REVISION 1 TO VIEWS FROM THE CM AND LM DURING THE … · 2018-08-08 · msc internal note no....

JUL 1 1 1969

• NATIONAL A E R O N A U T I C S AND SPACE ADMINISTRATION

MSC INTERNAL NOTE NO. 69-FM-197

0July 3, 1969

REVISION 1 TO

VIEWS FROM THE CM AND LM

DURING THE FLIGHT OF APOLLO 11

(MISSION G)

VIEWS FBOH THE CM AND N/t-/

DOBING THE FLIGHT OF APOLLO 11:|j (MISSION G) -(BiSA) 303 p Dnclas

;.::' 00/99 16164

Fl ight A n a l y s i s B r a n c h

MISSION PLANNING AND ANALYSIS DIVISION

M A N N E D SPACECRAFT CENTERHOUSTONTEXAS

MSC INTERNAL NOTE NO. 69-FM-197

PROJECT APOLLO

REVISION 1 TO VIEWS FROM THE CM AND LMDURING THE FLIGHT OF APOLLO 11 (MISSION G)

By Alfred N. LundeFlight Analysis Branch

<** "-—j—.»

July3, 1969

MISSION PLANNING AND ANALYSIS DIVISION

NATIONAL AERONAUTICS AND SPACE ADMINISTRATION

MANNED SPACECRAFT CENTER

HOUSTON,TEXAS

Approved:1

Cfiarlie C. Allen, ChiefFlight Analysis Branch

Approved:John PfMissiol

Mayer, ChiefPlanning and Analysis Division

CONTENTS

Section Page

1.0 SUMMARY AND INTRODUCTION 5

1.1 Summary . . . 5

1.2 Introduction ..... .5

2.0 SYMBOLS AND NOMENCLATURE 9

3.0 DISCUSSION OF DATA 13

3.1 General Information 13

3.2 Mission Geometry . ......... lU

3.3 TLI Burn . . ........ lU

3. Translunar Coast 15

3.5 Views from the CSM During LOI Burn 15 .

3.6 Views from the LM During Descent 15

3.7 Views from the LM During Ascent Phase . . . . . 16

3.8 TEI Burn . 16

3.9 Post-TEI . . .i 16

3.10. Transearth Coast ........ 16

3.11 Views from the CM During Entry Phas;e ...... 16

3.12 Views Through the Scanning Telescope IT

3.13 View through the Alinement Optical Telescope . 18

U.O MISSION GEOMETRY, 23

5.0 VIEWS FROM CSM DURING TRANSLUNAR PHASE ........... 31

5.1 TLI Burn 33

ill

Section Page

5.2 Translunar Coast ................ 39

5.2.1 Earth Vievs ............... Ul5.2.2 Moon Views ............... 69

6.0 VIEWS FROM GSM AND LM DURING LUNAR ORBIT PHASE ... 89

6.1 Views from GSM During LOI Burn ......... 91

6.2 Views from LM During Descent Phase ....... 101

6.2.1 DOI burn ................ 1106.2.2 PDI burn ................ 113

6.3 Views from LM During Ascent Phase

6.3.1 Ascent burn . . . ............6.3.2 CSI maneuver .......... . . . . 1696.3.3 CDH maneuver .............. 1736.3A TPI maneuver .............. ITT

7.0 VIEWS FROM GSM DURING TRANSEARTH PHASE ....... 183.

7.1 TEI Burn . . ...... ............. 185

7.2 Post-TEI .................... 191

7.3 Transearth Coast ................ 195

7.3.1 Moon views ............... 1977.3.2 Earth views ............... 213:

8.0 VIEWS FROM CM DURING ENTRY PHASE .......... 231

9..0 VIEWS THROUGH SCANNING TELESCOPE .......... 2 3

9.1 Earth Parking Orbit Phase ........... 2Uo

9.2 Translunar Coast Phase . . . . . . . . . . . . . 253

9.3 Lunar Orbit Coast Phase ............ 265

9. Transearth Coast Phase ............. 277

IV

Section Page

10.0 VIEWS THROUGH ALINEMENT OPTICAL TELESCOPE 285

11.0 STAR IDENTIFICATION CATALOGUE 291

12.0 . REFERENCES 299

APPENDIX - MAJOR APOLLO F AND G MILESTONES FORTHE CONTINGENCY ANALYSIS SECTION . . . . . . . . . 303

FIGURES

Figure Page

It. 0-1 Illustration of lunar orbit plane in year1969 ............... ....... 25

U. 0-2 Sun-centered inertial geometry of Apollo 11(Mission G) .......... ........ 26

It. 0-3 Location of the sun and moon at major phasesof Apollo 11 (Mission G) ............ 2?

