19740077565_1974077565
TRANSCRIPT
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A T I O N A L A E R O N A U T I C S A N D S P A C E A D M I N I S T R A T I O N
V
M S C INTERNAL
NOTE NO. 66-FM-122 ,&\\ -
4
October 21 1966
I
FLIGHT
CREW
LAUNCH
q @RT
MODE
SELECTION
CHAPS
OR
MISSION AS-204A
B Y B o b b i e D . W e b e r
F l i g h t A n a l y s i s B r a n c h
, I* (NASA-CR-7C392) F L I G H T CREW LAUNC H
A B O R T
*:iaOCE S E L E C T I O N CHARTS
F O R
M I S S I O N A S - L C 4 A
: : ( N A S A ) 48 p
.
7 4 - 7 5 5 6 4
Unclas
0 0 / 9 9
16635
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I.
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' M A N N E D S P A C E C R A F T C E N T E R
H O U S T O N , T E X A S
I
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e
. . :b I SS I ON P L A N N I N G A N D A N A L Y SIS D I V I S IO N
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c
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MSC INTERNAL NOTE NO. 66 -F M- 12 2
PROJECT APOLLO
FLIGHT CREW LAUNCH ABORT MODE SELECTION
CHARTS
FOR
MISSION AS-204A
By Bobbie D. Weber
F i igh t Anaiysis Branch
October
21,
1966
MISSION PLANNING AND ANALYSIS DIVISION
NATIONAL AERONAUTICS AND SPACE ADMINISTRATION
MANNED SPACECRAFT CENTER
HOUSTON, TEXAS
Approved: c .?. / LL
Claiborne R. Hicks,
Jr.
, Chief
FI
ght Analysis Branch
Approved:
John P(r\ Mayer, Ch ie f
I
Mi ss iov Planning and Analysis Divi sion
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FIGURFS
Figure Page
1
Fl igh t - cont r o l t r a je c to r y da ta a s a f unc tion
of i n e r t i a l v e lo c i ty and i n e r t i a l f l i g h t -
pa th angle a t
s-IVB
cu to ff pl us 1-5 seconds
assuming CSM/S-IVB se pa ra ti on ha s occu rred
. . . . . 9
2
3
6
Fl ight-contro l t r a jec tor y da ta as a func t ion
of t ime of f re e fa l l and perigee a l t i t ud e a t
S-IVB cutoff plus
15
seconds assuming CSM/S-IVB
sep ara tio n has occurred.
(a ) Af te r Separa t ion
-
Scale
I . . . . . . . . . . 10
b ) After Separation
.
cale
I1
. . . . . . . . . .
u
( c )
After
Separation
.
cale
I11
. . . . . . . . . .
2
Fl ig h t con t r o l t r a jec to r y da ta a s a f unc t ion of
apogee a l t i t u d e and perigee a l t i t u d e a t S-IVB
cutof f p lus
15
seconds assuming CSM/S-IVB
sep ara tio n has occurred
( a ) After Separation - Sca le
I
.
13
( b )
After Separa t ion . cale I1
. . . . . . . . . . 15
(c ) Af te r Separa t ion
.
cale
I11
. . . . . . . . . .
17
( d ) After Separation
.
cale . . . . . . . . . .
19
Fl igh t - con t r o l t r a jec to r y da ta a s a function of
i n e r t i a l v e l o c i t y and i n e r t i a l f l i g h t -p a t h a ng le
a t
S-IVB
cutof f p lus
15
seconds assuming CSM/S-IVB
sep arat ion occurs a t S-IVB cu tof f plus
45
seconds
.
21
Fl igh t - con t r o l t r a jec to r y da ta a s a f unc t ion
of t i m e
of f r e e f a l l and pexigee a l t i t ud e a t S-IVB cutoff
p lus
15
seconds assuming CSM/S-IVB se para t ion occ ur s
a t S-IVB cutoff plus 45 seconds.
(a ) Before Separation - Scale
I
. . . . . . . . . 22
(b) Before Separation . ca le I
. . . . . . . . . 2 3
( c ) Before Separtaion
.
ca le
111
. . . . . . . . .
