r o l assembly prov ides a f re e- mo vin g s t r u c t u r a l i n t e r -face between t h e g l o v e a n d t h e w r i s t disconnec t s o as t o a s s u r e c o n vo l ut ea c t i o n f o r w r i s t movement i n th e pr ess ur ize d s t a t e . The des ign inheren t lya l lo w s t h e g l o v e t o t a k e v a r i o u s n e u t r a l p o s i t i o n s .


14.3.3 In te rva lomete r Cyc l ing

During in te rv al om et er o pe ra tio n, th e. Command Module P i l o t hea rd onedouble cyc le f rom th e in te rva lomete r. Photography in d ic a te d th a t doublecyc l ing occur red 13 t imes out o f 283 exposures .

P o s t f l i g h t t e s t i n g w i t h t h e f l i g h t i n t e rv a l o m et e r a nd camera h asi n d i c a t e d t h a t t h e d o u bl e c y c l in g w a s caused by a random response of thei n t er v a l o m et e r t o t h e camera motor cu rr en t. The camera motor used on t h eApollo 1 4 cameras w a s a new motor hav ing s l i g h t l y h igher cur ren t charac-t e r i s t i c s .of th e u n i t s and no double cyc l ing .

P r e f l i g h t t e s t i n g of t h e e qu ip men t i n d i c a t e d c o m p a t i b i li t y

Double c y c l i n g d o es n o t r e s u l t i n d e t r i m e n t a l e f f e c t s t o t h e c am erao r t h e i n t e rv a l o m et e r. No loss of photographic d a t a occurs as a r e s u l to f d o ub l e c y c l i n g . M o d i fi c at i on s t o t h e in t e r v a l o m e t e r t o make i t l e s ss e n s i t i v e t o t h e random p u l s e s o f t h e camera motor w i l l be made, i f prac-t i c a l . On A po llo 1 5 , t h e i n t e r v a l o m e t e r w i l l only provide Hasselblad

backup t o th e s c i e n t i f i c ins t rument module cameras.


1 4 . 3 . 4 Intermittent Voice Communications

A t approximately 29 hours , Miss ion Cont ro l had d i f f i cu l t y i n com-mun icating with th e Coxnander. The Commander re pla ced h i s con stan t wearg a r m e n t e l e c t r i c a l a d a p t e r ( f i g . 14-30) with a s p a r e u n i t , a n d s a t i s f a c -tory communicat ions were reestabl ished.

Fo l lowing re l ea se o f t h e hardware f rom qua ran t ine , a l l four con-s t a n t w ear g ar me nt e l e c t r i c a l a d a p t e r s w ere t e s t e d f o r c o n t i n u i t y an dr e s i s t a n c e , a n d a l l u n i t s were s a t i s f a c t o r y . The a d a p te r s were t h e n



14-47

c o n ne c t ed t o a portable communications s e t which provided condi t ionss i m i l a r t o f l i g h t c on di ti on s. Whi le connec ted , the adap te r s were sub-j e c t e d t o t w i s t i n g , b en di ng , and pu l l in g. None of th e ada pte rs showedany e l e c t r i c a l i n t er m i t t e n ts .

The most l ikely cause o f t h e problem w a s poor contact between con-

nec to r s because of s m a l l contaminants or improper mating of8

connec to r,which w a s cor r ec te d when th e spa re adap te r w a s i n s t a l l e d .


1 4 . 4 MOLL0 LUNAR SURFACE EXPERIMENTS PACKAGE

1 4 . 4 . 1 Acti ve S eism ic Experiment Thumper Mis fi res

. During the f i r s t e x t r a v e h i c u l a r a c t i v i t y , t h e c rew d ep lo ye d t h et hu mp er a nd geophones a nd a tt e mp t ed t o f i r e t h e i n i t i a t o r s w i t h t h e

fo l lowing r e su l t s : 1 3 f i r e d , 5 m i s f i r e d , and 3 i n i t i a t o r s w ere d e l ib -e r a t e l y sk ipped t o save t ime .t o f i r e e a c h i n i t i a t o r .i t w a s n e c e s s a ry t o s q u ee z e t h e f i r i n g s w i t c h knob w i t h b o t h h a nd s .s e q u e n t l y, t h e e x c e ss i v e s t i f f n e s s seemed t o be r e l i e v e d an d one-handa c t u a t i o n w a s p o s s i b l e .

I n some instances , wo attempts were madeI n a d d i ti o n , f o r t h e f i r s t f ou r o r f i v e f i r i n g s ,

Sub-

The m os t l i k e l y c a u s es o f t h e p ro bl em a r e a s s o c i a t e d w i t h t h e d e t e n tp o r t io n of t h e s e l e c t o r sw i tc h ( f i g . 14-31) and dirt on t h e f i r i n g sw i tc ha c t u a t o r b e a r i n g s u r f a c e . The s e l e c t o r s w i tc h d i a l c an r e p o s i t i o n o u t ofd e t e n t i n t h e c o u r s e o f n orm al h a n dl i ng b e c au s e o f t h e l a c k o f p o s i t i v es e a t i n g i n t h e d e t e n t f o r ea ch i n i t i a t o r p o s i ti o n . For an i n i t i a t o r t ob e f i r e d , t h e s e l e c t o r s w it ch must p r ov i de c o nt a c t t o t h e p r o p er u n f i r e d

i n i t i a t o r p o s i t i o n . Exam ination o f t h e q u a l i f i c a t i o n u n i t ha s shown t h a tt h e d e t e n t i s p o s i t i o n e d a t t h e l e a d i n g e dg e o f t h e c o n t a c t s u r f a c e s ot h a t any movement toward th e previous po si ti on w i l l break t h e c o n t a c t .Also, t h e l i g h t e n i n g h o le s i n t h e f i r i n g s w i t c h knob make i t p o s s i b l e f o rd i r t t o g e t o n to t h e Te f lo n be a ri n g s u r f a c e s , t e m p o ra r i l y i n c r e a s i n g t h ef o r c e r e q u i r e d t o c l o s e t h e s w it ch ( f i g . 1 4- 31 ).

Cor rec t ive a c t i on f o r Apollo 1 6 c o n s i s t s o f a d d i n g a p o s i t i v e d e -t e n t mechani'sm, pro per ly a l ig ned w i t h t h e s e l e c t o r s w it c h c o n t a c t s , a ndd u s t p r o t e c t i o n f o r t h e f i r i n g s wi tc h a c t u a t o r a ss em bl y.i s not ca rr ie d on Apol lo 1 5 .

The thumper




14-50

NASA-S-7 1-1700

cable

reel-spins crank

Figure 14-32.- Lunar portable magnetometer cable r e e l .



14-51

The l un ar por tab le magne tomete r r ibbon cab le sn a r l s eas i ly a t 1/68an d i s d i f f i c u l t and t e di o us t o u ns n a r l.t h e h and f ro m t h e c r an k t o u n s na r l t h e c a b l e d u r i ng t h e f i r s t p a r t o fr ew in di ng t h e c a b l e , t h e c a b l e w i l l unwind within t h e r e e l and s p i n t h er e e l h a n d l e ( f i g . 1 4 - 3 2 ) .ing deployment; however, i t i s d e s i ra b l e t o b e able t o l oc k t h e r e e la g a i ns t r o t a t i o n a t t i m e s dur ing rewind o f th e cab le . Rewinding w a sd i f f i c u l t b e ca us e t h e r e w a s no p ro v i s i o n t o l o c k t h e r e e l d u r i n g r ew i nd ,a nd g r i p p i n g t h e r e e l and crank w a s d i f f i c u l t w i t h t h e gloved hand.

If i t i s necessa ry t o remove

Free unwinding of the r e e l i s r e q u i r e d d u r -

C o r r e c t i v e a c t i o n f o r A p o l l o 16 c o n s i s t s o f a d di ng a r a t c h e t a n dp aw l l o c k i n g d e v i c e f o r a c t u a t i o n w i t h t h e gloved hand, and p rov id inga b e t t e r g r i p f o r t h e r e e l and crank.i s not ca r r i e d on Apol lo 15.

The lunar por tab le magne tomete r


14 .4 .4 Central Sta t ion Twelve-Hour T i m e r F a i l u r e

The c e n t r a l s t a t i o n t i m e r p u l s e s d i d not occur a f t e r i n i t i a l a ct iv a-t i o n . Uplink command t e s t s v e r i f i e d t h a t t h e t i m e r l o g i c a nd t h e p u l s es w i t c h e s w e r e f un c ti on in g s a t i s f a c t o r i l y , b ut t h a t t h e m e c h a n i c a l s e c t i o no f t h e timer w a s n o t d r i v i n g t h e s w i t c h e s . T i m e r f u n c t i o n s s t a r t e d t ooccur and the 12-hour pulses w e r e prov ided 13 times i n s u c ce s s i o n, i n d i -c a t i n g t h a t t h e t i m e r b a t t e r y a nd o s c i l l a t o r are s a t i s f a c t o r y , b u t t h a tt h e m e c ha ni c al s e c t i o n i s o p e r a t i n g i n t e r m i t t e n t l y. The f a i l u r e o f t h et i m e r i s a s s o c i a t e d w i t h t h e m e ch a ni ca l d e s i g n .

T h i s anomaly i s s imilar t o t h e t i m e r problem ex per ie nced on Apol lo 12 .The l o s s o r e r r a t i c o pe r at i on of t h e 1 2- ho ur t imer o u t p u t p u l s e h a s n oadverse e ff ec t on exper iments opera t ions . The Apol lo 1 5 c e n t r a l s t a t i o n

has a new so l id - s ta te t i m e r .off by ground command, as i s planned f o r t h e A po ll o 1 2 s t a t i o n .The Apollo 1 4 c e n t r a l s t a t i o n w i l l be t u r n e d


14.4.5 Passive Seismic Experiment Y- A x i s L e v e l i n g I n t e r m i t t e n t

The hor i ' zon ta l Y-axis l e ve l i ng motor of t h e g imbal l ev e l in g systemo p er a te s i n t e r m i t t e n t l y ( f i g . 14-33). Although a command verification i sr e c e i v e d when commands ar e s e n t , pow er i s n o t n e c e s s a r i l y r e c e i v e d by t h emotor. When t h e r e i s an i n d i c a t i o n o f p ow er t o t h e m ot o r, t h e m ot or d o e so p e r a t e . As a r e s u l t , d u r i n g t h e f i r s t l u n a r d a y, r e s p o n s e t o g r ou nd

commands w a s normal excep t fo r 6 o f t h e 22 conrmands when t h e r e w a s noresponse .



