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NA TIO NA L AERONAUTICS AN D SPACE ADM INISTRATION
WO 2-4155
N E W S WASHINGTON,D .C. 20546
T E L S
W O
3-6525
FOR
RELEASE:
THURSDAY A.M.
J u l y 1 5 , 1 9 7 1
RELEASE NO: 71-119K
P
R
E
S
S
K
I
T
PROJECT:
APOLLO 1 5
( T o be launched no
e a r l i e r t h an
J u l y 2 6 )
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NE
W S
NA TION AL AERONAUTICS A ND SPACE AD MINISTRA TION
(m2) 962-4155
WASHINGT0N.D.C.
20546
~ L S :
2132)
63-6925
Ken AtChison/Howard Allaway FOR
RELEASE:
THURSDAY, A.M.
(Phone 2 0 2 / 9 6 2 - 0 6 6 6 ) J u l y 15 , 1 9 7 1
RELEASE
NO: 71-119
APOLLO
1 5
LAUNCH
J U L Y 2 6
The 12-day Apollo 1 5 miss io n , schedu led fo r l aunch on
J u l y
26
t o
c a r r y o u t t h e f o u r t h U n i t e d
St a t e s
manned eyplora-
t i o n o f the Moon,
w i l l :
- Double t h e
t i m e
an d ex t en d t en f o l d the r ang e o f l u n a r
s u r f a c e e x p l o r a t i o n as compared with e a r l i e r miss ions ;
-
D e p l o y t h e t h i r d i n a n etw ork o f au t oma t ic s c i e n t i f i c
s t a t i o n s ;
-
Conduct
a
new group of expe rime nts i n
l u n a r
o r b i t ; and
-
R etu rn t o Ea r t h
a
v a r i e t y o f lunar rock and s o i l samples .
S c i e n t i s t s e x pe c t t h e r e s u l t s
w i l l
g r e a t l y i n c r e a s e m an's
knowledge both of th e Moon's h is to ry and composi t ion and of t h e
ev olu t io n and dynamic in te ra c t i o n of t h e Sun-Ear th system.
This
i s
so b ecau se t h e
dry a i r l e s s ,
l i f e l e s s Moon s t i l l
b e a r s r e c o r d s
of
s o l a r r a d i a t i o n and
the
e a r l y y e a rs
of
s o l a r
syst em h i s t o r y t h a t have been e ra sed from Ear th . Observa tions
of current lunar events a lso may in cr ea se unders tanding of
similar processes on E a r t h ,
such as ear thquakes .
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b
.
The Apoll
- 2 -
15 lunar module w i l l mak i t s d e s c e n t o v e r
th e Apennine peaks, one of
the
h ig h es t mountain ranges on
t h e Moon,
t o
l a n d n e ar t h e r i m of t h e canyon-l ike Hadley
R i l l e . From th i s Hadley-Apennine lu n ar ba se , between th e
mountain range and the r i l l e , Commander David R. S co t t and
Lunar Module P i l o t James B. I r w i n
w i l l
e x p l o r e
several
k i l ome t e r s from t he l un a r module , d r i v i ng an e lec t r i c -powered
l u n a r r ov in g v e h ic l e f o r t h e f i r s t
t i m e
on t h e Moon.
S c o t t and Irw i n
w i l l
leave t h e l u n a r module f o r t h r e e
e x p l o r a t i o n p e r i o d s t o em place s c i e n t i f i c e xp e ri m en ts on t h e
l u n a r s u r f a c e an d t o make d e t a i l e d g e o l o g i c i n v e s t i g a t i o n s o f
fo rma ti ons i n t h e A pennine fo o t h i l l s , a l ong t h e Ha dle y Ri l le
r i m , and t o o t h e r g e o lo g ic s t r u c t u r e s .
The
th re e prev iou s manned l an ding s w e r e made by Apollo
11
a t
T r a n q u i l l i t y B a s e , Apol lo 1 2 i n the O c e a n of Storms and
Apol lo 1 4 a t Fra Mauro.
The Apollo 1 5 m i s s i o n s h o u l d g r e a t l y i n c r e a s e the
s c i e n t i f i c
r e t u r n when compared t o
ea r l i e r exploration
missions.
Extens ive geologica l sampl ing and survey of the Hadley-Apennine
re gi on of t h e Moon w i l l be enhanced by use o f t h e
l u n a r
rov i ng
vehic le and by the improved
l i f e
suppor t sys tems
of
t h e
lunar
module and ast ronaut space su i t .
o f t h e lu n ar module has been inc rea sed
t o
p e r m i t landing
a
g re a t e r pay loa d on t he
l u n a r
s u r f a c e .
The load-ca r ry ing cap ac i ty
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c
-3-
A d di t i on a ll y , s i g n i f i c a n t s c i e n t i f i c d a t a o n t h e E a r th -
Sun-Moon sys tem and on t h e Moon i t s e l f w i l l be ga t he r e d by
a
ser ies
of
l u n a r
o r b i t a l
exper iment s
c a r r i e d
a b o a r d t h e
Apollo
c o m a n d / s e r v i c e
modules.
Most o f t h e o r b i t a l s c i e n c e
t a s k s w i l l be accomplished by Command Module P i l o t A l f r e d M.
Worden, wh i le h i s comrades are on t h e l u n a r s u r f a c e .
Worden i s a USAF major, S c o t t a USAF c o l o n e l a n d I r w i n
a USAF l i e u te n a n t co lon e l .
D ur in g t h e i r f i r s t p e r i o d o f e x t r a v e h ic u l a r a c t i v i t y (EVA)
o n t h e l u n a r s u r f a c e ,
S c o t t
a nd I r w i n w i l l d r i v e
the
l u n a r
r o v i n g v e h i c l e t o e x p l o r e t h e A pe nn i ne f r on t . A f t e r r e t u r n i n g
t o t h e LM, t h e y
w i l l s e t
up th e Apol lo Lunar Su r fac e Exper iment
Package (ALSEP) about
300 f e e t
W e s t
of
t h e
LM.
E xpe ri m en ts i n
the
A p o l l o 1 5
ALSEP
are :
p a s s i v e
seismic
exper iment f o r cont inuous measurement of moonquakes and
meteor i t e i m pac t s: l u na r s u r f a c e m a gne tom e te r f o r measur ing
t h e m ag ne ti c f i e l d a t t h e l u n a r
surface:
so l a r w i nd s pe c t r om e t e r
f o r m e as u ri ng t h e e n er g y an d f l u x of s o l a r pr o t ons a nd
e l e c t r o n s r e a c h in g t h e Moon: s u p r a t h e n a l i o n d e t e c t o r f o r
m e a s ur i ng de ns i t y o f s o l a r w ind h i gh a nd low- ener gy i ons : c o l d
c ak ho de i o n g au ge f o r m e as ur in g v a r i a t i o n s i n t h e t h i n l u n a r
a tm ospher e; a nd t h e h e a t
f l o w
e x p er i m en t t o m e as ur e h e a t
e m ana ti ng f rom be ne a t h t h e l u na r s u r f a c e .
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S c o t t and Irwin
w i l l
use f o r t h e
f i r s t
t i m e a p e r c u s s i v e
d r i l l f o r d r i l l i n g h o le s
i n
t h e Moon's c r u s t f o r placement of
t h e h e a t f lo w e xp e ri m e nt s e n s o r s a nd f o r o b t a i n i n g sa mpl es o f
t h e l u n a r c r u s t .
A d d i t i o n a l l y ,
two
e x p e r ime n t s i n d e p e n d e n t
of
t h e ALSEP
w i l l
b e
s e t
u p n e a r t h e
LM.
They
are
t h e s o l a r w ind c o m po s it i on
e x pe r im e n t f o r d e t e r m i ni n g t h e i s o t o p i c makeup o f n o b l e g a s e s
i n t h e s o l a r wind; and t h e l a s e r r an gi ng r e t r o - r e f l e c t o r
exper iment which
a c t s as
a
p a s s i v e
t a r g e t f o r
Ear th -based
l a s e r s
i n measuring Earth-Moon d i s t an ce s
over
a long- te rm pe r iod .
The s o l a r wind compos i t ion expe r iment ha s been
flown
on a l l
p r e v i o u s m i s s i o n s , a nd t h e l a s e r r e f l e c t o r e xp er im en t w a s
f lown on Apol los 11 and 1 4 . T h e Apol lo 1 5 r e f l e c t o r h a s three
t i m e s more
r e f l e c t i v e
area
t h a n the
t w o
p re vi ou s r e f l e c t o r s .
The second
EVA
w i l l
b e sp e n t i n
a
l e n g t h y g e o l o g y
t raverse
i n wh ich S c o t t a nd I r w i n
w i l l c o l l e c t
documented samples and
make geo logy in ve s t ig a t io ns and pho topanoramas a t a se r i e s o f
s t o p s a l o n g t h e A pen nin e f r o n t .
T h e
t h i r d
EVA
w i l l
be a
g e o l o g i c a l e x p e d i t i o n a l o n g
t h e
Hadley R i l l e and northw ard from t h e LM.
A t
ea ch s t o p i n
t h e
t r a v e r s e s ,
t h e
crew w i l l re-aim a
high-ga in an tenna on
t h e
l u n a r r o v i n g v e h i c l e
t o
p e r m i t a
t e l e v i s i o n p i c t u r e of
t h e i r
a c t i v i t i e s
to
b e beamed t o E a r t h .
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-5-
A sui t case- si ze devi ce
--
cal l ed the l unar communi cat i ons
rel ay uni t
--
f or t he f i r st t i me w l l al l ow t he crew to expl ore
beyond the l unar hor i zon f romthe
LM
and st i l l remai n i n con-
t act w t h Earth. The communi cat i ons uni t rel ays two- way voi ce,
bi omedi cal tel emet ry and tel evi si on si gnal s f romthe l unar
sur f ace t o Earth. Addi t i onal l y, the uni t permts Earth cont rol
of the tel evi si on cameras dur i ng the l unar expl orat i on.
Exper i ments i n the Sci ent i f i c I nst rument Modul e (SI M) bay
of the servi ce modul e are: gamma-ray spectrometer and X- ray
f l uorescence whi ch measure l unar sur f ace chemcal composi t i on
al ong the orbi t al ground t rack: al pha- part i cl e spectrometer
whi ch measures al pha- part i cl es f romr adi oact i ve decay of radon
gas i sotopes emt ted f romthe l unar sur f ace; mass spectrometer
whi ch measures t he composi t i on and di st r i but i on of the l unar
atmosphere: and a subsatel l i t e carryi ng three exper i ments whi ch
i s ej ected i nto l unar orbi t f or rel ayi ng sci ent i f i c i nf ormat i on
to Earth on the Earth' s magnetosphere and i t s i nteract i on w th
t he Moon, the sol ar w nd and the l unar gravi ty f i el d.
The
S I M
bay al so contai ns equi pment f or orbi tal photo-
graphy i ncl udi ng a 24- i nch panoramc camera, three- i nch mappi ng
camera and a l aser al t i meter f or accuratel y measur i ng space-
craf t al t i tude f or correl at i on w th the mappi ng photos.
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Worden
w i l l
p e r f o r m a n i n f l i g h t
EVA t o
r e t r i ev e
the
exposed f i l m . S e l e c t e d f l i g h t e xp er im e nt s w i l l be conducted
d u r i n g t r a n s e a r t h
coast .