24
Flig ht-co ntrol tr a j ec to ry data as a funct ion of apogee
a l t i tu de and per igee a l t i tu de a t S-IVB cutof f
plus
15
seconds assuming CSM/S-IVB sepa ra t ion occurs
a t
S-IVB cutoff plus 45 seconds.
iii
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Figure
( a) Before Separat ion - Scale I . . . . . . . .
b ) Before Separation - Scale I
.
.
. .
(c ) Before Separa t ion
-
Scale 111
. . . . . . .
( d )
Before Separation
-
Scale I V .
.
. . . . . .
i
AGC/DSKY
display s ava i lab l e fo r onboard a bor t
mode s e l e c t i o n . . . . . . . . . . . . . . .
25.
27
29
3 1
33
iv
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FLIGHT CREW
LAUNCH
ABORT MODE SELECTION
CHARTS
FOR MISSION
AS-204A
By Bobbie D . Weber
SUMMARY
This paper presents launch abort mode se le ct io n ch ar ts t o be used
by the
AS-204A
crew i n se le ct in g the appr opr iate launch abo rt mode
i f
an abor t s i t ua t i on develops fo lluwing the loss of ground-to-air com-
munications.
Various parameters ar e presented a s funct ions of apogee al t i t u d e
(ha ) , per igee a l t i t u de (h ) and t ime-of-freefal l ( T f f , time remaining
above 300 000 f t ) .
These parameters a r e computed by t h e Apollo guid-
ance computer (AGC) and d isplayed i n the re gi s t e r s of the d isp la y and
keyboard (DSKY) panel . I n add itio n, the parame ters a r e prese nted as
f u nc t io n s o f i n e r t i a l v e l o ci t y and i n e r t i a l f l i g h t - p a t h a n gl e t o pr ov id e
a more fa mi l i a r and an ove ra l l appr a isa l of th e near - inser t i on abor t
regions.
P
INTRODUCTION
During the second qua r t e r
of
t h i s ye ar , t h e
AGC
launch abort
se le c t io n programs ( re f .
1)
were removed from t h e guidance and n aviga -
t i o n (GN)
system operat ions plan f o r mission
A s - 2 0 4 A
t o provide addi-
t i o n a l computer s to rage f o r AGC programs which co nt ri bu te more t o the
nominal mission.
mission,
it
was appa rent t h a t t h e crew needed some means of s e l e c t i n g
th e a ppr opr iate launch abo rt mode t o use i f ground-to-air communications
are l o s t
To provide more onboard c ap a b i li ty f o r th e AS-204A
A t f i r s t ,
it
was thought the crew could as sess an abort s i t u a t i o n
e n t i r e l y w it h t h e AGC by observing the DSKY re g i s t e r dis pl ay s i n programs
2
and 7 1 and th e o r b i t a l maneuvering programs ( r e f . 2 ) .
The parameters
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2
a v a i l a b l e ( d i s p b y e d )
the d i s c r ete r ecove n
p ha tff
n th es e programs would have inc luded h
area (DRA, landing range of 3200 n. m i . )
miss
d is tance AR), nd the velocit y-change requi red t o achieve a contingency
o r b i t t a r g e t (AV). However, it was determined t h a t th e procedures
required
t o
a ss es s t h e ab or t s i t u a t i o n i n
i t s
e n t i r e t y and t h e n t o
per-
form th e t as ks nec essa ry f o r a given ab or t mode would
be
t o o time con-
suming.
With the displays presently available the crew can monitor the
AR display sequence t o S-IVB cutoff t o determine whether t o a bor t
using abort mode 11--separation and fu l l - l i f t entr y--o r using abor t mode
111--separation,
e n tr y t o t he
DRA.
(For thorough def in it io ns of th e abo r t modes, cons ult
r e f .