14-52

NASA-S-7 1-1 701

+29 volts

+12 volts 1-I

~ III

evel motor S .

RY-axis) on/ ~ _ t

off command

-12 ifolts

Figure 14-33.- Y-a xi s l e v e l i n g motor c i r c u i t r y.

Y-axis motordrive circuit

7

Although no sc ien t i f i c data have been l o s t t o d a t e , i n t e r m i t t e n tproblems have been encou ntered when l ev el in g t h e Y-axis of t h e g i m b a lplatform upon which are mounted th e t h ree or thogona l long-period seis-mmeters.o r t h e response i s delayed when the Y - a x i s m t o r i s commanded on. De-l a y times v a r y.commands a t v a r y i n g t i m e i n t e r v a l s .

O c ca s io n a ll y, e i t h e r t h e r e i s no e lec t ro -mechan ica l r esponse ,

Thus f a r , l e v e l i n g has been achieved by cyc l in g on/o ff

The problem i s caused by an i nt er mi t t en t component i n th e motorc o n t r o l c i r c u i t ( f i g . 1 4-3 3) .

rence of th e problem and t h e t e m p e r at u r e o f t h e lunar s u r f a c e , t h e c e n -t r a l s t a t i o n e l e c tr o n i c s , or t h e experiment. Whenever t he re i s an ind i -c a t i o n of power to t h e motor, th e motor oper a tes . When the m t o r oper-a t e s , i t o p e r a t e s p r o p e r l y and p u l l s t h e normal cur ren t .

There i s no cor re la t ion be tween the occur-

If th e p rob lem becomes worse u n t i l Y -ax i s l e ve l in g cannot beachieve d, an emergency op er at io na l mde can be implemented such as d r i v -i n g r e m ai n in g a x e s t o t h e i r s t o p s i n bo th d i r e c t i o n s i n an a t t em p t t of r ee electro-mechanical components which may be s t i c k i n g . P r e s e n t l y,however, t h e problem has n o t b een s u f f i c i e n t l y s e r i o u s t o w ar r an t i n t e r -r u p t i o n of c o n ti nu o us s c i e n t i f i c data t o at tempt s u c h o p e r a t i o n s .




14-53

14.4.6 Pass ive Se i smic Exper iment Feedback F i l t e r Fa i lu re

The long-period v e r t i c a l ( Z ) seismometer w a s un st ab le when oper ate dw i t h the feedback f i l t e r i n . The f ee db ac k f i l t e r s f o r a l l t h r e e l o n g -p e r i o d axes (X, Y , and Z ) were removed by command, and good data (undamped)now con t inue t o be rece ived . The f i l t e r -o u t mode p rov ides feedback t o t h ese i smometer fo r a l l p e r i o d s o f o p e r a t i o n w i t h an ins t rument hav ing a n a t -u r a l pe r i od of approx imate ly 2 .5 seconds . Al though t h e response curvesare p e a k e d r a t h e r t h a n f l a t , and c r i t i c a l l y damped, no se i sm ic energy i nt h e 0.5- t o 15-second-per iod range i s l o s t .

The f i l ter- in mode provides a 1000-second t i m e c on st an t f i l t e r i nt h e feedback loop f o r an ins t rument hav ing a n a t u r a l p e r i o d of a p pr o xi -mate ly 1 5 seconds wi t h a c r i t i ca l l y damped, f l a t - res pon se curve . OnApollo 14 l o n g- p e ri o d s e is m om e te r s, t h e d a t a d u r i n g t h e f i l t e r - i n modehave ind ica ted a g e n er a l c h a ra c t e r i s t i c of i n i t i a l o s c i l l a t i o n s g oi ng ont o s a t u r a t i o n . The p ro bl em ap pe ar s t o b e e l e c t r i c a l r a t h e r t h a n mechan-i c a l as e x p e r i e nc e d w i t h t h e b e n t f l e x u r e s o f t h e A p ol lo 1 2 long-per iodv e r t i c a l s e is m m et e r.

i n g ha ve i n d i c a t e d n o a b n o r m a l i ti e s .

Performance data dur ing Apol lo 1 4 a c c e p t a n c e t e s t -

Pre l iminary ana lys i s o f sc ience da ta f rom Apol lo 11, 1 2 , and 1 4i n d i c a t e s t h a t t h e n a t u r a l lunar se i smic reg ime f a v o r s t h e r a n g e o f 0.5-t o 3.0-second periods. As a r e s u l t i t i s q u i t e p ro ba bl e t h a t f u t u r ep a s s i v e s e i s m i c e x p e r i m e n t u n i t s o n t h e lunar s u r f a c e w i l l b e o p e r a t e di n t h e f i l t e r - o u t mode i n o r d e r t o maximize t h e s e n s i t i v i t y a t t h e a p p a r -en t l y favored 2 .0- second pe r iod .long-period se i smometer s a re being opera t ed i n th e f i l t e r- ou t mode , pro-d uc in g s a t i s f a c t o r y d a t a .

A t p r e s e n t , b o t h A p o l l o 1 2 and Apollo 1 4


14.4 .7 Active Seismic Geophone 3 E l e c t ro n i c C i r c u i t E r r a t i c

The experiment w a s tu rne d on i n th e l is t en in g mode on March 26 ,1971, and geophone 3 d a t a were s p i k i n g o f f - s c a l e h i g h ( f i g . 14-34) .When t h e geophone channels were ca l i br at ed , t h e geophone 3 channel wento f f - s c a l e h i g h s im u l t a n e ou s l y w i th t h e s t a r t of t h e c a l i b r a t i o n p ul s ea nd s t a y e d o f f - s ca l e h i gh f o r t h e r e m ai nd er o f t h e l i s t e n i n g pe r i o d .Dur ing the 1 - second pe r iod when the ca l ib ra t ion pu l se w a s p r e s e n t , d a t afrom geophones 1 an d 2 showed th e normal 7-her tZ r in gin g caused by t h eca l i br at io n pu ls e . However, geophone 3 da ta showed four negat ive-goings p i k e s c o i n c i d e n t w i t h t h e f i r s t f o u r n eg a t i v e h a l f c y c le s of t h e r i ng -i n g on t h e o t h e r t wo c h a n n e l s .t h e f i r s t t o t h e l a s t , t h e l a s t having an ampl i tude o f 90 p e r c e n t o f

The s p i k e s d e c r e a s e d i n d u r a t i o n f r om



14-54

v ! ?L?N N l n

I

0



14-56

The experiment e l ec tr on ic s uses "cordwood" co ns tr uc t io n of t h e typewhich has caused so ld er c racks i n o t he r equipment . Two copper paths con-d u ct t h e f e ed ba ck d io d es t o t h e l o g a r i t h m i c c om pr es so r a m p l i f i e r.s o l d e r c ra ck i n e i t h e r p a t h would t h e n r e su l t i n t h e d a t a c h a r a c t er i s t i c s .

A

There are 10 s u ch s o l d e r j o i n t s f o r ea ch geopho ne ( f i g . 14-36) :four on th e oven t e r m i n a l board , fo ur on t h e mother board , one on th eto p board of t h e lo g compressor module, and one on t h e bottom board oft h e l o g compressor module.to p board of t h e lo g compressor module. Cont in ui ty a t t h e j o i n t re-covers as long as t h e c r a c k c l o s e s d u r i n g t h e lunar day.

The one most l i k e ly t o fail f i r s t i s o n t h e

NASA-S-71-1704

Most l ikely cracked joint

Oventermina Iboard -

- . . . .A ..

Log compressortop board

- Log compressabottom bad

Motherboard

Figure 14-36.- Suspec ted c racked so ld er jo in t s i n amp l i f i e r .

The log compressor modules f o r geophones 1 and 2 a r e o f t h e sametype cons t ruc t ion . S ince t h e s e are l o c a t ed s l i g h t l y f u r t h e r from t h eoven than the one for geophone 3 , t h e maximum tem pe ra tu re may n ot beq u i t e as high . As a r e s u l t , it may t a k e l o n g e r f o r them t o c r a c k , i fa t all.

S y s t e m s t e s t i n g i n c l u d e d o p e r a t i o n a l t h e r m a l c y c l i n g t e s t s o v e r t h etempera tu re range fo r l un ar day and n i gh t .are a f 'unct ion of t ime as w e l l as tempera tu re , and apparen t ly t h e g roundt e s t c y c l e d i d n o t allow enough t i m e f o r a c r e e p f a i l u r e .w a s designed a n d b u i l t p r i o r t o t h e t i m e when i t w a s found t h a t cordwoodc o n s t r u c t i o n w i t h s o ld e re d j o i n t s w a s u n s a t i s f a c t o r y.

However, c racked so l de r j o i n t s

This equipment

If li. ? 'L

?L-



14-57

A breadboard of t h e logar i thmic compressor has been constructed,and the diode feedback loop will b e o pe ne d t o d u p l i c a t e t h e e xp e ri m en td a t a . The mechanical design of th e log ar i thm ic compressor w i l l be re-viewed t o de te rmine t h e changes th a t must be made t o p reven t s o l de rcracks on Apollo 16.Apollo 1 5 .

The a c t i ve s e i sm ic exper iment i s n ot c a r r i e d o n

Procedura l changes under cons i de ra t ion inc lud e opera t ion o f t h eoven t o main ta in compressor module t empera tu re because t h e s o l de r j o i n twhich i s most l i k e l y cracked i s i n c om pr es si on ( s t r o n g e r ) a t t h e h i g h ertempera tu re .


14.4.8 I n t e r m i t t e n t Lnss of V a l i d Data from Suprathermal IonDet ecto r Experiment Po si t i ve Analog-to-Digi ta l Converter

The data i n w ord s 2 , 3, 7 , an d 8 o f t h e s u pr a t he r m a l i on d e t e c t o r

exper iment became e r ra t i c a t 19:09 G . m . t . on April 5 , 1971. Th is con-d i t i o n c o nt i nu e d. u n t i l 22:15 G.m. t . on April 6. The same e r r a t i c c o n -d i t i o n w a s a l so observed dur ing ope ra t ion a l suppor t pe r iods on Apr i l 7 ,9 , and 21. Only t ho s e measurements a s s o c i a t e d w i t h t h e p o s i t i v e s e c t i o no f t h e l o g a n a l o g - t o - d i g i t a l c o n v e r t e r w e r e a f f e c t e d . There has been noloss of s c i e n c e d a t a .