S ched ul ed f o r l au n ch a t 9:34 a .m.
E D T ,
J u l y 2 6 , from
NASA's Kennedy Space Ce nte r , F la . , t h e Apollo 1 5 w i l l l a n d
on
the
Moon on F ri da y Ju l y
30.
The l u n a r module
w i l l
remain
on
t h e s u r f a c e
about
67
hours. Splashdown
w i l l
b e
a t
26.1'
North l a t i t u d e by 158O West l o n g i t u d e i n t h e N o rth C e n t r a l
P a c i f i c , n o r t h
of
H a w a i i .
The p ri me r eco v e r y sh i p f o r A po ll o 1 5 i s t h e h e l i c o p t e r
l an d i n g p l a t f o r m
USS
Okinawa.
Apollo 15 command module c a l l s i g n
i s
"Endeavour," and
t h e l u n a r module i s "Falcon." A s i n
a l l
e a r l i e r l u n a r l a n d i n g
m i s s i o n s , t h e
crew w i l l
p l a n t an A merican F l a g on t h e l u n a r
s u r f a c e n e a r t h e l a nd in g p o i n t . A p l aq u e w it h t h e d a t e o f
t h e A p o l l o
1 5
l a n d in g a nd s i g n a t u r e s o f the
crew w i l l
b e
a f f i x e d
t o
t h e LM f r o n t l a n d i n g g e a r .
Apollo 15 backup
crewmen
are U S N Capt . Richard F. Gordon,
J r . , commander; M r . Vance Brand, command module p i l o t : and
D r .
H ar r i so n
H . S c h m i t t ,
l u n a r module p i l o t .
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IMPROVEMENT
M O B I L I T Y
EVA
DURATION
I
S
RFA CE
D URAT
I
N
K
ID
I
O R B I T A L
SCIENCE
PAYLOAD
C APA B l L l W
APOLLO 15
INCREASED OPERATIONAL CAPABIL IT IES
SYSTEM
LUNA R ROVER VEH ICLE
LCRUlGCTA
O A 7 L B S U I T
-7PLSS
LM
C M l S M
SAT UR N V LAUNCH VEHICLE
C A P A B I L I T Y
INCREASED RANGE, CREW MOBILITY,
TRAVERSE PAYLO AD CA PA CIT Y AND
EFFICIENCY
OF
SURFACE OPERAT IONS
IMPROVED L IFE SU P PORT SYSTEM
INCREASES TOTAL EVA DU RATIO N
F R O M
18
TO 40 MANHOURS
VE HIC LE MODIF CAT " PERM TTED
N O M I N A L L U N A R
S
RFA CE STAY T IME
ABO UT DOUBLE. (FROM 37
TO
67 HOUR S)
ADDED
SIM
B A Y A N D E X P ER IM E N T
CONTROLS TO PERMIT CONDUCTING
A D D I T I O N A L O R B I T A L S C I EN C E
C A P A B I L I T Y I NC R EA S ED T O
A
CCOMO DATE THE INCREASED
WEIGHT OF THE PRIOR ITEMS
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MISSION COMPARISON SUMMARY
APOLLO 14 APOLLO 15
LAUNCH
W I
NDOW
S
1-3-3
2-2-3
LAUNCH W I N D O W DURATION 3.5 HOURS
2.5 HOURS
LAUNCH AZIMUTH
72 - 96
DEGREES 80
- 100 DEGREES
EARTH PARKING ORBIT
100
NM 90 NM
SPACECRAFT PAYLOAD
102,095 POUNDS 107,500 POUNDS
TRANS LUNAR TRAJECTORY
TRANSFER MANEUVER NO TRANSFER MANEUVER
LUNAR ORBIT INCLINATION 14 DEGREES
26 DEGREES
SCIENTIFIC INSTRUMENT MODULE NO
LUNA R ORBIT & TRANSEARTH
LUNAR DESCENT TRAJECTORY 16 DEGREES
25 DEGREES
POST LUNAR
LA
ND
I
NG EVA-1
SEVA AND SLEEP
EVA'S 2 (4:45 AND 4~30) 3 (7-7-6)
LUNAR SURFACE STAY TIME 33.5 HOURS 67 HOURS
SUBSATELLITE DEPLOYMENT NO REV
74
TRANSEARTH EVA NO
ONE HOUR
EARTH LANDING
27
DEGREES
SOUTH 26 DEGREES NORTH
MI SS IO N DURATION 9 DAYS 12 DAYS, 7 HOURS
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-
COUNTDOWN
The Apol lo 1 5 launch countdown w i l l be conducted by a
government-industry team of about
500
working i n two cont ro l
c e n t e r s
a t
the Kennedy Space
C e n t e r .
O v e r a l l
s p a c e v e h i c l e o p e r a t i o n s
w i l l
be c on t ro l l e d f rom
F i r i n g Room N o . 1 i n the Complex 39 Launch Control Center.
The s p a c e c r a f t countdown
w i l l
be run from an Acceptance Check-
out Equipment ( ACE) room i n th e Manned Sp ac ec ra f t Operat ions
Bui lding.
More th an f i v e months
of
e x t e ns i v e c hec kou t o f t h e l a unch
ve hi c l e and spac ec ra f t components a re completed bef or e th e
s p ac e v e h i c l e i s r e a d y f o r the f i n a l countdown.
The
prime and
backup
crews
p a r t i c i p a t e i n many of these t e s t s i n c l u d i n g
m is si on s i m u l a t io n s , a l t i t u d e r u n s , a f l i g h t r e ad i ne s s t e s t and
a
countdown demonstration
t e s t .
T h e
space v e h i c l e r o l l o u t --
t h e three
and one-half-mile
t r i p from the Veh icle Assembly B ui ldin g t o t h e launch pad --
took p l a c e May 11.
Apol lo 15 w i l l b e t h e n i n t h S a tu r n V launch from Pad A
(seve n mann ed). ApolLo
1 0
w a s t h e on l y l a unc h t o da t e f rom
Pad B, which
w i l l
b e us ed a g a i n i n 1 9 73 f o r
t h e
Skylab program.
The Apollo 1 5 pre co un t a c t i v i t i e s w i l l s t a r t a t
T- 5
days.
The ear ly
t a s k s
i n c l u d e e l e c t r i c a l connec t ions and pyro technic
i n s t a l l a t i o n i n
the
space ve hi c l e . Mechanical bu i ld up of th e
s p a c e c r a f t
i s
completed , fo l lowed by se r v i c i n g
of
t h e v a r i o u s
ga s e s and c ryoge n i c p ro pe l l a n t s ( l i q u i d oxyge n and l i qu i d
hydroge n) t o t he CSM and LM. Once t h i s i s accomplished, t h e
s p a ce c r a f t b a t t e r i e s
are
placed on board and th e f u e l c e l l s a r e
a c t i v a t e d .
T he
f i n a l countdown be g i ns a t
T-28
hour s when t he f l i g h t
b a t t e r i e s are i n s t a l l e d i n t h e t h r e e s t a g e s and in s tr u m en t u n i t
of
the
launch
vehic l e .
A t the T-9 hour mark,
a
b u i l t - i n h o l d o f n i n e h o ur s an d
3 4 minutes
i s p la nn ed t o
m e e t
cont ingenc ies and provide a r e s t
p e r i o d
f o r
t he l a unc h
crew.
scheduled a t T-3 hours
30
minutes .
A o ne h ou r b u i l t - i n h o l d i s
Fol lowing are some of th e h i g hl ig h t s of t h e l a t t e r p a r t
of t he c oun t :
T-10 hour s , 1 5 minutes S t a r t m ob ile s e r v i c e s t r u c t u r e
(MSS)
move t o pa rk
s i t e
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8
T-9
h o u r s
T-8
h o u r s ,
05
m i nu t e s
T-4
h o u r s , 1 5 m i n u te s
T-4
h o u r s ,
00
m i nu t e s
T-3 hours,
30
m i nu t e s
T-3 ho ur s , 30 mi nu tes
T-3 hours,
06
m i nu t e s
T-2
h o u r s , 48 m i nu t e s
T-2
h o u r s ,
40
m i n u t e s
T - 1
h o u r s , 5 1 m i n u te s
T-43 minutes
T-42
m i nu t e s
T-37
minutes
T-30 minutes
T-20
m i nu t e s
t o T-10
minutes
T-15 minutes
T-6 m i nu t e s
-10-
B u i l t - i n h o l d
f o r
n i n e hou r s a nd
34 minutes .
A t
end of ho ld , pad
i s c l e a r e d f o r LV p r o p e l l a n t l oa d in g .
Launch v e h i c l e p r o p e l l a n t l o a d i n g
-
T h r e e s t a g e s
(LOX
i n f i r s t s t a g e ,
LOX
and
L H 2
i n se co nd a nd t h i r d
s t a g e s ) . C o n ti n ue s t h r u T-3 h o u r s
38 minutes .
F l i g h t crew a l e r t e d .
C r e w
medjca l examina t ion .
C r e w b r e a k f a s t .
O ne-h our b u i l t - i n h o l d .
C r e w
d e p a r t s Manned S pa c e c r a f t
O pe r a t i on s B u i l d i ng f o r LC-39 v i a
t r a n s f e r
van.
C r e w a r r i v a l
a t
LC-39.
S t a r t f l i g h t
crew
i n g r e s s .
Space
Vehic l e Emergency Detec t ion
System (EDS) t e s t ( S c o t t p a r t i c i p a t e s
a l o n g w i t h l a u n ch
team).
R e t r a c t A pol l o
access arm
t o s t a n d -
by p o s i t i o n
( 1 2
d e g r e e s ) .
Arm l aunch esc ap e sys tem. Launch
v e h i c l e pow er t r a n s f e r
t e s t ,
LM
s w it ch t o i n t e r n a l
power.
F i n a l l a un ch v e h i c l e r a ng e s a f e t y
checks ( t o 3 5 m i n u t e s ) .
L aunch v e h i c l e p ower t r a n s f e r
t e s t ,
LM
s w i t c h over t o i n t e r n a l power.
Shutdown
LM
o p e r a t i o n a l i ns tr um e n-
t a t i o n .
S p a c e c r a f t t o f u l l i n t e r n a l po wer.
Space
v e h i c l e f i n a l s t a t u s c hecks .
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-11-
T-5 minutes , 30
seconds
A m
d e s t r u c t
s y s t e m .
T-5
minutes Apollo access arm
f u l l y
r e t r ac ted .
T-3 m i n u t e s , 6 seconds F i r i n g command
(automatic
sequence) .
T-50 se co nd s Launch
v e h i c l e t r a n s f e r t o
i n t e r n a l
power.
T-8.9
seconds
I g n i t i o n
s t a r t .
T-2
seconds
A l l
engines
running .
T-0 L i f t o f f .
NOTE:
Some changes i n t h e countdown
are p o s s i b l e as
a
r e s u l t
of e x p e r i e n c e
gained
i n
the countdown demonstrat ion
t e s t w hich
occurs about t w o
weeks
before
l a u n c h .
Launch d a t e
J u l y 2 6 , 1 9 7 1
J u l y 2 7 , 1 9 7 1 (T +24 )
Aug.