3
and 4 ) .
grea t e r than ha l f the foo tpr in t length (wi th AR nega t ive) .
abor t ,
w i t h
no SPS burn, can be performed when AR i s e qu al t o o r
less
than ha l f the foo t pr in t length (wi th
AR
negative), and a mode
I11
abor t ,
with an SPS re tr og ra de maneuver, can be performed when AR
i s
gr ea te r
than zero (AR positive). The
SPS
maneuver would terminate when the
nR di sp la y equa ls zero. However, th e primary ab ort mode f o r approx-
imately the l a s t 27 seconds of S-IVB f l i g h t i s mode I V (contingency
o rb i t ins er t io n) . Along the nominal tr a j ec to ry , mode I V c a p a b i l i t y
e x i s t s pr io r t o mode II/mode I11 switchover.
able display s , the crew can only guess whether they have s u ff i c i e nt
AV
t o perform contingency or b i t inse r t io n .
service propulsion system
(SPS)
bur n, and a h a l f - l i f t
A
mode I1 abort can
be
performed when
AR i s
equa l o r
A
mode
I11
Using the presen t ly av a i l -
The enclosed c har tsh ave been generated t o be used i n conjuncti on
w i t h t h e
DSKY
r e g i s t e r d i s p l ay s t o a ll ow t h e
crew t o assess an abor t
s i tu at io n, s e l e ct an abor t mode, and provide app ropr ia te data f o r the
abo rt maneuver, i f requi red.
EXPLANATION OF CHARTS
Two s e t s
o f
c ha rt s have been provided. The
f i r s t sc
f igu r e s
1
hrough 3 , pr esent f l i gh t con t r o l t r a j ec to r y da ta assum ig CSM/S-IVB
separation has occurred.
The second set, f igures
4
through 6, present
f l i gh t cont ro l t r a je c t or y da ta assuming separa t ion has no t occur red
b u t
r e f l e c t i ng the s imu lat ion o f s epa r a t ion occur r ing a t S-IVB cu to f f
plus
45
seconds. (The ef fe ct of separa tio n occurr ing subsequent t o
43 secoxds but pr io r t o S-IVB cuto ff plus 123 seconds i s considered
negl ig ib le . )
A l l
dat a presented a re based on cond iti ons a t S-IVB cut off
p lus
15
seconds.
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3
A thorough explan at ion of th e enclosed f ig ur es can be st be pre-
sented by def in in g the abor t reg ions and f l igh t -c on t ro l l in es g iven
i n f i g u re s 1 nd 4. The remaining fi g u re s are simply conversio ns of
the data presented on f igures 1and
4
t o func t ion s of h and
T f f
o r
h and ha.
Figure 7 presents the AGC/DSKY display s which ar e a va i l -
ab l e fo r u se w i t h f i g u r e s 2 and
3
o r
5
and 6 f o r s e l e c t i n g an a b o r t
mode. Seve ra l examples
w i l l
be p re sented t o c l a r i f y the app l i ca t ion
of t he f igu res i n se lec t in g the appropr ia te abor t mode.
P
P
Def in i t ion
of
Abort Pegions m l
Fli,.ht-Contrd
Lines ( f igures 1 nd 4 )
Following i s a l i s t of the f l i gh t - co n t ro l l i ne s used i n f igu res
1 nd
4:
1 The Mode II/mode I11 swi tchove r ( f u l l - l i f t l and ing r ange =
3200 n.
m i . )
l i n e .
of
t h i s
l i n e ,
a
mode I1 abor t w i l l be performed. For any
V
t h e l e f t of
t h i s
l i ne ye t i n s ide r egion
B,
the primary abort mode w i l l
be mode
I V.
For any
Vi,
Yi outs ide region B and t o th e l e f t
Yi t o
i
2.
The Mode I11 ( h a l f - l i f t l a nd i ng ra ng e = 3200 n. m i . ) " l i n e .
For any
Vi,
vi outside region B, and between t h i s l in e and l i n e
1,
a
mode
I11 abor t w i l l be performed which w i l l require no SF S r e t rog rade
burn. For any
Vi,
yi
between
t h i s
l i ne and l i ne
1
yet ins ide region
B, the primary abort mode w i l l be mode IV.
of t h i s l i ne , an Africa impact can
be
avoided by performing a re t ro -
grade maneuver.
r e s u l t s i n a l an d in g a t t h e
DRA.
For any
Vi,
yi t o t he r igh t
(The normal procedure re qu ire s th a t th e SF'S maneuver
3.
The
"nv,, + AVm
t o d e o rb it a t h
2800 fps l i ne .
the negat ive and pos i t iv e f l i&t-pa th-ang le reg ions .
of contingency o rb i t
i s
P
Self-explanatory.