The a ff ec t ed measurements have a data c h a r a c t e r i s t i c w he re in e achp a r a m et e r p r o c es s e d by t h e p o s i t i v e l o g a n a l o g - t o - d i g i t a l c o n v e r t e ri n i t i a l l y i n d i c a t e s f i l l - s c a l e o u t p u t , f ol lo we d by an er ro ne ou s d a t av a l u e . The e r ro n eo u s d a t a v a l u e c o r r e l a t e s w i t h t h e v a lu e o f t h e p r e-ceding measurement i n t h e s e r i a l da t a format p roces sed by t h e nega t iv eana log- to - d ig i t a l conver te r . The e r roneous da ta va lu e i n some ins t ance s

i n d i c a t e s o n e PCM count l e s s than t h e nega t ive ana log- to -d ig i t a l con-v e r t e r p ar am et er.

An i n t e r m i t t e n t f a i l u r e o f t h e s t a r t r e s e t p u l se f o r t h e p o s i t i v el o g a n a l og - t o- d i g it a l c o n v er t e r c o n t r o l l o g i c ( f i g . 14-37) could causet h e problem. Although t h e f a i l u re p er mi ts t h e p o s i t i v e c o nv e rt e r i n i t i a lo u tp u t t o f i l l t h e e igh t -b i t b ina ry coun te r and p roduce a f u l l - s c a l e read-i n g ; t h e r e a f t e r , w h e n a s t a r t pulse f o r t h e p o s i t i v e c o n v er t e r s ho ul d re -s e t t h e e i g h t - b i t c o u nt e r , i t f a i l s t o do s o , and the negat ive word whichi s s t i l l i n t h e c ou nt er i s read ou t as a pos i t ive word .t o be an in t e r mi t t en t component o r w i r e c o nn e ct i on i n one o f t h e a s s o c i a t e dmodules.The components have been passed by normal high r e l i a b i l i t y sc ree nin g, and

systems t e s t s h av e i n c l u d e d o p e r a t i o n a l p r e s s u r e , t e m p e r a t u r e , v i b r a t i o n ,humid ity, and acc e le ra t ed lunar env ironment cyc les . N o f a i l u r e o f t h i s

The cause appears

However, i t does not appear t o be a f u n c t i o n o f t h e t e m p er a t ur e .



14-58

Analog to Clock Serial

digital data inp utsenable

Engineering c Multiplexer bit format c

counter logic

Data tocentralstation

Figure 14-37.- S i m p l i f i e d d a t a l o g i c c o n t r o l .

type has been experienced with ground t e s t s . No a d d it i o na l t e s t i n g i scons idered war ran ted f o r Apollo 15, which w i l l be t h e l a s t m i s s i o n f o rthe exper iment .


14.4.9 Charged Par t i c le Lunar Environment ExperimentAnalyzer B Data Lost

The voltage measurement r e a d i n g on t h e a n a l y z e r B power supply( f i g . 14-38) became er r a t i c on Apri l 8, 1971, a n d t h e a n a l y z e r B s c i e n c ed a t a w e r e l o s t .

On A p r i l 1 0 an d 1 6 , the exper iment w a s commanded on t o nor mal (low-vo lt ag e) mode, and t o in cr ea se (high-vol tage) mode i n a se r i e s o f t e s t s .The r e s u l t s i n d i c a t e t h a t t h e p l u s 28 -v oi t i n p u t , t h e r e g u l a t o r , an d t h ea n a l y z e r A power supply w e r e f u n c t i o n i n g p r o p e r l y, a nd t h a t t h e p ro bl emw a s i n t h e a na ly ze r B power supply.

The high -volta ge power sup ply i s a t r a n s i s t o r o s c i l l a t o r . The reso-nant elements a re a t r an s fo rmer p r imary winding and a capac i to r connec tedi n p a r a l l e l b etween t h e t r a n s i s t o r e m i t t e r and ground.f o rm e r w in di ng p r o vi de s p o s i t i v e f ee db ac k t o t h e t r a n s i s t o r base , c a u s i n g

A second trans-



r

4I

Cr)I

fr l



14-60

t h e c i r c u i t t o o s c i l l a te . A t h i r d t r an s f or m e r w in di ng s u p p i i e s t h e i n -p u t t o a d i o d e - c a p a c i t o r v o l t a g e m u l t i p l i e r c h a i n .v o l t a g e m u l t i p l i e r i s t h e n f i l t e r e d and d r iv e s t h e c h ar ge d p a r t i c l e ana-l y z e r .f i l t e r e d . The f i l t e r e d v o l ta g e i s t h e n m o n i t o r ed by t h e i n s t r u m e n t a t i o nsystem and i s p r o p o r t i o n a l t o t h e h ig h v o l t ag e s u p p l ie d t o t h e a n a l y ze r .

T h e o u t p u t o f t h e

The o u t p u t o f t h e f o u r t h t r a n s f o r m e r w in d in g i s r e c t i f i e d and

Data i n d i ca t e d t h a t a f t e r t h e f a i l u r e o c c u r re d , t h e i n st r u me n ta t io no u t p u t w a s between 2.00 and 2.25 v o l t s dc . T h i s c o u ld n o t oc c u r i f t h eo s c i l l a t o r were no t s t i l l o s c i l l a t i n g . The i n p u t t o t h e v o l t ag e m u l ti -p l i e r i s a l s o p r o po r t io n a l t o t h e i n st r u me n ta t io n o u tp u t . S h o r ts t oground can be pos tu la ted a t v a r io u s p o i n t s i n and downstream of t h e vo l t -age m u l t i p l i e r , and t h e s h o r t c i r c u i t c u r r e n t can be r e f l e c t e d back i n t ot h e t r a n s f o r m e r p ri ma ry w i n d in g t o deter mine how much t h e out pu t v ol ta geshould be decreased . The decrease occurs because t h e t ransformer p r i -mary w in d in g ( t h e d r i v i n g w i n d i ng ) h as r e s i s t a n c e ( a b o ut 300 ohms) , an dany v o l t a g e d ro pp ed a c r o s s t h i s r e s i s t a n c e i s n o t a v a i l a b le t o d r i v e t h etrans fo rmer.

T he se c a l c u l a t i o n s show t h a t t h e s h o r t c i r c u i t mu st be i n o ne o ft h e o u tp ut f i l t e r ca pa ci to r s i n t h e h ig h- vo ltag e f i l t e r , i n t h e i n t e r -connect ing cable between the f i l t e r an d an a l y z er , o r i n t h e a n a ly z e r.S h o r t c i r c u i t s i n any o t h e r l o c a t i o n s w o u l d r e s u l t i n a much lower in-s t r u m e n t a t i o n o u t p u t v o l t a g e .

This i s t h e l a s t t i m e t h e c h a rge d p a r t i c l e l u n a r en v ir on m en t e x p e r i -ment w i l l be flown. If t h e f a i l u r e p r o pa ga te s t o t h e p o i n t w here t h em a l fu n c ti o n in g power s u p pl y s t o p s o s c i l l a t i n g , t h e c u r r e n t t a k e n b y t h i ss u pp l y w ou ld i n c r e a s e t o a bo ut 0 .1 am pere. I f t h i s i s s u f f i c i e n t t odamage t h e s e r i e s v o l t a g e r e g u l a t o r used f o r l o w - v o l t a g e o p e r a t i o n , t h eopera t ing p rocedures w i l l be m o d i fi e d t o u s e l o w - vo l ta g e o p e r a t i o n asl i t t l e as p o s s i b l e t o e x te n d t h e v o lt a g e r e g u l a t o r ' s l i f e .



A-1

APPENDIX A - VEHICLE DESCRIPTION

The Apollo 1 4 s p a c e v e h i c l e c o n s i s t e d o f a block I1 c o n f i g u r a t i o ns p a c e c r a f t a n d a Saturn V l aunch veh ic le (AS-509). The assemblies com-p r i s i n g t h e s p a c ec r a f t c o n s is t ed o f a launch escape system, command and

service modules (CSM-1101, a s p a c e c r a f t / l a u n c h v e h i c l e a d a p t e r, a n d alunar module (IM-8). The changes made t o t h e command and s er v ic e modules,t h e l u n a r m o du le, t h e e x t r a v e h i c u l a r m o b i l it y u n i t , t h e lunar s u r f a c eexperiment equipment, and t h e l au n c h v e h i c l e s i n c e t h e A p ol lo 13 missiona re pre sen ted . The changes made t o t h e s p a c e c r a f t s ys te ms are more num-e r o u s t h a n f o r p r e v i o u s l u n a r l a n d i n g m i s si o n s p r i m a r i l y b e c au s e of im-provements made as a r e s u l t of t h e A po ll o 13 problems and preparat ionsf o r more e x t e n s i v e e x t r a v e h i c u l a r o p e r a t i o n s .

A . l COMMAND AND SERVICE MODULE

A . l . l Structural and Mechanical Systems

The m o r s t r u c t u ra l changes were i n s t a l l a t i o n s i n t h e s e r v i c e mod-ule t o accommodate an ad di t io na l cryogenic oxygen t ank i n s e c to r 1 an dan a u x i l i a r y bat tery i n s e c t o r 4. These changes are d i s c u s s e d f u r t h e ri n s e ct io n A.1.3.

S t r u c t u r a l c ha ng es w er e made i n t h e s p a c e c r a f t / l a u n c h v e h i c l e a d a p t e ras f o l l o w s .c e s s t o q ua dr an t 2 of th e luna r module descen t s t a ge where Apol lo lun arsu rf ac e experiment subpackages 1 an d 2 were stowed.bonded on t h e a d a p t e r a t s t a t i o n 547 ( 21 5 de g ) i n c a s e a s imilar door ha d

b ee n r e q u i r e d f o r c o nt in ge nc y a c c e s s t o t h e lu na r module cryogenic heliumtank dur ing p re launch opera t ions .

A door w a s i n s t a l l e d a t s t a t i o n 547 (305 deg) t o p rov ide ac-

Also, doublers were

The i n t e r i o r o f gussets 3 and 4, which contain t h e breech-plenumassemblies of t h e fo rward hea t sh ie ld j e t t i s o n i ng sys tem, were armoredw i t h a poly imide- impregnated f i be rg la ss t o p reven t burn- th rough of th egussets and poss ib le damage t o ad jacen t equ ipment i n th e even t o f es-cap ing gas f rom th e b reech assembl ies .



A-2

A . 1 . 2 Environmental Control System

The p o s t l a nd i n g v e n t i l a t i o n v a l v e s were m o d if i ed t o i n c o r p o r a t e dry( n o n - l u b r i c a t e d ) b r ak e s h oe s t o p re v e n t p o s s i b l e s t i c k i n g an d a secondshear p i n w a s added t o i n s u r e p o s i t i v e d r i v e b et we en t h e a c t u a t o r s h a f tand cm.