U.O-lt A schematic of the maneuver attitude andlighting conditions for Apollo 11(Mission G) .................. 28

^. 0-5 Flight of Apollo 11 (Mission G) projected on amap of the celestial sphere .......... 29

5.1-1 Translunar injection burn

(a) Begin TLI burn ............... 35(b) Middle of TLI burn ............. . 36(c) End of TLI burn . . ....... . . . . . . 37

5.2.1-1 Translunar coast - constant field of view (earth)

(a) g.e.t. = 10 hours(b) g.e.t. = 20 hours(c) g.e.t. = 30 hours(d) g.e.t. = hO hours(e) g.e.t. = 50 hours(f) g.e.t. = 60 hours(g) g.e.t. = 70 hours

5.2.1-2 Translunar coast - variable field of view (earth)

(a) g.e.t. = 3 hours .............. 50(b) g.e.t. = H hours .......... . . . . 50(c)' g.e.t. =5 hours .............. 50(d) g.e.t. =6 hours .............. 50(e) g.e.t. =7 hours .... .......... 51(f) g.e.t. = 8 hours .............. 51(g) g.e.t. =9 hours .............. 51(h) g.e.t. = 10 hours .............. 51(i) g.e.t. =11 hours .............. 52

VI

Figure Page

(J) g.e.t. = 12 hours ".'' 52(k) g.e.t. = 13 hours 52(I) g.e.t. = Ik hours 52(m) g.e.t. =15 hours . 53(n) g.e.t. = 16 hours .53(o) g.e.t. =17 hours 53(p) g.e.t. = 18 hours ....'. 53(q) g.e.t. = 19 hours 5k(r) g.e.t. = 20 hours . . ' . . . . . . 51*(s) g.e.t. = 21 hours 5^(t) g.e.t. = 22 hours . . . . 5k(u) g.e.t. = 23 hours . . . . 55(v) g.e.t. = 2k hours , 55(w) g.e.t. = 25 hours 55(x) g.e.t. = 26 hours 55(y) g.e.t. = 27 hours 56(z) g.e.t. = 28 hours 56(aa) g.e.t. = 29 hours 56(•fab) g.e.t. = 30 hours 56(cc) g.e.t. = 31 hours . 57(dd) g.e.t. = 32 hours 57(ee) g.e.t. = 33 hours 57(ff) g.e.t. = 3^ hours 57(gg) g.e.t. = 35 hours 58(hh) g.e.t. = 36 hours 58(ii) g.e.t. = 37 hours 58(JJ) g.e.t. = 38 hours . . . . . . . 58(kk) g.e.t. = 39 hours ' 59(II) g.e.t. =1+0 hours 59(mm) g.e.t. = Ul hours 59(nn) g.e.t. = k2 hours . / 59(oo) g.e.t. = k3 hours / 60(pp) g.e.t. = kk hours 60(q.q) g.e.t. = k5 hours 60(rr) g.e.t. = U6 hours 60(ss) g.e.t. = kl hours 6l(tt) g.e.t. = kQ hours 6l(uu) g.e.t. = k9 hours 6l(w) g.e.t. =50 hours 6l(ww) g.e.t. = 51 hours 62(xx) g.e.t. = 52 hours 62(yy) g.e.t. = 53 hours ; . 62(zz) g.e.t. = 5^ hours . . 'T" 62(aaa) g.e.t. = 55 hours 63(bbb) g.e.t. = 56 hours ' . 63(ccc) g.e.t. = 57 hours 63

vii

Figure Page

636U6U6k

. 6k656565656666666667676767

(ddd)(eee)(fff )(egg)

(hhh)(iii)(JJJ)(kkk)(111)(mTmn )(nnn)(ooo)(ppt>)(qdq )(rrr )( sss )(ttt)

a:.ee.eg. e

S. eS. eg. eg. eS. eS. eg .eg . eg. eg . eg .eS. eg . efi.e

t,tt,tt,t,t,t,tt,t,t,tt,tt.t.