This
l i n e bounds regio n B i n b o th
4. The Nominal t ra c e a t S - 1 ~ 6 u to f f +
15
sec. l in e . On
f i g u r e
1,
t h i s l i n e
i s
based on the assumption th a t sep ar at i on has
occurred
.
5 .
The Ar riv al a t apogee conici des wi th C Y 1 AOS based on 3
e l e v a t i o n ( T i m e t o ha
>
8 min) l ine .
t h e
spacec ra f t w i l l a r r i v e a t a pogee c o i n c i d e n t i a l w i t h t h e
C Y I t r a c k i n g
For any Vi, Y along t h i s l i n e
1
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4
s t a t i o n AOS. I f t he s pac ecr af t has lo s t ground-to-air communications
as a r e s u l t o f a ground problem ra th er tha n an onboard systems p r o b l q
the crew could await C Y 1
AOS
before
performing an abort maneuver when
th e i r abort so lu t ion p l aces them e i th e r on
o r
t o t h e r i g h t of t h i s l i n e .
6. The Time t o apogee, Ta, min. l ine. Self-explanatory.
7. The '% =
75
n. m i . l ine . Se l f -explana tory .
8.
The ha = 500 n. m i . l ine . Se l f -explana tory .
9.
The
Sum
of ve loc i ty change a long the t h r us t ax i s r equi r ed t o
achieve h = 75 n. m i . , nVINS f
ps
. l i n e .
P
t h e s e l i n e s (AV = 0 t o AV = 2400 fps, ) t h e AV t o apply a t S-IVB cutof f
plus 125 seconds
i s
gi ven. The maximumAV pre sente d f o r mode I V abor t s
i s 2400 fps.
This data assume8 the posigrade maneuver
w i l l
be performed a t a fix ed
a t t i t u d e
of 31.7
between the l ine-of -s ight t o the hor izon and th e X
body axi s wit h th e crew i n a heads-down po sit ion .
P
For any
Vi,
Yi on one of
This l i n e bounds region B i n t h e l ow ve loc i ty r eg ion .
The regions on fi gu re s 1and
4 are def ined
a s
fol lows:
1
Region A
- For
any Vi, yi i n r e gi o n A (bounded by lines
1, 2,
and 3 ) t h e primary mode of a bo rt
i s
abort mode
I11
with no
SPS
r e t r o -
grade maneuver.
2. Region
A -
For any V Y i n r eg io n
A '
(bounded by lines 2
and
3
fo r negat ive f l i gh t - pa th ang le s and l i n es
2,
3 ,
and
5
f o r p o s i ti v e
fli gh t-p ath an gle s) the primary mode
of
abor t i s abor t
r
de 111, which
requires an
SPS
retrograde maneuver.
if
i
3 . Region B - For any V Yi i n r eg io n B (bounded lines 3 , 5,
i
and
AV =
2400 f p s ) th e primary mode of a bo rt i s a b o r t
r equ i r e s a SPS posig rade maneuver a t 125 seconds a f t e r S-IVB cu to ff .
xle
I V ,
which
4 Region C - ( f i g u r e 4 only) For any Vi, Yi i n r eg ion C (bounded
by the AVINs
= 0
l ine and the h
= 75-11.
m i .
l i n e ) , t h e AV irnparted
P
by the normal separation sequence
w i l l
assu re a s a fe o rb i t .
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5 .
Region D - For any V
?. i n r eg ion D (bounded by lines 3, 5,
i
1
and 7 ) , the crew can perform an
SPS
pos igr ade maneuver a t S-IVB cu to ff
plus 125
seconds and have s uf f i ci en t f u e l reserve t o deo rbi t . However,
the primary procedure would be
t o
perform a maneuver
a t
apogee t o r a i se
p er ig ee t o 75 n.
m i .
6.
Region E - For any
Vi,
yi i n r eg io n E (bounded by lines 3
and 5 , the primary procedure
w i l l
be f o r th e crew t o perform a man-
euver a t apogee t o r a i s e p er ig ee t o 75 n.
m i .
7.
Region F - For any V
required. A safe perigee i s assured.