25 , 19 71 (T +24)
S e p t . 2 2 , 1 9 7 1 ( T- 24 )
S e p t . 2 3 , 1 9 7 1 (T-0)
S e p t . 2 4 , 1 9 7 1 ( T+ 24 )
Aug. 2 4 , 1 9 7 1 ( T- 0)
Launch Windows
Windows
( E D T )
Open
C l o s e
9:34
am
1 2 : U pm
9:37 am 12: 14 pm
7:59 am
1 0 : 3 8 a m
8:17
a m
10 :55
a m
6:37 am 9:17 a m
7:20
am
1 o : o o
a m
8:33
a m
1 1 : 1 2
a m
Sun
E l e v a t i o n
Angle
12.00
*
23.2"
1 1 . 3 O
22.5'
12.00
12 .00
23 .0
*
Only
f o r
l aunch azimuth
of
80
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-12-
Ground Elapsed
Time
Update
I t
i s
planned
t o
u p d a t e, i f n e c e s sa r y ,
t h e
a c t u a l
ground e lapsed
t i m e ( G E T )
d u r i n g t h e
mission t o
al low t h e
major
f l i g h t p l a n e v e nt s
t o
occur
a t
the pre -p lanned
GET
r e g a r d l e s s of e i t h e r
a l a t e
l i f t o f f
o r
t r a j e c t o r y d i s p e r s i o n s
t h a t would otherwise have changed th e eve nt t i m e s .
F or ex am ple, i f t h e f l i g h t p l a n c a l l s f o r d es ce nt o r b i t
i n s e r t i o n ( M I ) o oc c ur a t GET 8 2 hours , 4 0 minutes and the
f l i g h t t i m e t o t h e Moon i s t w o minutes lo ng er than planned due
t o t r a j e c t o r y d i s p e r s i o n s
a t
t r a n s l u n a r i n j e c t i o n , t h e GET
clock
w i l l
be tu rned back
two
m in u te s d u r i n g t h e t r a n s l u n a r
coas t
p e r i o d
so
t h a t D O 1 oc c ur s
a t
the pre -p lanned t i m e r a t h e r
t h a n
a t
8 2
hour s ,
4 2
minutes .
I t
f o ll o ws t h a t t h e o t h e r
major
miss ion eve nt s would then a l s o be accompli shed
a t
t h e p r e-
planned t i m e s .
Updat ing the GET c l oc k
w i l l
accompli sh i n one ad jus tment
w hat w ould o t he rw i s e r e qu i r e s e pa ra t e
t i m e
a d j us t me n t s
f o r
each event .
By
upda t i ng t he
GET
c l o c k , t h e a s t r o n a u t s an d
g ro un d f l i g h t c o n t r o l p e r s on n e l
w i l l
b e r e l i e v e d
of
the
burden
of
changing t h e i r
c h e c k l i s t s ,
f l i g h t p l an s , e t c .
b e k ep t t o
a
minimum and
w i l l ,
g e n e r al l y , b e l i m i t e d t o
t h ree
u p d a t es . I f r e q u i r e d , t h e y w i l l oc c ur
a t
a bou t 53 9 7 and 150
hour s i n t o t h e mi s s ion . Both
t he
a c t u a l
GET
and t h e upda te
GET w i l l
b e m a in t ai n ed i n t h e
MCC
t h roughou t t h e mi s s i on .
The
planned t i m e s i n t h e mi s si on f o r upda t ing GET
w i l l
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II
-13-
L aunc h and M i s s ion P r o f i l e
The Saturn
V
l aun ch v e h i c l e (SA-510) w i l l b o o s t t h e
A po l l o 1 5 s p a c e c r a f t from Launch Complex 39A a t t h e Kennedy
S p ac e C e n t e r , F l a . , a t 9:34 a .m.
EDT,
J u l y 2 6 ,
1 9 7 1 ,
on an
azimuth of 80 degrees .
The f i r s t s t a ge ( S - l C ) w i l l l i f t t h e v e h i c l e 38 n a u t i c a l
m i l e s above
t h e E a r t h .
A f t e r
s e p a r a t io n t h e b o o s t e r w i l l
f a l l
i n t o t h e A t l a n t i c O cean a b o u t 367 n a u t i c a l
miles
downrange
f rom Cape Kennedy , approx im ate ly n in e minu tes , 2 1 s e c o n d s a f t e x
l i f t o f f .
T he s e c ond s t a ge
S-11) w i l l
p us h t h e v e h i c l e
t o
a n
a l t i t u d e
of
a b o u t
9 1
n a u t i c a l m i l e s .
A f t e r
s e p a r a t io n , t h e
S-11
s tage w i l l f o l l o w a b a l l i s t i c t r a j e c t o r y
as
it p l unge s
i n t o t h e A t l a n t i c a b ou t
2 , 2 4 1
n a u t i c a l m i l e s downrange from
Cape Kennedy
about
1 9
m i n u t e s ,
4 1
s e c onds
i n t o
t h e
mission.
t h e v e h i c le i n t o a 9 0 - n au t ic a l -m i l e c i r c u l a r p a r k i n g
o r b i t
befo re it i s
c u t o f f
f o r
a
c o a s t i n g p e r i o d . When r e i g n i t e d ,
t h e e n g i n e w i l l i n j e c t t h e A pollo s p a c e c r a f t i n t o
a
t r a n s l u n a r
t r a j e c t o r y
.
The
s i n g l e en g i n e o f t h e t h i r d s t a ge
S-IVB) w i l l
i n s e r t
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T i m e
H r s Min
Sec
00
00
00
00
00
0 0
4
::
00
(D
I
00
00
00
00
00
00
00
00
01
02
02
02
02
03
03
07
09
09
09
11
11
00
20
15.8
38.7
40.5
42.2
10.5
16.2
38.8
9.4
10.4
13.5
38.8
48.8
Event
F i r s t Motion
Maximum Dynamic P re s s u re
S-1C Center Engine Cutoff
S-1c Outboard Engines Cutoff
S-lC/S-II S e p a r a t i o n
S-11
I g n i t i o n
S - I 1
A f t I n t e rs t a g e J e t t i s o n
Launch Escape T o w e r J e t t i s o n
S-I1 Center Engine Cutoff
S - I 1
Outboard Engines Cutoff
S-II/S-IVB Separation
S-IVB I g n i t i o n
S-IVB
F i r s t C u to ff
P a r k i n g O r b i t I n s e r t i o n
(90 nm)
Launch Events
V e h ic l e
W t
(Pounds)
6,407,758
4,048,843
2,388,283
1,841,856
1,477,783
1,477,782
1,406,067
1,383,533
651,648
476,526
476,155
317,273
309,898
309,771
A l t i t u d e
(Fee t
198
42,869
155,162
225,008
230,893
236,196
320,265
335,636
584,545
576,526
576,535
576,529
563,570
563,501
V e l o c i t y
(F t /Sec )
0
1,605
5,573
7,782
7,799
7,778
8,116
8,210
17,362
21,551
21,560
21,564
24,233
24,237
Range
(Nau
Mi)
0
3
26
48
50
52
86
93
594
876
880
890
1,422
1,461
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M is s ion Events
GET V e l o c i t y c h an g e
D a t e / E D T
f e e t / s e c
Trans lunar in je ct io n 02:56 26/12:30 pm 10,036
(s-IVB
e n g in e i g n i t i o n )
CSM se pa ra ti on , dock ing 03:20 26/12:54 pm
_ _
E jec t ion f r om
SLA
04:15 26/01:49 pm I
S-IVB
evasive
maneuver 04:39 26/2:13 pm 10
Residual Pr op el la nt Dump 05:OO 26/2:3 4 pm
AF S Impact Burn
( 4
min .) 05:45 26/3:19 pm
26/7:04 pm
M APS Corr ect ion Burn 09:30
I
M idcour s e co r r ec t ion 1 TLI+9 h r s 26/9:29 pm
O*
M idcour s e co r r ec t ion 2
TL1+28 h r s 27/4:29 pm 0
Midcourse co rr ec ti on 3 LOT-22 h rs 28/6:05 pm
O*
M idcour s e co r r ec t ion
4 LO T- 5
hrs 29/11:05 am o *
SIM Door j e t t i s o n
LOI-4.5 h rs 29/11:35 am 9
Lunar o r b i t i ns e r t i on 78:33 29/4:07 pm -2,998
( T h u s .
I
P u rp o s e a nd r e s u l t a n t o r b i t
I n j e c t i o n i n t o t r a n s l u n ar
t r a j e c t o r y
w i t h
68 nm
p e r i c y n t h i o n
Mati ng o f CSM
and
LM
S e p a r a t e s CSM-LM fro m S-IVB/SLA
P r o vi d e s s e p a r at i o n p r i o r
t s - In pro-
pe l l an t dump
and
t h r u s t e r m a n e u v e r
to cause
l u n a r i m p a c t
* Th es e m i d c o u rs e c o r r e c t i o n s h a v e
a
nomina l
v e l o c i t y c h a n g e of 0 f p s , b u t
w i l l be c a l -
c u l a t e d
i n
r e a l
t i m e
t o c o r r e c t TLI d i s -
p e r s i o n s; t r a j e c t o r y w i t h i n c a p a b i l i t y of
docked DPS burn aho uld SPS f a i l t o i g n i t e .
I n s e r t s
A p o ll o 1 5 i n t o 58
X
170 nm e l l i p t i c a l
l u n a r
o r b i t
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GET
hrs:min
S-Iv8 i mpact s l unar 79:13
surf ace
Descent orbi t i nser t i on 82: 40
( D O I )
CSM- LM undocki ng 100: 14
CSM ci rcul ar i zat i on 101.35
LM Power ed descent 104: 29
i ni t i at i on
104: 41
LM t ouchdown on l unar
surf ace
Dat e/ EDT
29/ 4:47 pm
29/ 8:14 pm
30/ 1:48
pm
30/ 3:09 pm
30/ 6:03 pm
30/ 6: 15 pm
(Fr i day)
Vel oci t y change
eet/ sec
_ _
- 207
_ _
70
6, 698
Purpose and resul t ant orbi t
Sei sm c event f or Apol l o 12 and 14
passi ve sei smomet ers
SPS burn pl aces CSM LM i nto 8
x
58 nm
l unar or b i t
I nser t s
CSM
i n to 54 X 6 5
nm
or bi t
SPS
burn)
Thr ee-phase
DPS
bur n
to
brake LM out of
t r ans fer o rb i t , ver t i cal descent and
t ouchdown on l unar s urf ace
Lunar expl orat i on, depl oy ALSEP, col l ect
geol ogi cal sampl es, photography
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APOLLO 15
25
APPROACH TRAJECTORY
SIGNIFICANT ENHANCEMENT OF TERRAIN CLEARANCE
SIGNIF ICA NT NHANCEMENT OF V IS IB IL IT Y AND FIDELITY
OF LPD
NO SIGNIFICA NT INCREASE I N VERTICAL VELOCITY
MODEST INCREASE IN
A V
FOR REDESIGNATlmS
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M I A D 7 1 5 1 7
f
5562
5534
4111
3444
2500
1163
318
66 ( 76 ) .