___

__

_

__

=

S8SQ6n616063fill6s6667686Q707172737U

hourshourshourshourshourshourshours

hours . . . •hourshours ...hourshourshourshourshourshours

5-2.2-1 Translunar coast - constant field of view (moon)

fa)(b)(r)(ri)

((f)(E)fh)m(J)(V)(1)(m)

g . eg. eS Pg. eg .eg . eS. eg . eg . eg.eg .eg. ee p

t,tt,t,t,ttttt,tt.t .

___________=

in?n30hnsn6n6s70717?737U7S

hours .hourshours

hourshourshourshourshourshours ...hourshours

5.2.2-2 Translunar coast - variable field of view (moon)

7172.7371*757677787980818283

(a) g.e.t. = 10 hours 8^(b) g.e.t. = 20 hours ^(c) g.e.t. = 30 hours 81*(d) g.e.t. = kO hours 81+(e) g.e.t. = 50 hours 85(f) g.e.t. = 60 hours . 85

Vlll

Figure Page

6.0-1 LM/CSM docked orientation ..... 91

6.1-1 Lunar orbit insertion burn

(a) Begin of LOI-burn (g.e.t.: = 75 = 55:02.8) . . . . . . . . 95(b) Middle of LOI burn (g.e.t. = 75:58:02.8) 96(c) End of LOI burn (g.e.t. = 76:01:08.2) . . . . . . . 97

6.2.0-1 Descent phase . . .

(a) LM descent phase geometry 101(b) Powered descent profile, . ...... . . ..... . ., . . 103

6. 2.0-2 LM groundtrackyduring descent and ascent ... • • , • • • 105

6.2.1-1 LM window and body-axes geometry . . . . . . . . . . . . 109

6.2.1-2 DOI burn (g.e.t. = 101:38:1*8) . . . 110

6.2.2-1 P D I burn - . " ' _ . . : :

(a) Begin descent burn 113(b) 26 seconds into descent burn llU(c) 1 minute 6 seconds into descent burn . . . . .-. . . 115(d) 1 minute h6 seconds into descent burn .. . .• . . . . Il6(e) 2 minutes 6 seconds into descent burn ... . . . . . 117(f) 2 minutes 26 seconds into descent burn . . . . . . . 118(g) 2 minutes U6 seconds into descent burn . 119(h) 3 minutes 6 seconds into descent burn . . . . . . . 120(i) 3 minutes U6 seconds into descent burn 121(j) 5 minutes 26 seconds into descent burn .. . . . . . . 122(k) 6 minutes 6 seconds into descent burn 123(l) 6 minutes 26 seconds into descent burn ..... . . . , 12U(m) 6 minutes &6 seconds into descent burn 125(n) 7 minutes 6 seconds into descent burn . ... . . . 126(o) 7 minutes k6 seconds into descent burn 127(p) 8 minutes 6 seconds into descent burn . . . . . . . 128(q) 8 minutes 26 seconds into descent burn . . . . . . . 129(r() 8 minutes U6 seconds into descent burn . . . ... . 130(s) 9 minutes 6 seconds into descent burn 131(t) 9 minutes h6 seconds into descent burn . . . . . . . 132(u) 10 minutes 6 seconds into descent burn . . . . . . . . 133(v) 10 minutes U6 seconds into descent burn,.. . .... 13^(w) 11 minutes 6 seconds into descent burn . 135(x) 11 minutes 26 seconds into descent burn 136(y) 11 minutes h6 seconds into descent burn 137(z) End of descent burn 138

ix

Figure Page

6.3.0-1 Ascent phase

(a) LM ascent phase geometry .............(b) Vertical rise phase . . . . . ..... .....