Yi i n r eg io n F no immediate action i s
i
h -Versus-T
Charts ( f igures 2 and
3 )
P f f
A s indica ted previous ly , a l l ch ar t s a re based on
a
f ixed t ime
from S-IVB cu to ff (S-IVB cu to ff p lu s 15 seconds). I f DSKY re g i st e r
d i sp l ays
(
of h
15 seconds are used t o solve the abor t problem, the re su l ts w i l l be
wrong unle ss some ot he r time re fer enc e i s u t i l i z e d (ref.:, and 6).
However, reference 6 i nd ica t e s t ha t t h i s p rob lem can be compensated
f o r i f t h e d i g i t a l event t i me r (DET) i s a lways r es e t t o zero a t S-IVB
cu to ff . Using the DE T rea din g and th e DSKY di sp la ys (h T f f ) wi th
th e h -versus-Tff ch art s, th e abort problem can be solved f o r any
time following S-IVB cu to f f
unt i l
S-IVB cutoff plus
s:
econds. The
h t o be used i s th e h dis pla yed by th e DSKY r e g i s t e r . The T f f t o
be used i s t h e T f f displayed by t h e DSKY plus t h e DE T rea din g minus
15
seconds. The fol low ing examples w i l l c l a r i f y t h e u se of hp, Tff
ch ar ts and th e importance of using th e
Dm7
readings.
T f f ) other than those occurr ing a t cutof f p lus
P
P
P
P
P
Suppose some imminent cata str oph e ca use s th e as tr on au t t o send
an abor t d i sc re e t which w i l l s h u t the S-IVB engine
d a m a n d i n i t i a t e
the separa t ion sequence. In t h i s case , the DET i s au toma t i ca l ly r e se t
t o z er o.
Then, suppose a t S-IVB cu to ff pl us 45 seconds the astronaut
reads t h e DSKY r e g i s t e r dis pl ay s and recor ds h
minutes 30 seconds. I f t he se va lues ( f i g . 2), were used t o so lve th e
abo rt problem, the ast ron aut would see t h a t h i s primary a bor t mode
i s
mode I V , which requires 1700 fps. Or, he could perform a suborbital
=
-625 n.
m i . ,
T f f
=
0.5
P
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abort via mode
11.
But, t h i s so lu ti on would be wrong because read-
ings a t o ther than the f ixed t ime were used.
so lu t i on the astr onau t would need t o add
30
seconds t o t h e
Tf f
reading.
(The DET would read 00 minutes
45
seconds).
I f the as t ronaut uses these va lues
t o
solve the abort problem,
he
w i l l
see that the mode I V burn requires only
1600
fps .
a su bo rb it al abor t v ia mode 111. I n
t h i s
case the choice between
l7OO fps and I600 f p s o r s u b o r b i t a l a b or t
modes
would not be c ata str oph ic.
But
the
as t ronaut m i g h t make an unwise decision
if
t h e
DET
i s not used
near the mode I V bounda ries. Such a de ci si on would result i n e i t h e r
achievin g a contingency o r b i t from which de or bi ts nea r perige e could
not
be
performed or performing a s u b o r b i t a l ab or t when mode
I V
capa-
b i l i t y e x i s t e d .
To ge t the co r re c t
Then, Tff would be 06 minutes.
O r , he can perform
The use of the h -versus-T ch ar t s has o ther l im i ta t io ns . S ince
P f f
T f f
i s
a conica l so lu t ion of t ime t o
300
000
f t ,
t he re ex i s t s no
solu-
t i o n s f o r Tff when h of the p re sen t o rb i t i s g r e a t e r t h a n 300
000
f t .
Also, t he re i s a so ftware r e s t r i c t i o n l im i t ing the va lue o f Tff d i s -
played t o '39 minutes 59 seconds . These re s t r i c t io ns a re indica ted
on scale I11 [figures 2 ( c ) and 5(c)] of the
h
-versus-Tff charts .
P
P
h -Versus-ha Charts (f ig ur es 3 and 6 )
P
h -versus-ha char t s a re not subjec t t o the l i mi t a t i ons indica ted
i n th e previous paragraphs. However, th ey ar e su bj ec t
to
o the r r e s -
t r i c t i o n s when bein g used t o solve th e abor t problem. 1 ? fol lowing
example w i l l c l a r i f y
t h e
use of thes e ch art s , point out 'Lie r e s t r i c t -
ions on
i t s
use, and show how thes e re s t r i c t io ns a re com' nsa ted for .