POWERED DESCENT PROFILE
-5
.50,087
-4 49.979
-58 44.040
-67 39,878
-85 33,623
-80 22 , 950
-162 7,029
- 2 3 6 9 4
.--
11:oor 1o;ooy
50-
6 4 q
40-
12:02
ALTITUDE. 30-
N
MI
S UMMA RY
-
I
I
EVENT
POWERED DESCENT INITIATION
THROTTLE TO M A XI M U M THRUST
Y A W TO VTRTICAL
LANDING RADAR ALTITUDE UPDATE
LANDING RADAR VELOCITY UPDATE
THROTTLE RECOVERY
HIGH GATE
L O W G A TE
TFI,
MIN:SEC
0:oo
0:26
3:OO
4:06
5:34
7:24
9:24
10:42
L A N D I N G
12:02
VI, FPS I il, FPS I
A,
FT
-15 (0) -5 5
I
A V ,
FPS
0
28
1468
2159
3167
4597
5640
6241
6698
*(HOR IZONTA L VELOCITY RELATIVE TO SURFACE)
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APPRO ACH PHASE CO M PARI S I O N
0
I TIME TO LANDING,
-25 APPROACH
- - - - A POLM 14
6
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APOLLO 15 LU N AR SU R FAC E AC T IV IT IES SU MMAR Y
B R I EF
& EA T EV A - 1 PR EPS
EVA-I
EV A - 2 PR E PS EV A - 2
PERIOD
N
EA T
POST EV A - 1 A C TM TI ES
PERIOD
REST PERIOD 6-8:301
i
EVA-2
I
EVA-3
B R I EF
PO ST EV A -2 A C TM TI ES
&
EAT RES T PERIOD (-7:30)
&
E A T E V A -3 P R E P S
B R I EF
PERIOD PERIOD
P OS T E V A 4
A C T M T I E S
- 5
I
I
I
I I
EA T LM
PERIOD L~~~~
51
i8
62 63 4
$5
$6
$7
A I F T O F F
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-21-
EVA Mission Events
GET
Events hrs :min Date/EIYP
CDR starts standup EVA (SEVA) for
verbal description of landing site,
360 photopanorama
End SEVA, repressurize
Depressurize
LM
for EVA 1
CDR steps onto surface
W P steps onto surface
CDR places T V camera on tripod
LMP collects contingency sample
LMP climbs
IN
ladder t o leave
contingency sample
on
platform
Crew unstows LRV
LRV test driven
LRV equipment installation complete
Crew mounts LRV for drive t o geology
station No. 1--Hadley Rille rim near
elbow : 2--base of Apennine front
between elbcw and St. George crater:
3--Apennine front possible debris flow
area
Start LRV traverse back t o LM
Arrive at
LM
Offload ALSEP from LM, load drill and
LRRR on LRV
106:lO
106:40
119:50
120:05
120:14
120
:
6
120:17
120:20
120
:
0
120
:
5
120:58
121:12
123:12
123:40
123:58
Jul 30/7:44 pm
8:14 pm
Jul 31/9:24 am
9:39 am
9:48
am
9:50 am
9:51 am
9:54 am
9:54 am
10:09 am
10:32 am
10:46 am
12:46 pm
1:14 pm
1:32 pm
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T RA V E RS E S U M M A R Y
I
N
W
6
I
n
I
INCLUDES
LRV
INGRESSIEGRESS TIMES
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T R A V E R S E PL AN
E V A - 1
STATlONlAREA ACTIVITY
1
(ELBOW) RA DIAL SAMPLE
2 (ST. GEORGE) RA DIA L SAMPL E
COMPREHENSIVE SAMPLE
500mm PHOTOGRAPHY
STEREO PAN
P
ENETROMETER
H
l
3
DOCUMENTED SA MPL E
NEAR LM ALSEP DEPLOYMEN
LR3 DEPLOYMENT
SWC DEPLOYMENT
M A RE S A M P L I N G
STATION T IME
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c
- 2 5 -
GET
Events hrs:min Date/EDT
CDR drives LRV to ALSEP site,
IMP
walks
Crew deploys ALSEP
AISEP deploy complete, return
by LRV to LM
Arrive at
LM
LMP deploys solar wind composition
experiment, CDR makes polarimetric
photos
Crew erects
US
flag
Crew stows equipment at
LM
and on LRV
Crewmen dust lunar material from each
other's EMUS
U P ingresses
LM,
CDR sends up Sample
Return Container No. 1 on transfer
conveyor
CDR ingresses r.. f
Repressurize
LM,
end
EVA
1
Depressurize
LM
for EVA 2
CDR steps onto surface
LMP steps onto surface
Crew loads gear aboard LRV
for
geology
traverse, begin drive
to
Apennine front
Arrive secondary crater cluster (sta.4)
Arrive at Front Crater, gather samples,
photos of front materials on crater rim
124:05
124:08
125:49
125 t55
125 :58
126:13
126: 18
126
:
4
126:27
126:40
126:50
141:12
141:23
141
:
7
141:59
142 : 7
143:16
1:39 pm
1:42 pm
3:23
pm
3:29 pm
3:32 pm
3:47 pm
3:52 pm
3:58 pm
4:Ol pm
4:14 pm
4:24 pm
Aug 1/6:46 am
6:57 am
7:11 am
7:33 am
8:01 a m
8:50 am
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STATIONlAREA
4 (SECONDARIES
5 - 6 - 7 (SECOND
I
I
8
(MARE)
T R A V E R S E PL AN
E V A - 2
ACT1
V
ITY
SOILIRAKE SAMPLE
DOCUMENTED SAMPLE
500mm PHOTOGRAPHY
EXPLORATORY TRENCH
CORE TUBE
(1)
S T A T IO N T I M E
STATION 5 : DOCUMENTED A PLES FROM UPSLOPE S IDE-
DOCUMENTED SAMPLE S DOWNSLOPE SID E
EXPLORATORY TRENCH
500mm PHOTOGRAPHY
STATION
6 - 7:
DOCUMENTED SAMPLES
EXPLORATORY TRENCHES
CORE TUBE SAMPLE
500mm PHOTOGRAPHY
COMPREHENSIVE SAMPLE
DOUBLE CORE TUBE SAM PLE
DOCUMENTED SAMPLE
SESC
TRENCH
SOIL MECHANICS EXPERIMENT
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- 2 7 -
GET
Events hrs:min Dat e/EDT
Arrive at area stop 5-6 on crater rim
slope, samples, photos, soil mechanics
trench
Arrive at stop 7--secondary crater
cluster near 400m crater; collect
documented samples, photopanorama
Arrive at stop 8 for investigations of
materials in large mare area
Arrive back at LM, hoist Sample Return
Container
No.
2 into
LM
Crew ingresses
LM,
repressurize,
End EVA 2
Depressurize for EVA 3
CDR steps onto surface
LMP steps onto surface
Prepare and load LRV for geology
traverse
Leave for stations 9-13
Arrive station 9--rim of Hadley Rille;
photos, penetrometer, core samples,
documented samples
Arrive at station 10; documented
samples, photopanorama
Arrive at station 11--rim of Hadley
Rille; documented samples, photopanorama,
description of near and far rille walls
144:23
146:ll
146:47
147:lO
148
: 0
161:50
162:03
162:09
162:ll
162:44
163 : 8
164:Ol
164:17
9:57 am
11:45 am
12:21 pm
12:44 pm
1:44
pm
Aug 2/3:24 am
3:37 am
3:43 am
3:45 am
4:18 am
4:42 am
5:35 am
5:51 am
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STATIONIAREA
9 - 10
(RILLE)
T R A V E R S E
P L A N
E V A - 3
ACT I l TY
STATION
9:
500mm PHOTOGRAPHY
COMPREHENSIVE SAMPLE
DOUBLE CORE
DOCUMENTED SAMPLE
SESC
PENETROMETER
STATION
10:
500mm P H O T O G R A P H Y
5OOmm PHOTOGRAPHY
DOCUMENTED S AMP LE
DOCUMENTED SAMPLE
12 (N. COMP LEX/ DOCUMENTED SAM PLE
CH AIN CRATER) CORE TUBE
13
(N. COMPLEX)
CRATER - DOCUMENTED S AM PLE
- PHOTOGRAPHY
EAGLE CREST
N O R M CO MPLEX
SCARPS
SAMPLES, OBSERVATION & PHOTOGRAPHY
OF:
14 ( MARE)
DOCUMENTED SAMPLE
S T A TI ON T I M E
I
N
I
m
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- 2 9 -
GET
Events hrs:min Date/EDT
Arrive at station
12--SE
rim of Chain
crater: documented samples, photopan-
orama, seek unusual samples
Arrive at station 13--north complex
scarp between larger craters;
documented samples, photograph scarp,
observe and describe 750m and 390m
craters, core tubes, trench,
penetrometer
Arrive station 14--fresh blocky crater
in mare south of north complex:
photopanorama, documented samples
Arrive back at
LM
Load samples, film in LM: park LRV
300
feet east of LM, switch to
ground-controlled TV for ascent
crew ingress LM, end 3rd EVA
165 :00 6:34 am
165
:
1 7:05 am
166:43
167: 7
167
:
5
167:50
8:17 am
8:51
am
9:09 am
9:24 am
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CSM pla ne change
LM
a s c e n t
I n s e r t i o n i n t o l u n a r
o r b i t
T e r m i n a l p h a s e i n i t i a t e
(TPI) (LM APS)
I
it
Braking
(LM
RCS;
4
b u r n s )
Docking
LM
j e t t i s o n , s e p a r a t i on
LM
a s c e n t
stage
de-
o r b i t
(RCS)
LM
impac t
CSM o r b i t a l c h a n q e
S u b s a t e l l i t e e j e c t i o n
GET
hrs:min
165:13
171:35
171:43
172:30
1 7 3 : l l
173:30
177:38
179:06
179:31
221:25
222:36
M is s ion E ven t s ( Con t ' d . )
V e l o c i t y c h an g e
Date/EDT feet /sec
2/6:47
am
309
2/01: 09 pm
6,056
2/01:17 pm
2/2:04
pm
2/2:45 pm
52
3 1
2/3:04 pm
2/7:12 pm
2/8:40 pm -195
2/9:05
am
4/2:59 pm
4/4:10 pm
64
P ur po se a nd r e s u l t a n t o r b i t
C h an g es CSM o r b i t a l p l a n e b y 3 .3 '
t o c o i n c id e w i t h LM o r b i t a l p l a n e
a t t i m e
of a s c e n t f r o m s u r f a c e
B o os t s a s c e n t s t a g e i n t o 9
X
46 nm
l u n a r o r b i t f o r r en de z vo us w i t h
C S M
B o os t s a s c e n t s t a g e i n t o
6 1 X
4 4
nm
ca t ch - up o r b i t ; LM
t r a i l 5
CSM by 32
nm
and 15 nm below a t
t i m e
of TPI burn
L i n e - o f- s i g h t t e r m i n a l p h a s e b r a k i n g t o
place LM
i n
59
x 5 9 nm o r b i t f o r f i n a l
appr oach , dock ing
CDR
and LMP t r a n s f e r b ac k
t o
CSM
P r e v e n t s r e c o n t a c t
of
CSM w i t h LM a s c e n t
s t a g e d u r i n g r e m a i n de r
of
l u n a r o r b i t
ALSEP
seismometers a t
Apol lo
15, 1 4
and
1 2 l a n d i n g
s i t e s
r e c o r d i m p a c t e v e n t
Impact
a t
a b o u t 5 , 5 2 8 f p s
a t
-4'
a n g l e ,
32 nm from Ap ol lo
15
ALSEP
55
X
75 nm o r b i t
(Rev
73)
L u n a r o r b i t a l s c i e n c e e x p er i m en t
w
I
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GET
r a n s e a r t h i n j e c t i o n 2 23 :4 4
( T E I ) SPS
M idcours e co r r ec t io n 5 T EI +17 h r s
I n f l i g h t EVA 242:OO
M idcour s e co r r ec t ion
6
EI-22 hr s
M idcour s e co r r ec t ion 7 E I - 3 h r s
$
CM/SM
s epar a t ion 294 :43
i
?