To p r o v id e c o n t r o l l e d v e n t i n g f o r an oxygen t ank flow t e s t , t h e i n -t e r n a l diameter of t h e a u x i l i a r y dump no z z l e ( l o c a t e d i n t h e s i d e h a t c h )w a s en la rged .

Sodium n i t ra te w a s added t o t h e b u f f e r ampules used i n s t e r i l i z i n gt h e p o t a b l e water, Addit ion of t h e s o d i u m n i t r a t e w a s t o r e d u ce s y st emc o r r o si o n and enhance t h e s t e r i l i z a t i o n q u a l i t i e s o f t h e c h l o r i n e .

A vacuum cleaner w i t h detachable bags w a s added t o a s s i s t i n remov-i n g l u n a r d u s t from su i t s and equ ipment p r i o r t o i n t ra v e h ic u l ar t r a n s f e rfrom t h e l u n a r module t o t h e command module a f t e r l u n a r s u r f a c e o p e r a -t i o n s , a nd f o r c le an up i n t h e command module.

A.1 .3 E le c t r i c a l Power System

The e l e c t r i c a l p ower s y st em w a s ch an ged s i g n i f i c a n t l y a f t e r t h eApollo 1 3 cryogenic oxygen subsystem f a i l u r e .f o l l o w s .

The maJor changes a re as

a. T h e i n t e r n a l c o n s t r u c t i o n o f t h e c r y o g e n i c o x y g e n tanks w a s mod-i f i e d as d e s c r ib e d i n t h e f o l lo w i ng t a b l e .

Prev ious b lock I1 v e h ic le s CSM-110 and subs eque nt v eh ic le s

E a c h tank contained two destrat- Fans were dele ted .i f i c a t i o n f a n s .

Q u a n t i t y g a g in g p r o b e w a s madeof aluminum.

Heater c o n s i s t e d o f tw o para l -l e l - c o n n e c t e d elements woundon a s t a i n l e s s s t e e l t u b e .

F i l t e r w a s l o c at e d i n t a n kd i s c h a rg e .

Ta n k c o n t a i n e d h e a t e r t h e r m a ls w i t ch e s t o p r ev en t hea te relement from overhea t ing .

Fan motor wiring w a s Teflon-i n s u l a t e d .

Quant i ty gag ing probe materialw a s ch an ged t o s t a i n l e s s s t e e l .

Heater w a s changed t o t h r e e par-a l l e l -connec ted e lements w i t hsepara te con t ro l o f one e lement .

F i l t e r w a s r e l o ca t e d t o e x t e r n a ll i n e .

Heater t h e r m a l switches were re-move d.

All w i r i n g w a s magnesium oxide-i n s u l a t e d a n d s h e a t h e d w i t hs t a i n l e s s s t e e l .



A-3

b . A th i rd c ryogen ic oxygen s to rage t a n k w a s i n s t a l l e d i n s e c to r 1o f t h e service module. T h i s t a n k s u p p l i e d olCygen t o t h e f u e l c e l l s a ndcould be used s imul taneous ly With t h e two t a n k s i n s e c t o r 4. A new iso-l a t i o n v al ve w a s i n s t a l l e d betw een t a n k s 2 and 3 t o pr ev en t t h e l o s s o foxygen from tank 3 i n t h e e ve nt o f damage t o t h e p lumbing f o r t an ks 1 and2. The c l o s e d i s o l a t i o n valve a l s o would have prevented the f low of oxy-gen from tank 3 t o t h e f u e l c e l l s .t h e e n v ir o n m en t al c o n t r o l s ys te m w i th t h e i s o l a t i o n valve c l o s e d w h i l et h e a u x i l i a r y b a t t e r y, mentioned i n paragraph e , w a s t h e s o ur ce o f e l e c -t r i c a l power.

However, tank 3 could have su pp l ied

c. The tan k 1 and 2 pressure swi tches remained wi red i n se r i es asi n t h e p r e v i o u s c o n f i g u r a t i o n ; t h e t a n k 3 swi tch w a s w ir ed i n p a r a l l e land w a s independent of tanks 1 and 2.

d. The f u e l c e l l s h u t o f f v al ve u s ed p r e v io u s l y w a s an i n t e g r a lf o rg i n g c o n t a i n i n g t w o c h e c k v a l v e s a n d t h r e e r e a c t a n t s h u t o f f v a l v e s .I n t h e v al v e u se d f o r CSM-I lO, the two check valves remained i n t h e i n -te g r a l fo rg ing ; however, t he rea c tan t sh u to ff va lves were removed andr e p l a c e d by t h r e e v a l v es r e l o c a t e d i n l i n e w i t h t h e i n t e g r a l f o r g i n g .These valves were the same type as t h o s e u s e d i n t h e service module r e -ac t ion con t ro l he lium system. "he va lve s e a l s were changed t o a t y p et h a t prov ides a b e t t e r s e a l un de r ex tr em e c o l d . F igure A-1 i l l u s t r a t e st h e m aj or c ha ng es t o t h e s y st em e xc e pt f o r t h e i n t e r n a l t a n k c h a n ge s.

e . A n a u x i l i a r y b a t t e r y, h av in g a ca pa ci ty of 400-ampere ho urs , w a si n s t a l l e d o n t h e a f t bulkhead i n s e c t o r 4 o f t h e s e r v i c e module t o p ro -v i d e a s o u r c e o f e l e c t r i c a l power i n c a s e o f a cryogenic subsystem f a i l -ure. Two con t ro l boxes, no t used on p rev ious f l i g h t s , were added t o ac-commodate t h e a ux i l i a r y ba t t e ry . One box contained two motor switcheswhich could disconnect f u e l c e l l 2 from the service module and connectt h e a u x i l i ar y b a t t e r y i n i t s pla ce. The second box con tain ed an over-

l o a d s e n s o r f o r w i re p r o t e c t i o n .

A.1.4 Ins t rumenta t ion

S ix new tel em etr y measurements as so ci at ed wi th th e h igh-ga in an tennawere added t o in di ca te p i t ch , yaw, and beam-width, and whether th e antennaw a s o p e r a t i n g i n t h e m anual, a ut om at ic t r a c k i n g , o r r e a c q u i s i t i o n m d e .This a d d i t i o n a l i n s tr u m e n t at i o n p ro vi de d d a t a t o s u p p o r t F l i g h t C o n tr o lmanagement of t h e high -gain antenna.

Other instrumentat ion changes were as fol low s. The cabin pr es su ret r a n s d u c e r w a s re pla ced with one which had been reworked, c lean ed, andinspec te d f o r con taminan ts . I n t h e p a s t , l o o s e n i c k el - p la t i ng p a r t i c l e sh a d i n t e r f e r e d w i t h i n f l i g h t me as ur em en ts . A d d i t i on a l i n s t r u m e n t a t io nw a s i n c o r po r a t ed t o m o ni to r t h e a u x i l i a r y b a t t e r y, the oxygen tank hea te relement tempe ratures , th e oxygen tank 2 an d 3 manifo ld p res sur e , and th et m k 3 p r e s s u r e .



A- 4

NASA-S-7 1-1707c;1Oxygen relief

Pressure transducer

Pressure switch

(Third oxygen tankand half-system

valve module added)

Figure A-1.- Cryogenic oxygen storage system.



A-5

A.1 .5 Pyro techn ics

F a b r i c a t i o n a n d q u a l i t y c o n t r o l p r o c e d u re s o f t wo p y r o te c h n i c d e v i c e sused i n t h e command and se rv ic e module t en si on t i e cutter and the commandmodule fo rward hea t sh ie ld j e t t i s on in g sys tem were improved. Although noknown i n f l i g h t p ro blem w it h t h e t e n s i o n t i e c u t t e r h as e x i s t e d , a Skylabqu a l i f i c a t io n t e s t (pe rfo rmed under more severe vacuum and the rmal condi -t i o n s t h a n f o r Ap o ll o) r e v e a l ed t h a t i t v a r i e d i n p e r fo r ma n ce .f o r wa r d h e a t s h i e l d j e t t i s o n i n g s ys te m, t h e t e ch n i qu e o f a ss em b li ng t h eb r e e c h t o t h e p len um w a s im prov ed t o e l i m i n a t e t h e p o s s i b i l i t y o f damaget o th e O-r ing dur in g assembly. On Apollo 13, t h e p r o p e l l a n t g a s h ad l e a k -ed f rom the gusse t 4 breech assembly, a hole w a s burned th rough the a lu -minum gusset cover plate , and t h e p i l o t p a r a c h u t e m o r t a r c o v e r w a s damaged.S t r u c t u r a l m o d if i ca t io n s t o g u ss e ts 3 and 4 a re d e sc r ib e d i n s e c t i o n A . l . l .

I n t h e

The dock ing r ing separa t ion sys tem w a s m o d i fi e d by a t t a c h i n g t h e s e p-a r a t i o n c ha rg e h o l d e r t o t h e b ackup bars w i t h b o l t s as w e l l as t h e s p r i n gsystem used pre vio usly . This change w a s made t o i n s u r e t h a t t h e c h a rgehol der remained secure upon ac tua t ion o f the pyro techn ic charge a t command

m d u l e / l u n a r m d u l e s e p a r a t i o n .

~ . 1 . 6 C r e w P r o v i s i o n s

A cont ingency water s to rage sys tem w a s ad ded t o p r o v i d e d r i n k i n gw a t e r i n t h e e v e n t t h a t w a te r c o ul d n o t b e o b t a i n e d f rom t h e r e g u l a r p o t a -b l e w a t e r t a n k . The s y st em i n c l ud e d f i v e c o l l a p s i b l e 1 -g a l l on c o n t a i n e r s ,f i l l hose , and d i spen ser va lve . The con ta in ers were 6 -in ch p l a s t i c c ub e scovered with Beta c l o t h . The bags could also be u sed t o s t o r e u r i n e as ab ack up t o t h e waste management sy stem ove rb oa rd dump no zz le s.i l i a r y dump nozz le i n t h e s i d e hatch w a s m o d i f i e d f o r an oxygen tank flowt e s t and could not be used.)

(The aux-

A s ide ha tch window camera br ac ke t w a s added t o p rov ide t h e capa-b i l i t y t o p ho to gr ap h t h r o u gh t h e h a t c h w indow w i t h t h e 7Omm Hasse lb ladcamera.