P
For
t h i s
example assume th e same ev en ts occu r a s abovi bu t suppose
= 67 n. m i . , ha = 248 n. m i .
a t S-IVB cutoff plus 4'3 seconds the as t ronaut reads the
DSKY
r e g i s t e r
dis pla ys and records h
values t o solve the abo rt problem the astr onau t would f in d two
solu-
t io ns t o
t he
abort problem [ i g u r e 3(d)] .
hal f of the cha r t would indic a te th a t 300 f p s would be needed for a
mode I V burn. The so lu ti on i n th e lower ha lf of th e ch ar t would in-
di c at e t h a t only 200 fp s would be needed f o r a mode I V burn.
Also,
i f the so lu t ion in the lower ha l f of the ch ar t i s corre c t , the burn
would have t o
be
applied a t S-IVB cuto ff plu s
125
seconds.
s o l u t i o n
i n
the upper half of t he cha rt
i s
co rr ec t, th e mode I V burn
can be applied a t S-IVB c uto ff plus
125
seconds, or a burn of about
20 fps can be app lied a t apogee (which i s more than 2'3 minutes away)
Using these
P
The s olu t io n i n the upper
If t h e
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7
t o
ra i se
p er ig ee t o
75
n.
m i .
To help them determine which sol uti on t o
use,
the as tro naut s have av aila ble a disp lay of t ime t o per igee
( T ) .
P
For t h i s example the T
To avoid
the appl ica t ion of
s t i l l
another chart,
a
cons tan t o r b i t a l pe riod of
90
minutes
w i l l
be assumed f o r
all
cases when using the
h
h char ts .
Therefore, when T
half of th e ch ar t w i l l be used, and when
T i s less
than
45
minutes the
so lu t ion i n th e lower ha l f of th e char t
w i l l
be used.
I n t h i s example,
LIE S U L U I ~ ~n
the
i i p ~ r ;
a l f of the char t shcdd be used.
procedure would be t o apply
a
burn at apogee, approximately
33
minutes
from S-IVB cutoff ( T
The ast ron aut s would a l so have an opportunity t o re-e sta bl ish ground-
t o -a i r communications as th ey passed over
CYI .
di sp la y would read about
78
minutes.
P
P'
a
i s
more than 45 minutes th e solut ion i n the upper
P
P
L1.- 7 . L
The
primayJ7
-
45
minutes ), t o r a i s e pe rigee t o
75
n. m i .
P
CONCLUSION
The enclosed data are altitude-dependent. A U da ta were generated
assuming the nominal a l t i t u de a t
S-IVB
cutof f
.
curves
a r e the r e f o r e conse rva tive f o r pos i t ive a l t i tu de d i spe r s ions
and unconservative f o r negative al ti tu de disp ersio ns. When e i t h e r
se t
of char ts (h
t o the abo rt problem can be found i f some time r efe ren ce
i s
used
( e i t h e r DET read ings or
T
display) .
The mode
I V AVms .
versus
Tff
or h versus h ) are used,
a
unique solution
P P
a
P
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9
VI
-0
c
U
al
m
m
VI
m
m
sr
L
u
c
-
.-
E
a
37
L L
._
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10
c
. _
E
IL
LL
t
-
m
aJ
L
E
L
L
W
E
t-
._
21
20
19
18
17
16
15
14
3
12
11
10
9
8
7
6
f
VINS= 2400
fps
-2000 -1750 -1500
-1250 -1000 -750 -500 -2 50
Perigee alt itude, h n. mi.
P'
(a) After separation
-
Sca le
1
F igure
2 . -
Flight-control trajectory data as a function
o f
t ime of f reefal l and per igee al t i tude a t
S-IVB
cutoff p l u s 15 seconds assuming CSM/S-IVB separation has occurred.
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11
S
.-
E
LL
LL
I-
-
m
al
L
2
-
E
I-
1500 -450 -400
-350
-300 - 2 5 0 - 2 0 0
-15;
Perigee alt itude, hp, n. m i .
(b)
Afte r separation Scale II
Figure 2. Continued.
-
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12
c
.