E n t r y i n t e r f a c e
(400,000 f t )
Splashdown
294:58
295:12
Date/EDT
4/5:18 pm
S/l0:20
am
5/11:34 am
6/6:32 pm
7/01 :32 pm
7/4:17 pm
7/4:32 pm
7/4:46 pm
V e l o c i t y c h an g e
fee t /sec Pur pos e and r e s u l t a n t
o r b i t
3,047
I n j e c t CSM i n t o t r a n s e a r t h t r a j e c t o r y
0 T r a n s e a r t h m i d c o ur s e c o r r e c t i o n s w i l l
be computed i n
r ea l
t i m e f o r e n t r y
c o r r i d o r c o n t r o l a n d r e c o v e r y
area
w e a t h e r avo idaoce
To
r e t r i eve
f i l m c a n n i s t e r s f ro m
SM
SIM
bay
0
0
Command module oriented
for
E a r t h
a t m o s ph e r e e n t r y
Command module en te rs atmosph ere
a t
36 , 097 f ps
L and ing 1 , 190 m downrange f rom ent ry:
s p l a s h
a t
26. 1' Nor th l a t i t u de , 158O
W e s t l o n g i t u d e
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EVA
PROCEDURES
C R E W M A N PATH
TO
FOOT RESTRAINTS
\ Q U A D B
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3 3
Ent ry Event s
Event
Ent ry
Ent er S-band communi cat i on
bl ackout
I ni t i at e const ant drag
Maxi mumheat i ng rate
Maxi mum l oad f act or (FI RST)
Exi t S- band communi cat i on
bl ackout
Maxi mum l oad f actor ( SECOND)
Termnat i on of CMC gui dance
Drogue parachut e depl oyment
Mai n parachut e depl oyment
Landi ng
Ti me f rom400, 000 ft.
m n: ec
0O:OO
4: 32 p.m 7t h August
00: 18
00: 54
01
: 0
01: 24
03:34
05: 42
06: 50
07: 47 ( a l t i t u d e ,
23, 000
f t . )
08: 36
( a l t i t u d e , 10, 000 f t . )
13:26 4: 45 p.m 7t h August
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,
-35-
Recovery Opera t ions
Laun ch a b o r t l a n d i n g
areas
e x t e nd dow nra nge 3 ,400 n a u t i c a l
miles
from Kennedy Space Ce nt er , fanw ise
50
nm ab ov e and below
t h e
l i m i t s of
t h e
var i ab l e
l aunch az imuth
(80-100
d e gr ee s ) i n
t h e
A t l a n t i c
Ocean.
Splashdown f o r a f u l l - d u r a t i o n l u n a r la n d i n g m i ss io n
launched on t i m e J u l y
2 6
w i l l b e
a t 4 : 4 6
p.m.
E D T ,
August
7 a t
2 6 . 1 "
N orth l a t i t u d e by
158O West
l o n g i t u d e -- a b o u t 2 9 0 nm
d u e n o r t h
of
P e a r l
Harbor,
H a w a i i .
The l a n d i n g p l a t f o r m - h e l i c o p t e r
(LPH)
USS Okinawa, Apollo
15 pr im e r e c ove r y vesse l , w i l l b e s t a t i o n e d n e a r t h e e nd -o f-
m i s si o n a i m i ng p o i n t p r i o r
t o
e n t r y .
I n a d d i t io n t o t h e pr im a ry r e co v er y v e s s e l l o c a t e d i n t h e
r e c o v e r y a rea , HC-130
a i r
r e s c u e a i r c r a f t w i l l
be
on s t a ndby
a t
s t a g i n g b a s e s a t Guam,
H a w a i i ,
A z ore s a nd F l o r i d a .
Recovery Opera t io ns C on t ro l Room i n t h e
Mission
C o n t r o l C e n t e r ,
s u p p or t ed by t h e A t l a n t i c R e cover y C on t r o l C e n t e r , N or f o l k , V a . ,
a nd t h e P a c i f i c R ec ov er y C o n t r o l C e n t e r , K u ni a,
H a w a i i .
A p o ll o 1 5 r e c ov e r y o p e r a t i o n s w i l l
be direc ted f r o m
t h e
The Apol lo
1 5
crew
w i l l
r em a in a b o a rd t h e USS Okinawa u n t i l
t h e s h i p r e a ch e s
P e a r l
H a rbo r t h e day
a f t e r
splashdown.
w i l l be flown fsom Hickam
A i r Force
B a s e
t o H oust on a boa rd a
USAF t r a n s p o r t a i r c r a f t .
o f crew o r
spacec ra f t .
They
There
w i l l
b e
no
p o s t f l i g h t q u ar a n t i n e
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APOLLO
15
C R E W POST-LANDING ACTIVITIES
DAY S FROM RECOVERY ATE AC TIV ITY
SPLASHDOWN AUGUST 7
R +
1
AUGUST
a
R+
2
A UGUS T
9
R + 3 M R U
R+15
i
.5
t
s
I
5
R + 5 ,
AUGUST 12
A RR I V E P E ARL HARB OR
A R R I VE M S C
CREW DEBRIEFING PERIO D
CREW PRESS CONFERENCE
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- 3 7 -
A P O L L O
1 5
MISSION OBJECTI VES
F i r s t o f
t h e
Apol lo
J
m i ss io n s e r i e s wh ich a r e c a p ab l e
of l o n g e r s t a y t i me s on t h e Moon a nd g r e a t e r s u r f a c e mo b i l i t y ,
Apol lo 15 has fo u r pr i ma ry o b j e c t i v e s wh ic h
f a l l
i n t o t h e
g e n e r a l c a t e g o r i e s o f T un ar s ur f a c e s c ie n c e , l u n a r o r b i t a l
s c i e n c e , a n d engi neer i ng/ oper at i onal .
T h e mi s s i o n o b j e c t i v e s a r e t o exp lore the Had ley-
A pen nin e r e g i o n , s e t up a nd a c t i v a t e l u n a r s u r f a c e s c i e n -
t i f i c e x p e r i me n t s, make e n g i n e e r i n g e v a l u a t i o n s o f new
Apol lo equ ipment, and conduc t lun a r o r b i t a l expe r iments and
p h o t o g ra p h i c t a s k s .
E x p l o r a t i o n and g e o l o g i c a l i n v e s t i g a t i o n s a t t h e Hadley-
A ppenine s i t e
w i l l
b e e n ha n ce d by t h e a d d i t i o n o f
t h e
l u n a r
r o v e r v e h i c l e
t h a t
w i l l a ll ow S c o t t and I r wi n t o t r a v e l g r e a t e r
d i s t a n c e s f ro m t h e lunar module tha n the y cou ld on fo o t du r in g
t h e i r
t h r ee
E V A s . S e tu p of t h e A po ll o l u n a r s u r f a c e e x p e r i -
ment package (ALSEP) w i l l b e t h e t h i r d i n a t r i o of o p e r a t i n g
ALSEPs ( A p ol lo s 12 , 1 4 , and 1 5 . )
O r b i t a l s c i e n c e e x p e r i me n t s
are
p r i m a r i l y c o n c e n t r a t e d
i n a n a r r a y of i n st ru m e nt s an d ca mer as i n t h e s c i e n t i f i c i n -
s trument module (SIM) b a y o f t h e s p a c e c r a f t s e r v i c e module.
Command module p i l o t Worden
w i l l
o p e r a t e t h e s e i n s t r u m e n t s
d u r i n g t h e p e r i o d h e i s f l y i n g th e command module s o l o and agai n
f o r two d a ys f o l l o w in g t h e r e t u r n o f a s t r o n a u t s S c o t t and I rwin
from t h e l u n a r s u r f a c e . A f t e r t r a n s e a r t h i n j e c t i o n , h e
w i l l
go
EVA
t o r e t r i e v e f i l m c a s s e t t e s f ro m t h e SIM b ay . I n a d d i t i o n
t o o p e ra t in g SIM bay experiments, Worden
w i l l
conduc t o the r
exper iments such as g e ge n sc h ei n a n d u l t r a v i o l e t ph o to g ra p hy
t a s k s fr om lu n a r o r b i t .
Among th e en gi ne er in g/ op er a t io na l t asks t o b e c a r r i e d
out by t he ApnIlo 15 crew i s t h e e v a l u a t io n o f t h e modi f ica -
t i o n s
t o
t h e l u n a r module which were made for c a r r y i n g a h e a v i e r
p a y lo a d a n d f o r a
lunar
s t a y t i me o f a l mo s t t h r e e d a y s . Changes
t o
t h e
A po llo s p a c e s u i t a nd t o t h e p o r t ab l e l i f e s u p po r t s y s -
tem (PLSS) w i l l be ev a lu a te d . Pe r formance o f t h e l u n a r r o v e r
v e h i c l e
( L R V )
and th e o th e r new J -mis s ion equipment th a t goes
w i t h
i t - - t h e
lunar
c o mmu n i c a t i o n s r e l a y u n i t
( L C R U )
a n d t h e
g r o u n d - c o n t r o l l e d t e l e v i s i o n a s s e m b l y (GCTA)--also w i l l be
e v a l u a t e d .
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LUNAR SURFACE EXPERIMENTS
A
-
S - 03 1 L U N AR P A S S IV E S E IS M O LO G Y
S-033
LUNAR ACTIVE SEISMOLOGY
S-034 LUNAR TR I AX I S MAGNETOMETER
S-035 ME DIU M ENERGY SOLAR WIND
S-036 SUPRATHERMAL ION DETECTOR
S-037 LUNAKHEATFLOW
S-038 CHARGED PARTICLE LUNAR ENVIRONMENT
S-058 COLD CATHODE GAUGE
M-515 LUNAR DUST DETECTOR
x x x x
x
X X
X X
x x x
X
X
x x x
x x x
x x x x
X
x x
x x
x x x
X
x x
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LUNAR ORBITAL EXPERIMENTS
11 12 14
1 5
SERVICE MODULE
S-160 GAM MA-RA Y SPECTROMETER
S-161 X-R AY FLOURESCENCE
S-162 ALP HA -PAR TICL E SPECTROMETER
S-164
S-BAND TRANSPONDER
S-165 MASS SPECTROMETER
S-170 B ISTA TIC RADAR
5173 PARTICLE MEASUREMENT (SUBSATELLITE)
I
5 1 7 4 MAGNETOMf lER ISUBSATELLITE)
2
S-164 S-BAND TRANSPOND ER (SUBSATELLITE)
24 PANORAM IC CAMERA
3
M A P P ING CAMERA
LASER ALTIMETER
COMMAND MODULE
S-176 APOLLO WINDOW METEOROID
-177
S-178 GEGENSCHEIN FROM LUNAR OR BIT
W PHOTOGRAPHY
- EARTH
AND MOON
X
X
X
X X
X
X X
X
X
X
X
X
X
X X
X
X
X
I
w
(0
I
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- 4 0 -
L u na r S u r f a c e S c i e n c e
A s
i n p r e vi o u s l u n a r l a n d i n g m i s s io n s ,
a
c o n t i n g e n c y
sample of l u n a r s u r f a c e m a t e r i a l
w i l l
b e t h e
f i r s t
s c i e n t i f i c
o b j e c t i v e pe rf or m ed d u r i n g t h e
f i r s t
EVA p e r i o d .