The i n t r a v e h i c u l a r b oo t b l ad d e r was r e p l a c e d w i th t h e t y p e o f b l a d -der u s ed i n t h e e x t r a v e h i c u l a r b oo t b e ca u se it h a s s u p e r i o r wear qual-i t i e s .

A . l . 7 Disp lays and Cont ro l s

The following changes were made which a ff ec te d crew s ta t i o n d i sp lay sand co nt ro ls . The a l a r m l i m i t for cryogenic hydrogen and oxygen pressurew a s lowered from 220 p s i a t o a p pr o xi m at el y 200 p s i a t o e l im i n a te n u is an c ealarms.ac tan t v a l v e s were ch ang ed t o i n d i c a t e c l o s i n g o f e i t h e r s h u t o f f v a l v e

The f l a g i n d i c a t o r s on p a n e l 3 f o r t h e h y d r o g e n an d oxygen r e -



A-6

i n s t e a d o f c l o s u r e o f b o th v a l v e s , an d v a l v e c l o s u r e w a s ad ded t o t h eca ut io n and warning ma tri x. Oxygen tan k 2 and 3 m a n i f o l d p r e s s u r e w asadded t o th e caut ion and warning system.t o control and monitor oxygen tank 3 were added (hea te r s , pres su re , andq u a n t i t y ) .b a t t e ry end ac t iv a t e the new i s o l a t io n va lve between oxygen tank s 2 an d3 .the c ryogen ic fan motors were de le ted . The c o n t r o l s f o r t h e o xygen t a n kh e a t e r s were c han ged t o p er m i t t h e u se o f o n e, t wo , o r t h r e e h e a t e r e l e -ments a t a t i m e depending upon the need for oxygen flow.

C i r c u i t r y a nd c o n t r o l s n e c e s s a r y

Switches were added t o pane l 278 t o c o nn ec t t h e a u x i l i a r y

C i r c u i t r y a n d - c o n t r o l s (Slg, S20 on panel 2; C/B on panel 226) for

A . 2 LUNAR MODULF:

A . 2 . 1 Structures and Mechanical Systems

S u p p o r t s t r u c t u r e w a s a dd ed t o t h e d e s c e n t s t a g e f o r a t ta c h me n t o ft h e l a s e r r an g in g r e t r o - r e f l e c t o r t o t h e e x t e r i o r o f q u a d r a n t 1 an d a t -t ac hm en t o f t h e l u n a r p o r t a b l e m ag ne to me te r t o t h e e x t e r i o r o f q u a dr a nt 2( s e e s e c t i o n A.4 fo r desc r ip t ion o f exper iment equ ipment ) . A modularequ ipment t r anspor te r w a s a t ta c h e d t o t h e modular equipment stowage as-sembly i n quadran t 4. T h i s s y s t e m ( f i g . A-2) w a s p r ov i de d t o t r a n s p o r tequipment and lunar samples, and t o serve as a mobile workbench duringe x t ra v e h ic u l ar a c t i v i t i e s . The t r a n s p o r t e r w a s c o n s t r u c t e d o f t u b u l a raluminum, weighed 25 pounds, and w a s d e si gn ed t o c a r r y a l o a d of about140 pounds, incl udi ng about 30 pounds of lunar samples.

A . 2 . 2 E l e c t r i c a l P o w e r

Because of an anomaly which occurred on Apollo 1 3 i n which t h e de -

s c e n t b a t t e r i e s e x pe ri en ce d c u r r e n t t r a n s i e n t s and t h e crew noted athumping noise and snowflakes vent ing from quadrant 4 of t h e lu n ar mod-u l e , b o t h t h e a s c e n t and d e s c e n t b a t t e r i e s were modif ied as f o l l o w s :

a. The t o t a l b a t t e r y c o n ta i ne r w a s p o t t e d a n d t h e p o t t i n g o n t o pof t h e b a t t e ry c e l l s w a s improved.

b .i n c o r p o r a t e d .

M an if ol di ng from c e l l t o c e l l a nd t o t h e b a t t e r y c a s e v e n t w a s

c . The o u t s id e a nd i n s i d e s u r f a c e s o f t h e b a t t e r y c o v er were re-v e r s ed s o t h a t t h e r i b s w ere on t h e e x t e r i o r o f t h e b a t t e r y .

I n a d d i t i o n , t h e a s c e n t b a t t e r i e s were m d i f i e d i n t h e f o ll ow in gmanner :



A-0

A.2 .3 I n s t r u m e n t a t i o n

I n s t r u m e n t a t i o n ch an ge s i n t h e a s c e n t p r o p u l s i o n s y st em i n c l u d e d t h ei n s t a l l a t i o n o f a p r e s su r e tr a n s d uc e r i n e ach o f t h e two hel ium tanks i nplace of two t a n k temperkture E m i t sen sor s which had been used f o r meas-u r i n g s t r u c t u r a l t e mp e ra t ur e . The added pre ssu re t ran sd uc ers , i n con-j u n c t i o n w i t h t h e pr im a ry p r e s s u r e t r a n s d u c e r s a l r e a d y p r e s e n t , p r o v i d e d

r ed un da nc y i n m o n i t o ri n g f o r l e a k s . Two temperature lneasurements wereadded t o t h e a s ce n t water t a nk l i n e s t o m o ni to r s t r u c t u r a l t e m p e ra tu r esi n p l ac e of t h e measurements deleted from the ascent propuls ion systemhel ium tanks .

A descen t p ropu ls ion sys tem fue l b a l l valve tem per atur e measurementw a s a dd ed f o r p o s t f l i g h t a n a l y s i s p u r p o s es be c au s e o f c on c er n t h a t damagecould resul t from hea t soak-back i n t o p r op e l l an t l in es a f t e r powered de-s c e n t .

A . 2 . 4 Displeys and Controls

I n t h e a s ce n t p ro p u l s io n s y s te m , t h e i n p u t s from t h e f e e d l i n e i n t e r -f a c e p r e s s u r e s e n s o rs t o t h e c a u t i o n and w ar ni ng s y st em w e r e d i s a b l e d .Because of the low p r e s s u r e at t h e s e s e n s o rs p r i o r t o s ys te m p r e s s u r i z a -t i o n , t h e i r i n p u t s t o t h e c a u t i o n an d w ar ni ng s ys te m w ould h av e maskedth e low-pressure warn ing s i gn a l f rom t h e he l ium tanks at c r i t i c a l p o in t si n t h e m is si on .

B ec au se o f e r r a t i c i n d i c a t i o n s g iv e n by t h e ascen t p ropu ls ion sys temf u e l lo w -l ev e l i n d i c a t o r d u r i n g p r e f l i g h t c h ec ko u t, t h e i n d i c a t o r w a s d i s -a b l e d t o p r e v e n t m a s te r a la rms .

The f o u r r e a c t i o n c o n t r o l sys e m cluster temperature measurementi n p u ts t o t h e caution and warning system were i n h i b i t e d t o p r e ve nt n u is -

ance alarms s i n c e it w a s determined that these measurements w e r e no longerneeded.

An i n c o r r e c t i n d i c a t i o n o f t h e a s c e n t s t a g e g a s e o u s o x y g e n tank 1p r e s s ur e i n p u t t o t h e caut ion and warning system w a s exper ienced dur ingp r e f l i g h t c he ck ou t.system w a s disa b led t o p reven t meaning less alarms.

T h e re f or e , t h e i n p u t t o t h e caut ion and warning

A.2.5 Descent Propuls ion

A n t i - s l o s h b a f f l e s w e r e i n s t a l l e d i n s i d e t h e d e sc en t s t a g e p r o p e l l a n ttanks and t h e diameter o f t h e o u t l e t h o l e s f o r t h e p r o p e l l an t q u a n t i t y gag-

ing sys tem sensors w a s reduced from 5/ 8 i n ch t o 0 . 2 i n c h t o m in im iz e p re -mature low prope l lan t l eve l i n d i c a t i o n s due t o s l o s h i n g s uc h as had beenexperienced on Apollo 11 an d 12.

L i



A-9

I t w a s determined by t e s t t h a t t h e d e s ce n t p r o p u l s io n s y s te m f u e llu na r dump va lve would c l os e under l i q u i d f low con d i t ion s when i n s t a l l e di n t h e normal f low dir ec t i on and could not be reopened.d et er mi ne d t h a t , by r e v e r s i n g t h e v a lv e and i n s t a l l i n g an o r i f i c e u p s t r e a mo f t h e v a l v e, it would remain open under all e x p e c t e d l i q u i d f l o w c o n d i -t i o n s .and th e c ryogen ic he l ium tank under zero-g cond i t ions , th e va l ve w a s r e -i n s t a l l e d i n t h e r e v e r s e fl ow d i r e c ti o n .

I t w a s f u r t h e r

Because of a p o s s i b l e r eq ui re me nt t o v e nt t h e p r o p e l l a n t tanks

The p rope l l an t quan t i ty gag ing sys tem sensors w e r e m o di fi ed t o i n -c lude a =tal s p l i t r i n g be tw ee n t h e e l e c t r o n i c s pa ck ag e c o v er a nd t h es e n s o r f l a n g e s . T h i s i n c r e a se d t h e c l e a r a n c e b etw ee n t h e e l e c t r o n i c spackage and co v e r t o p r ec l u de t h e p o s s i b i l i t y o f c r u s h ed w i r e s d ue t oimproper c learance.

A.2.6 Ascent Propulsion

To improve the s e a l f o r t h e f ou r- bo lt f la n ge d j o i n t b etw een t h e f i l l -

Teflon O-rings were useda n d- d ra i n l i n e s and t h e main f e e d l i n e s i n t h e a s c e n t p r o p u l si o n s y st e m,O-rings were u se d i n p la c e o f i n j e c t e d s e a l a n t s .i n t h e o x i d i z e r l i n e s , a nd b u t y l r u bb e r O- ri ng s w ere u s ed i n t h e f u e l l i n e s .

A.2.7 Environmental Control

A muffler w a s added i n t h e l i n e a t t h e o u t l e t o f t h e w a te r -g l yc o lpump assembly t o reduce th e pump noise t ran sm it t ed t o th e c abin throught h e w a t er - gl y c ol l i n e s . The reg u la to r band o f th e h igh-pressure oxygenassembly w a s s h i f t e d t o i n c r ea s e t h e reg u la ted p ress ure from approx imate ly950 p s i g t o 990 p s i g , p r o v i d i n g a h i g h e r re c h ar g e p r e ss u r e f o r t h e p o r t -ab le l i f e support system and, t h u s , i n c r e a s i n g i t s o p e r a t i n g t im e f o r

e x t r a v e h i c u l a r a c t i v i t i e s .