E
LL
LL
I-
-
m
L
.-
L
L
0
I-
94
84
74
64
5 4
4 4
3 4
32
3 0
28
2 6
24
22
2 0
1 8
1 6
1 4
1 2
1 0
a
6
a
94
8 4
74
64
54
44
34
32
30
28
26
24
2 2
20
1 8
1 6
1 4
1 2
10
8
6
4
-200 -160 -120 80 -4
0
0 4 0 8 0
Perigee alt itude, h n . mi.
P
(c) After separation
-
Scale I l l
Figure 2.- Concluded.
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Perigee alti tude, h n. mi.
P'
- 1 1 0 0 - 1 0 0 0 - 9 0 0 - 8 0 0 -7 0 0 - 6 0 0
100
9 9
98
9
9 6
9 5
9 4
9 3
9 2
9 1
9 0
8 9
.-
E
c
.
m
-c
.
a
3
8 8
.
-
m
a
a
m
0
Q
a
landing
LMode IV boundary&
- 5 0 0 - 4 0 0
100
9 9
98
97
9 6
9 5
94
93
92
9 1
9 0
8 9
D
U
0
CQ
rD
m
E
F r
8 8 g
m
.
s
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600
Perigee alt itude,
h
n. mi.
P '
AS- 204
400 -3 00 200 -1 0 0 100
124
122
120
118
116
114
112
110
108
106
104
102
100
98
96
94
92
90
.
E
c
.
a
U
3 88
.
-
m
a
a
In
0
Q
a
90
-5 00
124
t 122
120
118
116
114
112
110
108
106
104
102
100
98
96
9
92
90
D
-0
0
m
(D
(D
r
88 g
.
p.l
3
3
.
90
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? w
2 00
Perigee alt itude,
h n. mi.
P '
120 8
0
4
0
0
40 80
2 68
258
248
238
228
218
2
08
198
188
178
168
158
148
138
128
118
108
98
.-
E
8
.
m
.
al
2
88
u
.
U
-
m
aJ
al
m
0
Q
a
98
-160
268
2 58
2 48
238
228
218
208
198
188
178
168
158
148
138
128
118
108
98
D
U
0
m
(D
(D
E
88 &
r r
I-
.
(D
.
p.
3
3
.
98
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C
a
20
328
3 08
288
2 68
248
228
2 08
188
168
148
128
108
.-
E
c
.
m
.
a
2
88
.
U
-
m
a
a
3 0
Perigee alt itude,
h
n.
mi.
AS 204
P I
40 50 60 70 80
9 0
328
3 08
288
268
2 48
228
2
08
188
168
148
128
108
D
U
0
m
I
I
E-
yr
yr
.
88
5
s
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VI
n
>
-
._
m
._
E
2
VI
VI
n
c
0
x
x
L
0
-
.-
E
-
c
Y
W
3
l
L L
._
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22
21
20
19
18
17
16
15
14
13
12
11
10
9
8
7
6
5
4
3
-2000 -1750 -1500 -1250 -1000 -750
Perigee alt itude, h
o,
n .
m i .
21
20
19
18
17
16
15
14
13
12
11
10
9
8
7
6
5
4
3
-500 -256
(a) Before separation
-
Scale I
Figure 5.- Fl ight-control t ra jectory data as a funct ion of t ime of f ree fa l l and per igee al t i tude at
S-IVB
cutoff plus
15
seconds assuming
CSM/S-IVB
separation occurs at S-IVB cutof f p lus
45
seconds.
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22
2 1
2 0
19
1 8
1 7
16
1 5
1 4
13
12
11
1 0
S
.-
E
- 9
I-
6
5
j
00
-450 -400 -350
300
-2 5 0 -2 0 0 -1 5 0
Perigee alt itude, hp , n . m i .
(b)
Before separation Scale I1
Figure 5.
-
Continued.
-
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24
c
.-
E
iL
LL
I
-
22
L
.
I
94
84
74
64
54
44
34
3 2
3 0
28
26
24
22
20
1 8
1 6
1 4
1 2
1 0
8
6
9 4
84
74
64
54
4 4
3 4
3 2
3 0
28
2 6
24
22
20
1 8
1 6
1 4
1 2
1 0
8
6
V
-200 -160 -120 -80 -4 0 0 4 0
Perigee alt itude,
hp,
n
mi .