The
Apol lo
1 5
l a n d i n g c re w w i l l d e v o t e a l a r g e p o r t i o n of t h e f i r s t EVA
t o d e p l o y i n g e x p e r i m e n t s
i n
t h e ALSEP. These in s t ru m en ts
w i l l
r em a in on t h e Moon t o t r a n s m i t s c i e n t i f i c d a t a Through the
Manned Space Fl i g h t Network
on
l o ng - te r m p h y s i c a l a nd e n v i r o n -
m e n t a l p r o p e r t i e s of t h e Moon. These d a t a c an be c o r r e l a t e d
w i t h known E a r t h d a t a for f u r t h e r k no wl ed ge on t h e o r i g i n s
of
t h e p l a n e t a nd i t s
s a t e l l i t e .
ments : S-031 Pa ss iv e Se i smi c Exper i ment , S-034 Lunar Su r fa ce
Magnetometer Exper i ment , S-035 S o l a r Wind Spe c tr om et er Exp er i -
ment, 5 - 0 3 6 S u p r at h e r m al I o n D e t e c t o r E x p er i m en t , S - 0 3 7 Heat
Flow Exper iment ,
S - 058
Cold Cathode Gauge Exper iment, and
M-515
L u na r D u st D e t e c t o r E x p e ri m e n t .
The ALSEP
a r r a y
c a r r i e d on A po l lo
1 5
h a s s ev en e x p e r i -
Two a d d i t i o n a l e x p e r i m e n t s , n o t p a r t
of
ALSEP,
w i l l
be
dep loy ed i n t h e ALSEP
area :
S-078
Laser
Rang ing Re t ro -Re f lec -
t o r a n d S-080 S o l a r Wind C ompos i t ion .
Pa s s i ve Se i smic Expe r imen t : (PSE)
: The
PSE measures
s e is m i c a c t i v i t y
of
t h e Moon and ga t he rs and
r e l a y s . t o
E a r t h
i n f or m at io n r e l a t i n g t o p h y s i c a l p r o p e r t i e s of t h e l u n a r c r u s t
a nd i n t e r i o r . The PSE r e p o r t s s e i s m i c
da ta
on man-made im p a ct s
(LM a s c e n t s t a g e ) , n a t u r a l i mp ac ts
of met eo r i t e s ,
and moon-
quakes .
D r . G a r y
Latham
o f
t h e Lamon t-Dohe rty Ge o lo g i ca l
O b s e r v a t o r y ( C ol um b ia U n i v e r s i t y ) i s r e s p o n s i b l e f o r PSE design
and expe r imen t data
a n a l y s i s .
Two s i m i l a r PSEs deployed
as
a p a r t of t h e Apol lo 1 2 and
1 4 ALSEPs have t ransmit ted t o E a r t h data on lunar s u r f a c e s e i s -
m i c e v e n t s
s i n c e
deploy ment. The Apo llo
1 2 ,
24 and 1 5
s e i s -
m om et er s d i f f e r f ro m t h e s e i s m om e t e r
l e f t a t
T r a n q u i l l i t y
Base
i n
J u l y 1 9 6 9
b y
t h e A p o l l o
11
crew i n t h a t t h e
l a t e r
PSEs a r e
con t inuous ly powered b y SNAP-27 r a d i o i s o t o p e e l e c t r i c g en -
e r a t o r s . The A p o ll o 11 se ismometer , powered b y s o l a r c e l l s ,
t r a n s m i t t e d
data
o n l y d u r i n g
t h e
lunar
d a y ,
and
i s
n o l o n g e r
f u n c t i o n i n g .
A f t e r A p o l l o 1 5 t r a n s l u n a r i n j e c t i o n , a n a t te m p t w i l l
b e
made
t o i mp ac t t h e s p e n t
S - I V B
s t a g e and t h e i n s t ru m e n t u n i t
i n t o t h e Moon,
This w i l l
s t i m u l a t e
t h e
p a s s i v e s e i s m o m e t e r s
l e f t
on t h e l u n a r s u r f a c e
by
o t h e r A p o ll o c r e ws .
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Background Scientific Information on the Lunar
Surface Experiments
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ALSEP ARRAY
L AYOUT
PROBE
->25-
I
ENTRAL-
STATION
>15
I
I
P
N
A
LRV
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-43-
Through
a
s e r i e s
of
switch-s elect ion-c omm and and ground-
commanded
t h r u s t
opera t ions , the S-IVB/IU
w i l l
be d i r e c t e d t o
h i t t h e
Moon w i t h i n a
t a r g e t a r e a
379
n a u t i c a l
miles
i n d ia -
m e te r . The t a r g e t p o i n t i s
3 . 6 5
d e g r ee s s o u t h l a t i t u d e by
7 . 5 8
de g r e e s w es t l ong i t ud e , ne a r L el a nde C r a t e r a bou t
1 6 1
n a u t i c a l
m i le s e a s t
of
Apol lo
1 4
l a nd in g s i t e .
A f t e r t h e l u na r module
i s
e j e c t e d f rom t h e S-IVB, t h e
l a unc h ve h i c l e
w i l l
f i r e a n a u x i l i a r y p r o p u l s i o n s y st em (APS)
u l l a g e m o to r t o s e p a r a t e t h e v e h i c l e from t h e s p a c e c r a f t
a
s a f e d i s t a n c e . R e s i du a l l i q u i d oxygen i n t h e a lm o st s p e n t
S-IVB/IU
w i l l
th en be dumped through th e en gi ne
w i t h
t h e v e h i c l e
p o s i t i o n e d
so
t h e dump w i l l slow
i t
i n t o
an
i m p a c t t r a j e c t o r y .
M i d - c a u r s e c o r r e c t i ons
w i l l
be made
w i t h
t h e s t a g e ' s APS u l l a g e
motors
i f
n e c e s s a r y .
The S-IVB/IU w i l l weigh 3 0 , 8 3 6 pounds and w i l l b e t r a v e l -
i n g 4 , 9 4 2 na u t i c a l - m i l e s - a n - hou r
a t
impac t . I t
w i l l
pr ov i de
an
e ne r gy s ou r c e a t i mp a ct e q u i v a l e n t t o a b o ut 11 t o n s
of TNT.
ope r a t i ons a nd r e nde z vous e d
w i t h
t h e command module i n l u n a r
o r b i t , t h e
lunar
module asc en t s t a ge w i l l b e j e t t i s o n e d a nd
l a t e r ground-commanded t o impac t on the lu na r su r f ac e about
25 n a u t i c a l m i le s w e st o f t h e A p ol lo
1 5
l a nd in g s i t e
a t
Hadley-
Apennine.
w i l l
a s s i s t
i n c a l i b r a t i n g t h e A pollo
1 4
PSE readouts
as
w e l l
as
pro vid i ng compara t ive r e ad in gs between th e Apol lo
1 2
and
1 4
se i smomete r s fo rming the
f i r s t
t w o s t a t i o n s
of a lunar
s u r f a c e
se i smic ne twork .
A f t e r S c o t t a nd I r w in h av e c o mp le te d t h e i r l u n a r s u r f a c e
Impacts
of
t h e s e o b j e c t s
of
known masses and ve loc i t i e s
There a r e t h re e major ph ys i ca l component s of t h e PSE:
one
t e d
1.
The sens or as sembly co ns i s t s
of
t h r e e l o n g - p e r i o d and
s h o r t - p e r i o d v e r t i c a l s e is mo me te rs
w i t h
o r t h a g o n a l l y - o r i e n -
c a pa c i t a nc e - t ype s e i s m i c s e n s o r s , c a ? a b le of measur ing a long
two h o r i z o n t a l components and one v e r t i c a l component. The
s e ns o r a s s e m b l y
i s
mounted on a gimbal pl at fo rm . A magnet- type
s e n s o r s ho r t - pe r i od s e is m om et e r
i s
l o c a t e d
on
t h e b a s e
of
t h e
s e ns o r a s s e m b l y .
2 .
The l e v e l i n g s t o o l a l l o w s manual l e v e l i n g
of
t h e
s e ns o r a s s e m b l y
b y
t h e crewman t o w i t h i n
+ 5
d e g r e e s . F i n a l
l e v e l i n g t o w i th i n 3 a r c s e c o n d s i s acccmpl ished by c o n t r o l
motor s .
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- 4 4 -
ALSEP t o I mpact Di st ance Tabl e
Km St at ut e M l es
Appr oxi mat e Di st ance i n:
Apol l o 12 ALSEP
t o :
Apol l o 12 LM A/ S I mpact
Apol l o
13
S- I VB I mpact
Apol l o
14
S- I VB I mpact
Apol l o
14
LM
A/ S I mpact
Apol l o
15
S- I VB I mpact
Apol l o
15
LM A/ S I mpact
Apol l o 14 ALSEP t o :
Apol l o
14
LM A/ S I mpact
Apol l o
15
S- I VB I mpact
Apol l o
15
LM A/S I mpact
Apol l o 15 ALSEP t o:
Apol l o 15 LM A/ S I mpact
75 45
134
85
173
105
116 70
480 300
1150
710
67
300
1070
50
40
185
660
3
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-
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S - l V B / l U I M P A C T
30'
20O'l
I
g
loo
I
f
I
100s
200
w.
-
EA
OF R A I N S
L
*r
r
I
R EIN H O LD
I V B
IMPACT
+ POLLO
14
FR A M AU R O ,
20 E. 30E.
-
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3
h
20 N
10 N
0
10S
L M
ASCENT STAGE IMPACT
W .
zoo w. 1
EA
O/
A I N S
I
APOLLO
12$
LH ASCENT STAGE
IMF ACT
+ ++ + P O L L O O M
I
c
POLLO 12
I M P A C T
L M ASCENT
S T A G E I
F R A M A U R O I
a.
I
, ..
w., 0 10 E.
20
E.
No
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- 4 7 -
3 . The f i v e - f o o t d i a m e t e r h a t - sh a p e d t h e r m a l s h ro u d
c o v e r s a nd h e l p s
s t a b i l i z e
t h e t e m p e r a t u r e
of
t h e s e n s o r
a s s e m b l y .
The i n s t r um e n t u s es t h e r m o s t a t i c a l l y c o n t r o l l e d
h e a t e r s
to
p r o t e c t
i t
f ro m t h e e x t re m e c o l d
of
t h e l u n a r
f l i g h t .