6.3.0-2 LM groundtrack during descent and ascent ....... lU3

6.3.1-1 Ascent burn

(a) Begin ascent burn ................(b) 1 minute 0 seconds into ascent burn ....... lU8(c) 1 minute 20 seconds into ascent burn ....... 1^9(d) 2 minutes 0 seconds into ascent burn ....... 150(e) 2 minutes 20 seconds into ascent burn ...... 151(f ) 2 minutes ^0 seconds into ascent burn ...... 152.(g) 3 minutes 0 seconds into ascent burn ....... 153(h) 3 minutes 20 seconds into ascent burn . . . . . . 15^(i) 3 minutes ho seconds into ascent burn . . . . . . . 155(j) H minutes 0 seconds into ascent burn ....... 156(k) h minutes 20 seconds into ascent burn . . . . . . 157(l) H minutes Uo seconds into ascent burn ...... 158(m) 5 minutes 20 seconds into ascent burn ...... 159(h) 5 minutes Uo seconds into ascent burn ...... l60(o) 6 minutes 0 seconds into ascent burn ....... l6l(p) 6 minutes 20 seconds into ascent burn ...... 162(q) 6 minutes Uo seconds into ascent burn ...... 163(r) 7 minutes 0 seconds into ascent burn ....... l6U(s) End ascent burn . . . . ...... ....... 165

6.3.2-1 CSI burn (g.e.t. = 125:21:20) ............. 169

6.3.3-1 CDH burn (g.e.t. = 126:19: 0) ............. 173

6.3.U-1 TPI burn (g.e.t. = 126:58:26) ............. 177

7.1-1 Transearth injection burn

(a) Begin TEI burn (g.e.t. = 135: 2k: 3k) ....... 185(b) Middle of TEI burn (g.e.t. = 135:25:^3.7) • • • • l86

(c) End TEI burn (g.e.t. = 135:27:03) ........ 187

7.2-1 Post TEI

(a) g.e.t. = 135:35:27 -. ...... ......... 191(b) g.e.t. = 135:36:03 ................ 191

:x

Figure Page

7.3.1-1 Transearth coast - constant field of view (moon)

(a) g.e.t. = lUb hours . . . . 197(b) g.e.t. = 150 hours . . . .,.,. 198(c) g.e.t. = l60 hours ; . . - . . .199'(d) g.e.t. = 170 hours . . . ..' ... . . ... . 200(e) g.e.t. = 180 hours . . . . . . . . . . . . . . . . . 201(f) g.e.t. =190 hours . . . ... . . . . . . . . . . . . 202

7.3.1-2 Transearth coast - variable field of view (moon)

(H)(h)(P)(rl)(P)(f) ff

PpPPP.p

.t ,ttt.t ..t.

_

— ._

_

_

—

1 0ISO160170180190

hourshours . .

hours . .

(a) g.e.t. = lUo hours . . . •.,•-.. . . . . . . . . . . . 203(b) g.e.t. = 150 hours ..... . . . . .... . . . . 203(c) g-.e-.t-. = 160 hours . . . .... . . . . . . . . . . 203(d) g.e.t. = 170 hours . . . . . . 203(e) g.e.t. = l80 hours . . . . . . ..... .... . . . . 20U

7.3.2-1 Transearth coast - constant field of view (moon)

207208209210211212

7.3.2-2 Transearth coast - variable field of view (earth);• ' • • - '. )

(a) g.e.t. = 136 hours . . . . . . . . . . . . . . . . 213(b) g.e.t. = 137 hours . . . . . . . . . . . . . . ...... . 213(c) g.e.t. = 138 hours . . . ...... . ..... .-.,•. . 213(d) g.e.t. = 139 hours .... .' .• . . . . . . . .,- . . 213(e) g.e.t. = 1^0 hours . . . . . . . . . . . . . . . . . . . 2lU(f) g.e.t. = lUl hours . . ...'•., . •_' . . 2ll|(g) g.e.t. = lk2 hours . . . . . . . . . . . . . . '. . . .(h) g.e.t. = 1^3 hours . . . . . . . . . .. . . . .... . .(i) g.e.t. = itU hours . 215(j) g.e.t. = ll*5 hours ;v . . 215(k) g.e.t. = 1^6 hours . . .. ... . . . . . . . . . . . 215(l) g.e.t. = lit7 hours t. . .... . ... . . . . . . . . . . . 215(m) g.e.t. = lU8 hours . . . .- . . . . . . ... . ..> . . 2l6(n) g.e.t. = ll*9 hours "'. . . . . 216(o) g.e.t. = 150 hours 216(p) g.e.t. = 151 hours 216(g) g.e.t. = 152 hours 217

xi''