~ . 2 . 8 Crew Provisions

The f l ex i b le - typ e con ta i ne r a ssembly p rev ious l y used fo r s towage i nt h e l e f t hand s ide o f the lunar module cabin w a s r e p l a c e d w i t h a metalmodular ized container which w a s p ac ke d b e f o r e b e i n g p la c e d i n t o t h e l u n a rmodule.

Re tu rn s towage cap ab i l i ty was p rov ided f o r two add i t i on a l l un ar rocksample bags .



A-10

A .3 EmVEHICULAR MOBILITY UNIT

The thi gh convolute of t he pr ess ur e garment assembly w a s r e i n f o r c e dt o d e c r e a s e b la d d e r a b r a s i o n wh ic h h ad b ee n n ot e d on t r a i n i n g s u i t s .A l so , t h e c r o t c h p u l l e y a nd c a b l e r e s t r a i n t system w a s r e c o n f i g u r e d t op r o v id e f o r h e a v i e r l o a d s .

The portable l i f e support system w a s modif ied as f o l l o w s . A carbond i o x i d e s e n s o r w a s added and a ss o ci at ed changes were made t o pro videt e l e m e t r y o f c ar bo n d i o xi d e p a r t i a l p r e s s u r e i n t h e p r e s s u r e garm ent as-sembly. I n a d d i t i o n , a n o r i f i c e w a s a dd ed t o t h e f e e dw a t er t r a n s d u c e rt o p re v e nt f r e e z i n g of water t r a p p e d w i t h i n t h e t r a n s d u c e r h o u s i n g, w hic hwould otherwise resu l t i n in co r r ec t r ead in gs . The oxygen purge sys temw a s modi f ied by th e de le t ion o f th e oxygen hea te r sys tem because th e oxy-gen d o e s n o t r e q u i r e p r e h e a t i n g t o be c o m p at i bl e w i t h crew requirements .

A new piece of equipment, t h e buddy secondary l i f e support system,was prov ided as a means of sh ar in g cool ing water f rom one portable l i f e

support system by both crewmen i n th e event t h a t one c oo l in g systembecame ino per a t iv e . The u n i t con s i s t s o f a w at er u m b i l ic a l , r e s t r a i n th o o k s a n d t e t h e r l i n e , a n d a water- f low d i v i de r assembly.

A . 4 EXPERIMENT EQUIPMENT

Table A -I l i s t s th e experiment equipment c ar r i e d on Apollo 14,i d e n t i f i e s t h e s to wag e l o c a t i o n s o f t h e e qu ip men t i n t h e l u n a r m odu le,a n d r e f e r e n c e s a p p l i c a b l e A p o l l o m i s s i o n r e p o r t s i f equipment has beendescr ibed p rev ious l y. Equipment no t ca r r i e d on p rev ious miss ions i s de-sc r ib ed in th e fo l lo wing paragraphs . The two subpackages of th e Apol lo

lunar sur fac e exper iments package are shown i n f i g u r e s A-3 an d A-4.

A . 4.1 Active Seismic Experiment

The act ive seismic experiment acquires i n fo r m a ti o n t o h e l p de te r-mine t h e p h y s i c a l p r o p e r t i e s o f l u n a r s u r f a c e an d s u b s u r fa c e materialsu s i n g a r t i f i c i a l l y p ro du ce d s e i s m ic waves.

The experiment equ ipment co ns i s t s o f t h re e i d e n t i c a l geophones, athumper, a mortar package, a c e n t r a l e l e c t r o n i c s as se mb ly, an d i n t e r -conn ect ing cab l ing . The geophones ar e e le ctro mag net ic dev ices whichwere deployed on t h e l u n a r s u r f a c e t o t r a n s l a t e su rf ac e move-nt i n t oe l e c t r i c a l s i g n a l s . The th um pe r i s a d e v i c e t h a t was operated by one of



A - l l

N l V N N ( UN

* -t

-

U

Y

U

n



A- 12

NASA-S-71-1709

Slde

F i g u r e A-3.- Experiment subpackage no. 1.NASA-S-71-1110

n Pa lk l and r.dioiro(g=

f

IW

Figure A-4.- Experiment subpackage no. 2 .



A-13

t h e crewmen t prov ide se i smi , T hh o l d i n g t h e thumper a g a i n s t t h e l u n a r surface

i g n a l s were g e n e r a t e d b ya t v a r i o u s l o c a t i o n s a l o n g

t h e l i n e o f t h e geophones and f i r i n g e x p lo s iv e i n i t i a t o r s l o c a t e d i n t h ebas e of th e thumper. The mortar package co n si s t s of a mortar box assem-b l y a n d a grenade l aunch tube assembly. The m o r t a r b o x e l e c t r o n i c s p r o -v id e f o r th e a rming and f i r in g o f rock e t motors which w i l l l a u n c h f o u rhig h-e xp los ive gren ades from th e laun ch tu b e assembly upon remote command.The monitor package i s d es ig ne d t o l a u nc h t h e g re na de s t o d i s t a n c e s o f5000, 3000, 1000, and 500 f ee t . Si gn als sensed by t h e geophones are t r a n s -m i t t e d t o e ar th - ba se d r e c o r d e rs .

A. 4.2 L u n a r Portable Magnetometer Experiment

The lunar portable magnetometer w a s u se d t o measure t h e m a gn e ti cf i e l d a t t w o l o c a t i o n s a l o n g a t raverse on t h e l u n a r s u r f a c e . The meas-urements w i l l be u s ed t o d e te r mi n e t h e l o c a t i o n , s t reng th and d imens ionso f . t h e s o u r c e , a n d , i n t u r n , t o s t u d y b o t h l o c a l a n d whole-moon g eo lo g -i c a l s t r u c t ur e .

The experiment equipment co n s is ts of a sensor head co n ta in in g t h r e eo r t h o g o n a l s i n g l e - a x i s f l u x g a t e s e n s o r a ss e m b l i es , an e l e c t r o n i c s an ddata di sp lay package, and a t r i p o d .by E r c u r y c e l l s .high and low w t e r ranges (?lo0 gammas and +50 gammas).c o n s i s t s o f t h r e e meters, one fo r each axis .

The e l e c t r o n i c s p a c k a g e i s poweredThe package has an on-off switc h and a s wi tc h t o s e l e c t

The da ta d i s p l a y

A .5 MASS PROPERTIES

S p a c e c r a f t mass p r o p e r ti e s f o r t h e Apollo 1 4 mission a re summarizedi n t a b l e A-11. These da ta r e p r e s e n t t h e c o n d i t i o n s as determined frompos t f l igh t ana lyses o f expendab le load ings and usage dur ing t h e f l i g h t .Va r i a t i o n s i n command an d s e r v i c e module and lunar module mass p r o p e r t i e sa r e d e t e r mi n e d f o r ea c h s i g n i f i c a n t m i ss i o n p h as e from l i f t - o f f t h r ou g hland ing . Expendables usage are based on rep or ted rea l- t i me and po st-f l i g h t data as p r e s e n t e d i n o t h e r s e c t i o n s o f t h i s r e p o r t . The weightsand center -of-g ravi ty of th e in di vi du al modules (command, se rv ic e, a sce nts t a g e , a nd d e s ce n t s t a g e ) were me asu red p r i o r t o f l i g h t a nd i n e r t i a v a l u e sc a l c u l a t e d . ' A l l changes incorporated a f t e r t h e a c t u a l w e i gh i ng were mon-i t o r e d , and t h e mass proper t i es were upda ted .



.

A-14

TABLE A-11.- MASS PROPERTIES

ll m.3

n2 083.6

61 388.033 8 9 . 2

98 037.2

91 901.)

91 104.1

97 033.1

n 168.8

10 162.3

35 996.3

35 6lo.4

3h i25:55 181.3

39 906.839 903.9

9 596.3

3L 554.4

24 6Y.9

21 375.0

11 659.912 115.1

12 m3.5

12 13o.t

ll 4 8 l . i-

841.51207.6

934.4l236.1

lo38.2

loss.

1038.9

lo39 o

l o b . 9

1086 .b

9b5.0

9L5.2

9 u . 5U 6 5 . 2

918.2916.3

947.5

947.3

975.3

975.1

906.41038.2

1039.2

1031.6

l o n . 9-

-2. 22 .4

C.0-. 2

2. 6

2. 6

2. 6

2. 6

1. 3

1. 3

2.2

2.2

1.94.6

2. 31. 9

2 O

2.0

-1.6

-1.6

-3.1-. 2

- 2

-.l

-.l-IAm

33 651.9

34 125.9

3b 067.8

16 3ll .T

M 779.8

5 911.8

5 M 0 . l

5 781.3

5 301.6

184.9 - . 3

186.0 - . 3

185.9 - .3

213.6 -.6

2b3.9 .2

251.0 . 3

256.8 .I

256.7 .4

258.2 .2

3. 14.0

6.b- . 3

4 .1

4. 1

b.0

b. 0

2 . 1

2 . 1

5.8

5. 8

6. 0-2.3

b . 84. 9

5.7

5.7

1. 4

1 .5

9 .45 . 1

5.6

5.8

4. 8-

68 9 167 445

25122 533

51 on56969

56 567

56499

43 395

b3 812

19 725

19 b94

18 6623 3b7

22 09021 910

18 74L

18 7 P

13 592

13 386

1 b595 897

5 8 9 0

5 6 8 6

5 9 1-

1 1 8 3 929 1 1 % 165T24926 12l209

. nos 1 9 5 3 l2b 3 9 24 9 M

531 5n 540 sob

5 3 ~ s ~ in535 156 539 02b

5% 582 5 3 8 *

410 855 b i i 3 U

bo2639 bo8b%

51 161 62 b5a

51 032 62 2bb

56 59 h 6 1 2182 291 2 723

913 Ub 95 8l o 5 7 5 1 U O 659

5 1 0 3 l 61660

56 553 61 lb

b1 585 l11 382

41 3 4b b1 l90

l2908 1 3 2 8 05 281 4 163

5 - l I162

4 6 f b L Lo3

4 45 1 b 083

-2b 925

26 U P

26 01 8

13 629

3 Lo8

2 908

2 8 9 9

2 ma2 m

25 034

26073

25 965

is059

5 95b

2 14b

2 123

2 055

2 0%

Lo585759

-1181-466

- 8 1 4

-R?P

- 8 2 3

-mu-5576

-M&

-urn

-1%3

-18l2-UT

-1341-zoo9

- i n 2

-1146

14 2

1 1

-4l8bb

bb

Lb

35-

l o b

M5

M5

-31b

3l 8

Y l l

398

6

5

6

8

3-



B-1

APPENDIX B - SPACECRAFT HISTORIES

The h i s to ry of command and service module, (CSM 11 0 ) o p e r a t i o n s a tt h e m a n u f a c tu r e r ' s f a c i l i t y , Downey, C a l i f o r n i a , i s s h a m i n f i gu re B-1,an d t h e o p e r a t i o n s a t Kennedy Space Cen ter, F lo r i da , i n f igu re B-2.