T h e
L u na r S u r f a c e M ag ne to me te r (LSM): The s c i e n t i f i c o b j e c t i v e
of
the magne tome te r expe r imen t i s t o
measure
t h e m ag ne ti c f i e l d
a t
t h e
l una r s u r f a c e . - Ch ar ge d p a r t i c l e s and t h e m a gn et ic f i e l d
o f t h e s o l a r w ind i m p a c t d i r e c t l y on t h e l u n a r s u r f a c e . Some
of t h e s o l a r wind p a r t i c l e s
a re
a b s o r b e d b y t h e s u r f a c e
l a y e r
of t h e Moon. Ot he rs
may
be d e f l e c t e d a round t h e Moon. The
e l e c t r i c a l p r o p e r t i e s of t h e
m a t e r i a l
making up
t h e
Moon
d e t e r m i n e
what
happens to t h e m a g n e t i c f i e l d when
i t
h i t s t h e
Moon.
I f
t h e Moon
i s
a
p e r f e c t i n s u l a t o r t h e m agne t ic f i e l d
w i l l
p a s s t h r o u g h t h e Moon un di s t ur be d . If t h e r e
i s
mate r i a l
p r e s e n t which a c t s as
a
c on du c t or , e l e c t r i c c u r r e n t s
w i l l
f low
i n t h e Moon.
A
s m a l l m a g n e t i c f i e l d
o f
a p p r o x i m a t e l y
35
gammas,
one t h o u sa n d t h t h e s i z e o f
t h e
E a r t h ' s f i e l d
w a s
r e c o r d e d a t t h e
Apo l lo
1 2
s i t e . S i m i l a r
smal l
f i e l d s were r eco rded b y t h e p o r t a b l e
magnetometer on Apol lo
1 4 .
Two p o s s i b l e models
a r e
shown i n
t h e
ne x t d r awing . The
e l e c t r i c c u r r e n t c a r r i e d by
t h e
s o l a r wind g o es t h r o u g h t h e
Moon a nd " c l o s e s " i n t h e s p a c e s u r r o u n d i n g t h e Moon ( f i g u r e
a ) . T h is c u r r e n t ( E ) g e n e r a t e s a m a g n e t i c f i e l d ( M ) as shown.
The magne t ic
f i e l d
c a r r i e d i n t h e s o l a r wind
w i l l
s e t up a S y S -
tem
o f e l e c t r i c c u r r e n t s i n t h e Moon
or
a l o n g t h e s u r f a c e .
T h e s e c u r r e n t s
w i l l
g e n e r a t e a n o t h e r m a gn et ic f i e l d w hich t r i e s
t o c o un t e r a ct
t h e
s o l a r wind f i e l d ( f i g u r e
b ) . T h i s
r e s u l t s
i n
a
change i n t h e t o t a l m ag ne ti c
f i e l d
measured
a t
t h e l u n a r
s u r f a c e .
The m a gn it ud e of t h i s d i f f e r e n c e c an be d e t e r m i n e d by
i n d e p e n d e n t l y m e a s u ri n g t h e m a g n e t ic f i e l d i n t h e u n di s tu r be d
s o l a r w ind ne a r b y, y e t a w a y f r o m t h e M oo n' s s u r f a c e . The v a l u e
of t h e m a g ne t ic f i e l d change
a t
t h e M oon' s su r f ac e can be u sed
t o deduce i n f o r m a ti o n on t h e e l e c t r i c a l p r o p e r t i e s
of
t h e Moon.
T h i s , i n t u r n , can b e u sed t o b e t t e r u nd er s t an d t h e i n t e r n a l
t e m pe r a t u r e
of t h e Moon a nd c o n t r i b u t e t o b e t t e r u n d e r s t a n d i n g
of
t h e o r i g i n a nd h i s t o r y
of
t h e Moon.
The des ign of t h e t r i - a x i s f l ux -g a t e magne tome ter and
a n a l y s i s of e x p e r i m e n t da ta a re t h e r e s p o n s i b i l i t y o f
Dr .
P a l m e r
D y a l - NASA/Ames R es ea rc h Ce n t e r .
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I
P
co
I
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Y
.
- 4 9
-
The magnetometer consis ts
of
t h r e e m a gn et ic s e n s o r s
a l i g n e d i n t h r e e o r t h o g o n a l s e n s i n g a x e s , e ac h l o c a t e d a t t h e
end
of
a f i b e r g l a s s s u p p o r t
arm
ex tend ing f rom a c e n t r a l s t r u c t u re .
T h is s t r u c t u r e ho u se s b o t h t h e e xp er im e nt e l e c t r o n i c s a nd t h e
e l ec t r o- m e c ha n i ca l g i m b a l / f l i p u n i t which a l l o w s t h e s e n s o r t o
be p oi n te d i n
any
d i r e c t i o n for s i t e s u rv e y an d c a l i b r a t i o n modes.
The a s t ro na u t a l ig n s th e magne tomete r expe r iment
t o
w i t h i n +
3
d e g re e s e a s t -w e s t u s i n g a s ha do wg ra ph on t h e c e n t r a l s t r u c t u r e ,
and t o w i t h i n + 3 degrees o f t h e v e r t i c a l us i n g a b ub bl e l e v e l
mounted on t h e y s e n s o r boom arm.
Si ze , weight and power ar e
as
fo l l o w s :
S i z e ( i n c h e s ) d e pl o ye d 4 0 h i g h
w i t h
60 between
Weight (pounds)
1 7 . 5
Peak Power Requirements (wat t s )
s e n s o r h e a d s
S i t e Surv ey Mode 11.5
S c i e n t i f i c Mode 6 . 2
1 2 . 3 ( n i g h t )
C a l i b r a t io n Mode 1 0 . 8
The Magnetometer experiment operates i n three modes :
S i t e S urve y Mode --
An
i n i t i a l s i t e su rvey
i s
performed
i n e ac h
of
t h e t h r e e s e n s i n g modes
f or
t h e p u rp o s e of l o c a t i n g
a nd i d e n t i f y i n g an y ma gn et ic i n f l u e n c e s p e r ma ne nt ly i n h e r e n t
i n t h e deployment s i t e s o t h a t t h e y w i l l n ot a f f e c t th e i n t e r -
p r e t a t i o n of t h e
LSM
s e n s i n g of ma g n e t i c f l u x a t t h e l u n a r
s u r f a c e .
S c i e n t i f i c Mode
--
T h i s i s
th e normal o pe ra t i ng mode
w he re in t h e s t r e n g t h a nd d i r e c t i o n
of
t h e l u n a r mag netic f i e l d
a r e measured contynuous ly
.
The th r ee magne t ic s e nso rs p rov ide
s i g n a l o u t pu t s p r o p o r t i on a l t o t h e i n c i d e n c e of m a g n e t i c f i e l d
c o mp o n e n t s p a r a l l e l
t o
t h e i r r e s p e c t i v e a x e s . Each s e n s o r w i l l
r e c o r d t h e i n t e n s i t y t h r e e t i m e s p e r s e co nd w hich
i s
f a s t e r
t h a n t h e m ag ne ti c f i e l d
i s
expec ted t o change. Al l s e n s o r s h a v e
t h e c a p a b i l i t y
t o
sen se ove r any one of t h r e e dynamic rang es
w i t h
a
r e s o l u t i o n
of
0 . 2
gammas.
-100 t o t 100 gamma
- 2 0 0 t o +200 gamma
- 4 0 0
t o t 400 gamma
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s
-50-
*Gamma
i s
a
u n i t o f i n t e n s i t y of a magnet ic f i e l d . The
E a r t h ' s m ag ne ti c f i e l d a t t h e E qu a to r , f o r example, i s 35,000
gamma. The in te rp la n et ar y magnet ic f i e l d f rom t h e Sun has been
re c o rd e d a t 5 t o 1 0 gamma.
C al ib r a t io n Mode - T h i s
i s
p e r fo rme d a u t o ma t i c a l l y a t
1 2- ho ur i n t e r v a l s t o d e te r mi n e t h e a b s o l u t e ac cu r ac y o f t h e
ma gn et omet er s e n s o r s a n d t o c o r r e c t any d r i f t f r o m
t h e i r l a b -
o r a to r y c a l i b r a t i o n .
The S o l a r Wind Spec trom eter: The S o l a r Wind Sp ect rom ete r
w i l l m easu re t h e s t r e n g t h , v e l o c i t y an d d i r e c t i o n s of t h e
e l e c t r o n s a n d p r o t o n s which emanate from the Sun
and
reach
t h e l u n a r s u r f a c e . The s o l a r wind i s t h e m a jo r e x t e r n a l f o r c e
working on t h e Moon's s u r f a c e . The sp 'ectrometer measurements
w i l l
h e l p i n t e r p r e t t h e m ag ne ti c f i e l d o f t h e Moon, t h e
lunar
a t mo s p h e re a n d t h e a n a l y s i s of lunar samples .
Knowledge of t h e s o l a r wind w i l l h e l p u s u n d e r s t a n d t h e
o r i g i n
of
t h e Sun and t h e p h y s i c a l p ro c e s s e s
a t
work on the
Sun,
i . e . , t h e c r e a t i on and a c c e l e r a t i o n o f t h e s e p a r t i c l e s and
how they p ropaga te th rough in te rp la ne ta ry space . It has been
c a l c u l z t e d t h a t t h e s o l a r wind p u t s one k i l o t o n o f e ne rg y i n t o
t h e E a r t h ' s ma gn e ti c f i e l d e v e ry s ec o nd .
T h i s
enormous amount of
e n e rg y i n f l u e n c e s s u c h E a r t h p ro c e s s e s as t h e a u ro ra , i o no -
sphe re and weat her . Al though i t r e q u i r e s 20 m i n u t e s f o r a
k i l o t o n t o s t r i k e t h e Moon i t s e f f e c t s s h o ul d be a p p a re n t i n
many w a y s .
I n a d d i t i o n t o t h e S o l a r Wind Sp e c tro me t e r , a n i n de p en -
d e n t e x pe ri men t ( t h e Sol ar Wind Composition Experiment) w i l l
c o l l e c t t h e g a se s o f t h e s o l a r wind f or r e t u r n t o E a r t h f o r
a n a l y s i s .
The design o f t h e s p e c t r o m e te r a nd t h e s u b se q ue n t d a t a
a n a l y s i s a r e t h e r e s p o n s i b i l i t y of Dr . Conway Sn yder o f t h e
J e t P r o p u l s i o n L a b o r a t o r y .