Figure Page

(r) t(s) i(t) t

(u) {(v) j(w) ((x) j(y) «U) f(aa)(bb)(cc)(dd)(ee)(ff)(gg)(hh)(ii)(JJ)(kk)(11)(mm)(nn).(oo)(pp)(qq)(rr)(ss)(tt)(uu)(w)(ww)(xx)(yy)(zz).(aaa)(bbb)(ccc)(add)(eee)(fff)(ggg)

g.e.t .5. e.t.5. e.t .?.e.t.;. e.t .5. e.t.5. e.t.5. e.t.5. e.t.g.e.t .g.e.t.g.e.t.g.e.t.g.e.t.g.e.t.g.e.t.g.e.t.g.e.t.g.e.t.g.e.t.g.e.t.g.e.t.g.e.t.g.e.t.g.e.t.g.e.t.g.e.t.g.e.t.g.e.t.g.e.t.g.e.t .g.e.t.g.e.t.g.e.t.g.e-it .g.e.tg.e.tg.e.tg.e.tg.e.tg.e.tg.e.t

= 153 hours= 15^ hours= 155 hours= 156 hours= 157 hours . . . . .= 158 hours= 159 hours= 160 hours= l6l hours . . .= 162 hours= 163 hours= l6h hours . . . .= 165 hours . . . .= l66 hours= 167 hours= l68 hours . . . .'= 169 hours ...= 170 hours= 171 hours= 172 hours= 173 hours= 17^ hours= 175 hours= 176 hours= 177 hours . . . . . . . . . .= 178 hours= 179 hours= 180 hours= l8l hours= 182 hours= 183 hours= 18U hours= 185 hours= 186 hours= 187 hours. = 188 hours. = 189 hours. = 190 hours. = 191 hours. = 192 hours. = 193 hours '.. = 19!* hours . . " . - . .

217. . . . . 217

217218218

...'.. 218218

. . . . . 219219219219220220220220221221221

. . . . . . 221222222222

. . . . . 22222322322322322U22i+22k22k225225225225226226226226227227

... . . 227

xir

Figure "' Page

8.0-1 Entry phase ',

(a) 15 minutes prior to entry (g.eet. =......... '.-..,. ...... 231

• (b) 13 minutes prior to entry (g.e.t. = . .19H:U8:12) .......... ........... 232

(c) 11 minutes prior to entry (g.e.t. .= ,19 :50:12) . . .. ..... . ... .....!. . ... 233

(d) 9 minutes prior to entry (g.e.t <=19 :52:12) . .. . -.- . .. . . ...... . . . . . . . . . 23h

(e) 7 minutes prior to entry (g.e.t. =19U: 5U:12) ........ . . . . . "'. . . . . . 235

(f.) 5 minutes prior to entry (g.e.t. = ; . <19U:56:12) ........ . ; . : . . . . . . . . . 236

(g) 3 minutes prior to. entry (g.e.t. == .19li: 58:12) . . ............ .... , • .- . 237

(h) 1 minute prior to entry (g.e.t. = ; .195:00:12) ... .. ...... ... .... •. .• . . 238

(i) Entry interface (g.e.t. .= 195:01:12) ....... 239

9.0-1 Approximate location of scanning telescope ,sighting ...................... 2U3

9. -0-2 General CM optics , field, of coverage .........

9.0-3. PTC modes . . . . . . . . . . . . . . . . . .