The h i s to ry of t h e lunar module (LM-8) a t t h e m a n u fa c tu r e r' s f a c i l -i t y, B e t h p a g e , New York, i s shown i n f igu re B-3, a n d t h e o p e r a t i o n s a tKennedy Space Center, Florida, i n f i g u r e B-4.

NASA-S-71-1711

1969

F e b u r y I Yrch I April I May I June I July 1 August I eptember I October November

-Individual systems checkout

lntepratcd systems test

=Data review

-odifications and retest

m ~ p o 1 1 0 0 and 11 mission supportm m I

rn1 emate

installations and checkout = I IWeight and balance IPreshipnent inspection I

Preparation fa shipment and ship

Command module

Final installations and checkout -reshipnent inspection 1Preparation for shipment and ship-[ervice module

Figure B-1.- Checkout flow f o r Command and se r v i c e modules a tc o n t r a c t o r ' f a c i l i t y .



B-2

NASA -S-71 -1712

1970 1 1971

April I May 1 June I July IAugust ISSemberl October INovember1 DecemberJanuary

' Waterlglycol sp il l clean up and equipment replacement (see note2)

-Equipment inst alla tion and retest

8Altitude chamber tests

Cryogenic and r et ur n enhancement modifications and retest-Jotes:

Spacecraflllaunch vehicle as se mb ly l

Move space vehicle to launc h complex

Sector 4 cryogenic shelf i nstal latio n1

Space vehicle systems and flight readiness tests-

1- Commandand service modulesdelivered to Kennedy SpaceCenter on November 19, 1969

2. Spil l resu lted from hole accidentallypunched in cold plate d uri ng install-ation of new in erti al measurementunit on April14, 1970

Spacecraft propulsion leak checks and propellant loading1-ountdown dem ons tration tes

Countdown(

Launch '1

F i g u r e 3-2.- Command and s e r v i c e module checkout h is to r y a tKennedy Space Center.

NASA-S-?I -1113

I 1969 IJanuary IFebruary1 March I April I May 1 June 1 July I August ISeptemberl October INovember

1Manuacurng cold flow I. and preparations lor subsystems testing

-Mated subsystems testing

IManufacturing, cold (low n, and electrical preparations forfinal engineering and evaluation acceptance test

Ihed crew compartment 111and function checks

Final engineering and evaluation acceptance test 1I

Cold Ilarvm and modifications=

Mated retest-reparation or shipment an d ship=

Figure B - 3 . - Checkout f l o w f o r lunar modulea t c o n t r a c t o r s f a c i l i t y .

L

r



B- 3

1 9 7 0

June Jul y DecemberI

NASA-S-7 1-1 14

1971

January

Ascent stage delivered to KennedySpace Center on November 21, 1969;descent stage delivered on November

24, 1969

Countdown1Launch7

Figure B-4.- Lunar module checkout history a tKennedy Space Center.



c-1

APPENDIX C - POSTF'LIGHT TESTING

The command module a r r i v e d at t h e Lunar Receiving Laboratory, Houston,Texas, on February 22, 1971, a f i e r r e a c t i o n c o n t r o l s ys te m d e a c t i v a t io nand p y r o te c h n i c s a f i n g i n H a w a i i . A t t h e e nd of t h e q u a r a n t i n e p e r i o d ,

the crew equipment w a s removed and t h e command module w a s s h i p p e d t o t h ec o n t r a c t o r' s f a c i l i t y i n D m e y , C a l i f o rn i a , on A p r i l 8. P o s t f l i g h t t e s t -in g and in sp ec ti on of t h e command module f o r eva lu at io n of t h e i n f l i g h tp er fo rm an ce a nd i n v e s t i g a t i o n o f t h e f l i g h t i r r e g u l a r i t i e s wer e co nd uc te da t t h e c o n t r a c t o r ' s an d v e nd o r' s f a c i l i t i e s an d at the Manned SpacecraftCenter i n accordance with approved Apollo Spacecraf t Hardware U t i l i z a t i o nRequests ( A S H U R ' s ) . The tes t s pe r fo rmed as a r e s u l t o f i n f l i g h t p ro blem sare d e sc r ib e d i n t a b l e C- I and d i scussed i n t h e appropriate systems per-formance sect ions of t h i s r e p o r t .poses i n accordance w i t h o t h e r ASHUR's an d t h e b a s i c c o n t r a c t are n o tinc luded .

Tests be ing conduc ted fo r o ther pur-



c-3

d0uI

I

HIu

Y2I 3



D- 1

APPENDIX D - DATA AVAILABILITY

Tables D-I and D-I1 are summasies o f t h e .d a ta made a v a i l a b l e f o rsystems performance analyses and anomaly invest igat ions.t h e d a t a from t h e command and se rv ic e modules, and t a b l e D-11, t h e l u n a r

m d u l e .s ta tus l i s t i n g o f a l l mission data i n t h e C e n t r a l M e tr ic Data F i l e ,b u i l d i n g 1 2 , MSC, sh ou ld be c on su lt ed .

Table D-I l i s t s

F o r a d d i t i o n a l i n fo r m at io n r e g a rd i n g d a t a a v a i l a b i l i t y , t h e



D-2

TABLE D-I.- COMMANDAND SERVICE MOWLE DATA AVAILABILITY

Tim. h r : d n-m a

-04:OO00 oo00:02w:4001:2802:2502 : 903:0503:lb03:k704:4505:43c 6 : b07:180 7 : b08:3710 : 6lo:%14:5115:1016:0717:0718:0719:0820:0722:4923:0823:%27.:0429 : 730:W30:W30 : 031:Ol

-

34:w34:5439:wb2:53U : b 81 9 : a5O:IO55:Ol

58:

859:W59:w6Q:5763:W64:w65:4967:2867:1969:4569:4970 : 571:497S:lO76:2576 : O76:5778:207 9 : uQ:15Q:bb&:02-

-l b

w:3000 : 000:1403:1501:4L02 : 403:b912:oo06:21Ob.:h705 : 506:450 7 : l llo:%08 : 910:3514 : 513:b617:5315: lh16:2019:W22:b923:0921:0926 : 624:0924 :5030:5930:3731:w30:3731:W31 3135:283 0 5 7b2:531 7 : W48:2651 : 95b:W5 8 : U

625161:oo61:W61:1967:m66:W66:4969:1@69:M70:5171: 975:&M : M78:b277:2577:oC77 :o;78:bi&:SI&:04&:Oh8Q:X

-

L. L

Bandpa88plota

or tam

XX. x

XXX

XXXXXXXXXXXX

X

X

XX

XX

XXX

XXX

XX

X

X

X

XX

X

XX

XX

? -L

Bilevela

xXXXXX

XXXXXXXXXXX 'XX

X

X

XX

XX

XXX

XXX

X

XX

X

X

XX

XXXX

XX

C a p u t r rvordn

X

X

XX

XXXXXX

X

X

X

X

X

XX

XXX

XXX

XX

X

X

X

X

X

XX

XX

XX

XX

XX

X

XX

XX

X

XX

X

1Y 1 - - L I

. X

X

XX

XXX

X

X

XX

XX

XX

X

X

X

XX

X

X

X

XX

X

X

X

X

XX

X

L

I "

L i L



D-3

TABLE D-I . - COMMAND ANDSEXVICE MODULEDATA AVAILABILITY - Continued

XI X

Tim. b r : d n

~~

&:1482:s

83:02&:a385:lO%:lo86:lO88:2588:s&:b29o:OOW : M91:OO9b:lO9b;59%:0197:55'98:Ob

.98:1998:b98:52W:b999:52

102:OO102:b2103:3810b:23

.104:47105:Y106:kh107:25108:42108:42110:Ll111:20111 : 4116:%?118: 1U9:02120:02l20:55

l22:31l23:15l25:15126:28121:15129:lO129:s129:b21Y:oo131:OO1Y:12131:33133:2913&:22135:08135:09136:19136:20139:05139:05i41:kolb2:lO112:lb

- I 'Ib~

82:blr83:43

8l:ll85:U86:0990:508 6 5 3&:35&:3b90:23

101:oo91:289b:5995:1898:bo97:u98:2098:U99:05

102:b298:55

100:591OO:Ob102:5b108:3610b:25lO4:47105:30106:&7lD8:42108:43ll0:42.lO9:30ll1:36112:08118: 37U8:%?122 1l20:32120:3212253

l26:26121:&9126:30l29:38128:25129:bO13o:bo130:lO1P:oo131:35135:58132:3b13b:24135:lO135:12136:20138:u138:lL1k3:49139:b5142:18lh3:OO146:05

B M & p u Op l o t .

or t a r

X

X

x

XXX

X

X

X

X

XXX

X

X

X

X

X

xX

Bilerals

XX

XXXXX

XX

XXXXXX

XX

X

XXXXXXXXXXX

XXX

X

X

X

XX

XXX

XXX

SpecialP l o t .

or t a r

XX

X

XX

X

X

X

X

X

X

Special

' x

X

X

XX



D-4

TA B U D-I.- COMMAND AND SERVICE MODULEDATA AVAILABILITi - Concluded

RurgeB.ndpass Oscillo-

plots Bilevelr graphor t a b s records

XXXX

XXXX

XX

XXX

XXX

X

X

XXXXXXXXXXX

XX

X

Time.

From

143:31l b 4 : 1 2145:13146:05146:56148:lO151:lk154:56159 : 0 8162:CO162:58165:17166:OO166:18166:47167:OO161:23168:18169:OO169 : 1170:57171:05174:Ol175:09 .