Sev en i d e n t i c a l mo d i fi e d Fa ra d ay c u p s ( a n i n s t ru me n t
t h a t t r a p s i o n iz e d p a r t i c l e s ) a r e u sed t o d e t e c t and c o l l e c t
s o l a r w in d e l e c t r o n s a nd p ro t o n s . One cu p
i s
t o t h e v e r t i c a l ,
w h er ea s t h e r e ma in i ng s i x c up s s u rr o u n d t h e v e r t i c a l where
the ang le be tween t h e normals of any two adjacent Cups
i s
approx ima te ly 6 0 degr ees . Each cup measures th e cur re n t p ro -
duced
b y
t h e charged p a r t i c l e f l u x e n t e r i n g i n t o it . Since
t h e cu ps a r e i d e n t i c a l , an d
i f
p a r t i c l e f l u x
i s
e q u a l
i n
each
d i r e c t i o n , e q ua l c u r r e n t w i l l be p roduced i n each cup . If t h e
f l u x i s n o t e q u a l i n e ac h d i r e c t i o n , a n a l y s i s of t h e amount of
c u r r e n t i n t h e s ev en c up s w i l l d e te r mi n e t h e v a r i a t i o n o f
p a r t i c l e f low w i t h d i r e c t i o n . A l so , by s u c c e s s i v e l y c h a n gi n g
t h e v o l t a g e s on t h e g r i d of the cup and measur ing the correspond-
i n g c u r r e n t , c om pl et e e ne rg y s p e c t r a
o f
b o t h e l e c t r o n s a n d
p r o t o n s i n t h e s o l a r wind a r e p ro du ce d.
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?
-51-
Data from each cup
are
p r oc e ss e d i n t h e
ALSEP
d a t a
subsyste m. The measurement c y cl e i s o rg an iz ed i n t o 1 6
sequences
of 1 8 6
te n- bi t words . The ins t rum ent Neighs
12 .5
pounds,
has
a n i n p u t v o l t a g e
of
about
2 8 . 5
v o l t s a n d h a s an
ave rage inpu t power o f about 3 . 2
wat t s .
The measurement ranges
a r e
as
fo l l o w s :
E l e c t r o n s
High ga in modula t ion
1 0 . 5 -
1 , 3 7 6
e . v . ( e l e c t r o n
Low ga in mod ul ati on
6 . 2 -
8 1 7
e . v .
v o l t s )
Pro tons
High ga in modula t ion
75 -
9 ,600 e . v .
Low ga in mo dul atio n 45 -
5 ,700 e . v .
F i e l d o f
V i e w 6 . 0
S t e r a d i a n s
Angula r Reso lu t ion 15 d e g re e s ( a p p ro x i ma t e l y )
Minimum Flux Detectable 10 p a r t i c l e s / c m / s e e
Supra t hermal Ion Dete ,c tor Exper iment (SIDE) and Cold
6
2
Cat hod e Gauge Exp erim ent The SIDE w i l l measure f l u x , com-
p o s i t i o n , e n e rg y a nd v e l o c i t y
of
l ow -e ne rg y p o s i t i v e i o n s
a nd t h e hi g h-e ne rgy s o l a r w in d f l u x
o f
p o s i t iv e io ns . Combined
w i t h t h e SIDE i s the Cold Cathode Gauge Experiment ( C C G E ) f o r
m e a s u r i n g t h e d e n s i t y
of
t h e l un ar ambient a tmosphere and any
v a r i a t i o n s w i t h t ime or s o l a r a c t i v i t y such a tmosphere may have .
Data
g a t h e r e d
b y
t h e
S I D E
w i l l
y i e l d i n f o r m a t i o n o n:
1)
n t e r a c t i o n b et w ee n i o n s r e a c h i n g t h e Moon f rom o u t e r s p a c e
and c a p t u re d by l u n a r g r a v i t y an d t h o s e t h a t escape ; 2 ) whether
or
n o t s ec on d ar y i o n s a r e g e n e r a t e d
b y
i o n s im p ac ti ng t h e l u n a r
s u r f a c e ;
( 3 )
whether vo l can i c p r oces ses e x i s t on th e Moon;
( 4 ) e f f e c t s
of
t h e a mbient e l e c t r i c f i e l d ; ( 5 ) l os s r a t e o f
c on ta mi na nt s l e f t i n t h e l a n d in g a r e a
b y
t h e
LM
and the crew;
and ( 6 ) a mbi en t l u n a r a tmo sp h ere p r e s s u r e .
D r .
John Freeman
of
R i c e U n i v e r s i t y
i s
t h e
S I D E
p r i n -
c i p a l i n v e s t i g a t o r , and D r . F r a n c i s B . Johnson o f t h e U n i v e r s i t y
of
Texas i s t h e
C C G E
p r i n c i p a l i n v e s t i g a t o r .
The
SIDE
i n s t r u m e n t c o n s i s t s
of
a v e lo c i t y f i l t e r ,
a
lo w-en ergy c u rv e d -p l a t e a n a l y z e r i o n d e t e c t o r a nd a high-energy
c u r v ed - p l at e a n a l y z e r i o n d e t e c t o r ho us ed
i n a
case measuring
15 . 2 by 4.5 b y 13 i n c h e s , a wi re mesh ground pl an e , and e l ec -
t r o n i c c i r c u i t r y t o t r a n s f e r d a t a t o t h e
ALSEP
c e n t r a l s t a t i o n .
The S I D E c a s e r e s t s on f o l d i n g t r i p o d l e g s . Dust c o ve r s, r e -
l ea sed by g round command, p r o te c t bo t h ins t rum ents . To ta l
S I D E weight i s
1 9 , 6
pounds.
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*
The
SIDE
a n d t h e CCGE connected
by
a s h o r t c a b l e ,
w i l l be deployed about 55 f e e t n o r t h e a s t o f t h e ALSEP c e n t r a l
s t a t i o n , w i t h th e SIDE a l igne d ea s t or wes t toward the subea r th
p o i n t a n d t h e CCGE o r i f i c e a l i g n ed a l o n g t h e n o rt h- so u th
w i t h
a
c l e a r f i e l d a w a y from o t h e r ALSEP in st ru m en ts and
LM
.
The
Cold
Cathode Gauge on Apollo 1 4
i s
measuring a
t o r r (where m e t o r r
i s
e q u a lr e s s u r e o f
1 0
t o
1 0
one mil l imeter of mercury and
7 6 0
mil l ime te rs o f mercury
equal one
E a r t h
a tmosphere ) .
-12
l i n e
t h e
t o
Lunar Heat Flow Experiment (HFE): The s c i e n t i f i c o b j e c t i v e
o f
the Heat Flow experiment
i s
t o m easur e t h e s t e a d y - s t a t e h e a t
f lo w from t h e l u n a r i n t e r i o r . Two p r e d i c t e d s o u r c e s of h e a t
a r e : (1) o r i g i n a l he a t
a t
t h e t i me o f
t h e
Moon's formation
and ( 2 ) r a d i o a c t i v i t y . S c i e n t i s t s b e l i e v e t h a t heat could have
been gene ra ted b y t h e i n f a l l i n g of m a t e r i a l a n d i t s subsequent
compaction
a s
t h e Moon was formed. Moreover, va ry in g amounts
of t h e - ra d i o ac t i ve e lements u ran ium, thor ium and po tas s ium were
f ou nd p r e s e n t i n t h e A po ll o
11
and
1 2
lunar samples which
i f
p r e s e n t a t dep th , would supp ly s i g n i f i ca n t amounts of he a t . No
simple way
.Mas
been dev i sed for r e l a t i n g t h e c o nt r ib u t i o n of
e a ch of t h e s e s o u r ce s t o t h e p r e s e n t r a t e o f h e a t
l oss .
I n
a d d i t i o n t o t e mp e ra t ur e , t h e e x p er im e nt i s capable of measur ing
t h e t he r m al c o n d u c t i v i t y o f t h e l u n a r r oc k m a t e r i a l .
The combined measurement of temperature and thermal
c o n d u c t i v i t y g i v e s t h e n e t h e a t f l u x f ro m
t h e
l un ar i n t e r i o r
th rough th e luna r su r fa ce . S i mi la r measurements on
E a r t h
have
c o n t r i b u t e d b a s i c i n f or m a t i o n t o o ur u n de r st a nd i ng o f ,vplcanoes ,
ea r thquakes and mounta in bu i l d in g p ro ces s es . In con j .unc t ion
w i t h t h e s e i s mi c a nd ma gn et ic d a t a o b t a in e d on o t h e r l u n a r e x p e r i -
ments t he va lues de r ived f rom th e he a t f low measurements w i l l
h e l p
s c i e n t i s t s t o b u i l d more e x a c t m odels o f t h e Moon and
the reby g ive us
a
b e t t e r u n de rs ta nd in g o f i t s o r i g i n a n d h i s -
t o r y .
The
Heat Flow
e x pe r ime n t c o n s i s t s o f i n s t ru me n t p ro b e s,
e l e c t r o n i c s a nd emplacemen t t o o l a nd t h e l u n a r s u r f a c e
d r i l l .
Each
of two
p r o b e s i s
connected
b y a
c a bl e t o an e l e c t r o n i c s
b ox wh ich r e s t s on t h e l u n a r s u r f a c e .
The
e l e c t r o n i c s , w h i c h
p ro v i d e c o n t ro l , mo n i t o ri n g a nd
da ta
p r o c e s s i n g
f o r
t h e e x p e r i-
men t, a r e co n ne ct ed t o t h e ALSEP c e n t r a l s t a t i o n .
Each p robe cons i s t s of two i d e n t i c a l 2 0- in ch
(50 Cm)
l o n g s e c t i o n s e a c h o f wh ich c o n t a i n s
a
"g ra d i e n t " s e n s o r b r i d g e ,
a
" r i n g " s e n s o r b r i d g e an d two h e a t e r s . Each b r i d g e C o n s i s t s
o f
f o u r p l a ti n um r e s i s t o r s m ounted i n
a
t h i n - w a l l e d f i b e r g l a s s
c y l i n d r i c a l s h e l l . A dja ce nt a r e a s of t h e
b r i d g e
a r e l o c at ed i n
s e n s o r s
a t
o p p o s i t e e n d s of t h e 2 0- in ch f i b e rg l a s s p ro b e s h e a t h .
G ra d i e n t b r i d g e s c o ns e qu e nt l y mea su re t h e t e mp e ra t u r e d i f f e r e n c e
between t w o s e ns o r l o c a t i o n s .
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-
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.
.
-5
3-
PROBE PACKAGE
ELECTRONICS PROBE CARRYING PACKAGE
CABLE TRAY PACKA GE
(CONTAINS
2
PROBES 8
\ I
EMPLACEMENT TOOL)
THERMAL
I CABLE BRACKET
MASK
REFLECTOR REMOVED DU RIN G
DEPLOYMENT
LUNAR RADIATION
HEAT FLOW EXPERIMENT
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-
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.
I
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In the rmal conduc t iv i ty measurement s
a t
very low
v a l u e s
a
h e a t e r s u r r o u n d i n g t h e g r a d i e n t s e n s o r
i s
e n e r g i z e d
w i t h
0 . 0 0 2 watts
and t h e g r a d i e n t s e n s o r v a l u e s m o n it o re d .
The r i s e i n t e m p er a tu r e
of
t h e g r a d i e n t s e n s o r
i s
a
f u n c t i o n
o f t h e r m a l c o n d u c t i v i t y of t h e s u r r o u n d i n g
lunar
m a t e r i a l .
For
h i g h e r r a n g e
of
v a l u es , t h e h e a t e r i s e n e r g i z e d a t 0 . 5
watts
of hea t and moni to red by
a
r i n g s e n s o r . The r a t e of
t e m p e ra t u re r i s e , m on it or ed by t h e r i n g s e n s o r
i s a
f u n c t i o n
of t h e t h e r ma l c o n d u c t i v i t y
of
t h e s u rr o un d in g l u n a r m a t e r i a l .
The r i n g sen sor , approx imate ly