8 0 -
(c) Before separation - Sca le l l
Figure 5.- Concluded.
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~
Y
Perigee alti tude,
h
n.
mi.
P'
- 1 1 0 0
1 0 0 0 - 900 -8 0 0 - 7 0 0 - 6 0 0 - 5 0 0 - 4 0 0
100
9 9
98
97
9 6
9 5
9 4
93
92
9 1
9 0
8 9
.-
E
8
.
.
8 8
U
-
m
a
a
m
100
9 9
D
u
0
ca
rD
rD
ru
T
t-r
.
S
n
rD
.
.
3
-
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.
a
73
3
U
Y
.-
-
m
a
a
m
a
a
.
L
Apogee
altitude,
ha,
n.
mi.
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t
Perigee al t i tude, h n. mi.
P'
D
U
0
a
rD
rD
E
R
8
a
rD
.
.
s
-
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-200
a _
-1
6 0
Perigee alt itude,
h n.
mi.
P'
-120
-8
0
-4
0
0
4 0 8 0
2
68
258
248
238
228
218
2 8
1 9 8
188
1 7 8
168
158
1 4 8
138
1 2 8
1 0 8
9 8
D
u
Q
(D
(D
E
88 E
Fr
R
.
(D
.
p1
3
3
-.
9 8
-
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4
Perigee alti tude,
h
n. mi.
40 50 60
7 0
P'
8
0
9 00 30
328
308
288
2 68
248
228
2 08
188
168
148
128
108
D
U
0
cn
I
I
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PRIOR TO LE T JET FOLLOWING LET JET
PRGGRAM 12 PROGRAM 7 1
R 1 -D EL TA R
R2-PERIGEE A LT.
R 1 GAMMA R 1 - G MAX
R 2 -V E LOC ITY
R2-PERIGEE ALT.
R3-TFF
-
PROGRAM 1 2
MODE
1 1 / 1 1 1
A
R 1 -D EL TA R
R2-PERIGEE A LT.
R3-TFF
R OU TINE 3 4
MODE
1 1 / 1 1 1
- - - - - -
1-APOGEE ALT.
R2-PERIGEE A LT.
R 3 - T F F
ROUTINE 34
EY V3 3E (PROC)
MODE
1 1 / 1 1 1
J
R1-APOGEE ALT.
R2-PERIGEE A LT.
R 3 - T F F
R OU TIN E 3 4 I
- - - -
1-T PERIGEE HRS.
R3-T PERIGEE SEC.
R2-T PERIGEE MIN.
MODE IV
I ROUTINE
341
R1-APOGEE ALT.
R2-PERIGEE ALT.
R 3 - T F F
(S-IVB/CM
SEP)
R1-T PERIGEE HRS.
R2 -T PERIGEE MIN.
R3 -T PERIGEE SEC.
CANNOT BE MONITORED
(DISPLAYS WIL L NOT UPDATE)
(ZERJ
Figure
7.
- AGC/DSKY disp lays available for onboard abort mode selec tion.
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34
REFERENCES
1.
R-507, G&N Systems Operations Plan Mission AS-204A, MIT/ IL
June,
1966.
2.
Weber, Bobbie
D.
and Treadway, Alexander H.: The Feas ib i l i ty
of Using The Apollo Guidance Computer Orb i t Maneuvering Programs
For Contingency O rb it In se rt io n f o r AS-204A.
Sept. 23, 1966.
MSC I N 66-FM-102,
3.
AS-204 Launch Abort Description For Or b i t a l De b ri s S t u d i es .
MSC M
66-m34-136,
Sept. 2,
1966.
4.
Contingency An aly sis Se ct io n, F l i g h t An aly si s Branch: AS-204A
Ope ration al Abort and Alter nat e Mission Stud ies.
MSC
I N 66-FM-113,
o c t .
13,
1966.
5 .
AS-204/Crew Ch ar ts For b u n c h Abort Mode S e le c t io n And Procedures--
S ta tus .
MSC M 66-m34-48,
August 23,
1966.
6.
Procedural Suggestion
(DET
Resetting) To
A i d
I n The Use
of
AS-204
Crew Charts . MSC
M 66-m34-49,
Aug. 26,
1966.