175 : 8179:05119:50183:05187:02187:25190 : 5419&:49199:06203:U207:06210:b8211:ll21b:17

215:Ob2 l 5 : 0 8215:08215:31215:31

XXXX

XXXX

XX

XXX

XXX

X

X

X

XXXXXXXXX

XX

X

hr:min

To

1 4 h : l O145:08146:14150:54147:551&8:50151:52158:57162 : 61 6 4 : ~166:07166:18176:OO167:18

. 170:53168:18168:031 6 9 : u169:20170 : 8174:4017b:Ob175:59178:56178: 52182:52184:OO186:52188:62190:54194 : 9198:46203:02206:50210:522 U : U2l4:L92l5:06

215:b621S:b3215:bb21S:51216:oi

XXXXXXXXX

XX

X

X

XXXXXXX

X

XXXXXX

X

XX

X

Special

I

Specialproer-



D-5

Time. hr:aia-From

-01:OO61 061 : 277:31

101 A 5101:16102 2103:3810L:lL101:23105:31106:05106:bb107:25107:b2loa&108:b3109:bO

110 : 1112:20112:25113:02114:sll5:02119 :21=:15122 ll22:51126:28126:b3l28:39129:2b129:3T130:3513l:121 P : Y133:b

135:U136:19137:08137:19138:M139:05139:39110:s1bO : 9111 :lo111 : 5111:C9112:11112:59lb3:2l113:&111:58115 05lb5:l2lh6:oblb6 : 5lbT:l2-

T A B U D - 11 . - LUNAR MODULE DATA AVAI LAB ILIT Y

-To

-02:oo62:1562:15T8:lO

102 0102:b2106:kblOb:25108:51101 : '1106 : 1M : 1 Tlo8 2107:15108:b3U0:15lo9:ooll0:36

ll1 : b111:s113:lOU5:03U9:03u 9 : m=:1512253126:28M : 1 5m : 3 8l29:bOm:Low:36130:38131:s135:58U 3 : S135:lT

137:lo136:b6138:OT138:M139:Wlb3:191bl:Wl&:W1 h : W111: 8111:slb2:18lb6:05113:slbb :l6lbb :Ollb5:15lb5:15lb6:lk117:W1b7 : 0lbT:b2

-

-

R.n(F8 t . t i o n

ALDGHS K

omOD B

m n

m nm nm n

.om

aD8aD8omlrsn

om0

tenamI S K

I B K

1p)KMADI6n

WID

am

m n

m n

m nomm namaD8omanPDBlrscanamaml p lK

mKWIDIUD

IUDWIDWIDIYDIUDIUD

IUDIU DIUDIUDIUDIUDIan

-

lrsn

m n

lrsn

XXXXXXXXX

XXXXX

X

X

X

X

X

X

X

XXX

XXX

X

X

XXXX

X

XXXX

X

XXXXXXXXXXXX

X

X

X

X

X

X

X

XXX

XXX

X

X

XXXX

X

XX

XX

X

XXXXXXXXX

X

X

X

X

X

X

X

XX

X

XXXX

XXXX

X

X

X

XXX

XX

X

XX

B n u hrecorda

X

XX

X

XXX

XX

X

X

X

X

X

X

XXX

XX

X

XXX

X

XXX

XXX

XX

XX

8p.ci.lplot8

or t a r

X

X

X

X

XX

X

X

X

X

X

XXX

XXXX

X

XX

X

X

XXX

XX

X

X

XX

X



E-2

TABU E-I .- MISSION REPORT SUPPLEMENTS

P u b l i c a t i o nd a t e s a t usi t l eupplement

number

Apollo 71 Tr aje cto ry Rec ons truc tion and Analy sis May 19692 Communication System Perfo rman ce Ju n e 19693 Guidance, Navigation, and Control System

4 Reactio n Co ntr ol System Performance August 19695 Cancelled6 E n t r y P o s t f l i g h t A n a l y s i s

November 1969Performan ce An al y s i s

December 1969

Apollo 8

1 . Tr aje cto ry Recon structio n and Analy sis December 19692 Guidance Na vi ga tio n and Co nt ro l System November 1969

3

4 Serv ice Propu ls ion System Fin al Fl ig ht September 1970

5 Cancelled6 Analysis of Apollo 8 Pho togr aphy and December 1969

December 1969

Performance Analysis

Reaction Control System

Evalua t ion

Performance of Command an d S e r v i c e Module March 1970

Visual Observat ionsEnt ry Pos t f l igh t Ana lys i s

5

6

7

8

9101112

Apollo 9

Tra jec to ry Recons t ruc t ion and AnalysisCommand and Se r v i c e Module G ui da nc e, Navi-

g a t i o n s and Control System PerformanceLunar Module Abort Guidance System Perform-

ance AnalysisPerformance o f Command and Service Module

Reaction Control SystemServ ice Propuls ion Sys tem Fina l F l igh t

Evaluat ionPerformance of Lunar Module Reaction Control

SystemAscen t Propuls ion Sys tem Fina l F l igh t

Eval ua t i onDescent Propuls ion System Final Fl ight

Evaluat ionCancelledSt rok in g Tes t Ana lys isCammunications System PerformanceEnt ry P o s t f l i g h t A n a l y s i s

~~ ~

November 1969November 1969

November 1969

Apr i l 1970

December 1969

August 1970

December 1969

September 197(

December 1969December 1969December 1969

L



E-3

TABLE E-1.- MISSION REPORT SUPPLEMENTS - Continued

T i t l epplementnumber

Pub li c a t i o ndate / s t a t us

12

3

4

5

6

7

09

10ll

12

3

4

5

6

7

0

91011

Tr a j e c t o r y R e c o ns t r uc t io n an d AnalysisGuidance, Navigat ion, and Control System

Per for man ce of Command and S e r v i c e Module

S e r v i c e P r o p u l s i o n S y s t e m F i n a l F l i g h t

Performance o f Lunar Module Reaction Control

Ascen t Propuls ion Sys tem Fina l F l igh t

Descen t Propuls ion Sys tem Fina l F l igh t

Cancel ledAnalys i s of Apollo 10 Photography and Visual

E n t ry P o s t f l i g h t A n a ly si sComunications System Performance


Reaction Control System

Evalua t ion

System

Evalua t ion

Eva lua t i on

Ob s e rvat i on s

Apollo 11

Tr a j e c t o r y R e c o ns t ru c t io n an d AnalysisGuidance, Nav igatio n, and Con trol System

Performance of Command and S e r v i c e Module

S e r v i c e P r o p u l s i o n S y s t e m F i n a l F l i g h t

Performance of Lunar Module Reaction Control

Ascen t Propuls ion Sys tem Fina l F l igh t. Evalua t ionDescent Propuls ion Sys tem Fina l F l ig h t

Eva lua t ionCancel led

Apollo 11 Pre l iminary Sc ience Repor tCommunications System PerformanceEn t 4 Pos t U g h t Analy s i s


React ion Control System

Evalua t ion

Sy s e m

March 1970December 1969

Augus t 19 70

September 1970

Augus t 19 70

January 1970

January 1970

I n p u b l i c at i o nas SP-232

December 1969December 1969

May 1970September 1970

Review

October 1970

Revi e w

September 197C

September 197C

December1969January 1970

A p r i l 1 9 7 0



E- 4

TABLE E-1.- MISSION REPOR" SUPPLEMENTS - Concluded

P u b l i c a t i o nd a t e s t a t usi t l eupplement

number

Apollo 1 2

Tra jec to ry Recons t ruc t ion and Ana lys i sGuidance, Navigation, and Control System

Serv ice Propuls ion Sys tem Fina l F l igh t

Ascent Propuls ion System Final Fl ight

Descent Propuls ion System Final Fl ight

Apollo 1 2 Prel iminary Science ReportL an ding S i t e S e l e c t i o n P r o c e s s e s


Evaluat ion

Evaluat i on

Evaluat ion

September 1970September 1970

P r e p a r a t i o n



J u l y 1 9 7 0F i n a l r e v i e w

Apollo 1 3I

Guidance, Navigation, and Control System

Descen t Propuls ion Sys tem Fina l F l igh t

Entry Pos t l i gh t Analy s i s


Evaluat i on

September 1970

October 1970

Cancel led

Apollo 14

Guidance, Navigation , and Control System

Cryogenic Storage Sys em Performance

Serv ice Propuls ion Sys tem Fina l F l igh t

Ascen t Propuls ion Sys tem Fina l F l igh t

Des cen t Propuls ion Sys em Fin a l F l i gh t

Apollo 14 Prel iminary Science ReportA n a l y s i s of In f l igh t Demons t ra t ionsAtmospheric El ec tr ic i t y Experiments on


Analysis

Evaluat ion

Evaluat ion

Ev a lu a t i on

Apollo 13 an d 1 4 Launches






P r e p a r a t i o nP r e p a r a t i o nPr e p a r a t i on

L -



R- 1

1. Manned Sp ac ec ra ft Ce nt er : Apollo 1 2 Miss ion Re po rt. MSC-01855.March 1970.

2. Manned Space craf t C enter : Apollo 12 Pre l im ina ry Science Report .NASA SP-235. Ju ly 1970 .

3 . Manned Sp ac ec ra ft Cen ter : Apollo 13 Mi ssi on Re po rt . MSC-02680.September 1970.

4. Manned Sp ac ec ra ft Cen ter: Apollo 11 Pre l iminary Sc ience Repor t .NASA SP-214. December 1969.

5. Marsha l l Space F l ig h t Cen te r: Sa tu rn V Launch Vehicle Fl ightMPR-SAT-FE-71-1.va lu at io n Repor t AS-509 Apollo 1 4 Mission.

A p r i l 1971.

6. Manned Space cra ft Cente r: Apollo 1 0 and I l Anomaly Report No. 1 -F u e l C e l l Cm'denser Exit Tempera tu re Osc i l l a t ions .A p r i l 1 9 7 0 .

MSC-02426.

7. N A S A Headquarters : Apollo Fl ig ht Mission Assignments. OmF M-DMA 500-11 (SE 010-000-1) October 1969.

8. Manned Sp ac ec ra ft Ce nte r: Mission Requirem ents, H-1 Type Mission(Lun ar Landinp;) . SPD9-R-056. June 9, 1970.

9. Goddard Space Fl ig h t Cen ter : Pos t Miss ion Ana lys i s Repor t.

S-832-71-175.

10 . Manned Spa cecra ft Ce nte r: Ra dio met ric Temperature Measurement ofApol lo 14 /Sa turn V Exhaust.C o n tr ac t NAS9-10950. A p r i l 1971.

Lockheed El ec tr o ni cs Company (1 ~ 2 0 6 1 ) .

NASA - SC



R - 2

MISS ION REPORTQUESTIONNAIRE

Mission Reports are prepared as an overall summary of specific Apollo flightresults, with supplemental reports and separate anomaly reports providing theengineering detail in selected areas.questionnaire so that our evaluation and reporting service to our readership mightbe improved.

Would you kindly complete this one-page

apollo 14 mission report

Documents