9.1-1 Scanning telescope - earth parking orbit - rev 1

(a) g.e.t. = 00:U5:00(b) g.e.t. = 01:00:00(c) g.e.t. = 01:15:00

9.2-1 Scanning telescope - evasive maneuver attitude(g.e.t. = 05:30:00) , . , \ ; •

(a) Evasive maneuver roll ......... .; . . ., . . . 253(b) Evasive maneuver roll + 60, ° . . . . .' .-, . . ';. . . 253(c) Evasive maneuver roll + 120° ........... 253(d) Evasive maneuver- roll + 180° . ,...' ,.r .,...•.,...;.. . . ,.253(e) Evasive maneuver roll + 2i*0° . .•,-.=-. ..-".. .. ;. . . . 253"(f ) Evasive maneuver roll + 300° ...... .".... 253

xiii

Figure Page

9.2-2 Scanning telescope - translunar coast -(g.e.t. = 11:00:00)

(a) Roll = 0° . . . . . -, 25^. (b) Roll =60° . 25U(c) Roll = 120° 251*(d) Roll = 180° . 25^(e) Roll = 2 0° •. ... .25U(f) Roll = 300° '•...' 25^

9.2-3 Scanning telescope - PTC attitude -(g.e.t. = 12:00:00)

(a) Roll = 0° . . . 255(b) Roll =60° 255(c) Roll = 120° 255(d) Roll = 180° 255(e) Roll = 2UO° . . 255(f) Roll = 300° 255

9.2-U Scanning telescope - PTC attitude -(g.e.t. = 23:00:00) -

(a) Roll = 0° 256(b) -Roll =60° 256(c) Roll = 120° . 256(d) Roll = 180° . 256(e), Roll = 2UO° 256(f) Roll = 300° . . . . . . 256

9.2-5 Scanning telescope - PTC attitude -(g.e.t. = 26:00:00)

(a) Roll = 0° 257(b) Roll = 60° 257(c) Roll = 120° .' 257.(•d) Roll = 180° 257(e) Roll = 2itO° 257

. (f) Roll = 300° 257

9.2-6 • Scanning telescope - PTC attitude -(g.e.t. = 53:00:'00) . - . - . -

(a) Roll =0° 258(b) Roll = 60° 258

xiv

Figure Page

(c) Roll = 120° . . :;238(d) Roll = 180° . . . . . . . . . * . . . . . . . . . 258(e) Roll = 2 0° 258(f) Roll = 300° . . . .;-... 258

9.2-7 Scanning telescope - PTC attitude T . . . . . , -(g.e.t. = 70:00:00)

(a) Roll =0° . . . - , . - . . ... .'. . ., . . 259(b) Roll = 60° .. . , .,. . . :.. ..-. .. . . . .",'. ... 259(c) Roll = 120° 259(d) Roll = 180° . . . . . . -... . .. ...... ... . . . 259(e) Roll = 2*10° 259(f) Roll = 300° . . . . .. . .-•-.•.- ... . .... , . ... . 259

9.2-8 Scanning telescope - HDI burn attitude r-(g.e.t. = 73:00:00)

i ' " ' - - ' . . ", : : '• . ' "J " •'

(a) Burn attitude roll . . . . . . . . . . 260(b) Burn attitude roll + 60° . , . .. . . . . . .... . 260(c) Burn attitude roll + 120° ... ... . . ..- ... . . , . . 260(d) Burn attitude roll + 180° 260(e) Burn attitude roll + 2 0° . 260(f) Burn attitude roll + 300° . . -.. . ... . .: . . . . 260

9.2-9 Scanning telescope - LOI burn attitude -(g.e.t. = 7 :30:00) . . . . . .

(a) Burn attitude roll 26l(b) Burn attitude roll + 60° . . •...-...; . ..,..••....- .:••. . 26l(c) Burn attitude roll + 120° . . . . . . .... . . 26l(d) Burn attitude roll + l80° , ,. .'. . . .,.. .. . .. . . 26l(e) Burn attitude roll + 2 0°..-.,. .. . .. ... ... . . . 26l(f) Burn attitude roll + 300Q. . . :. .. -.. . . .. . . .. 26l

9-3-1 Scanning telescope - rev 1 ...-. ; •

(a) gte.t. = 77:00:00 . . . . . . . . . . . . ,-.. . . . . 265(b) g.e.t. = .77:25:00. . . . . . . . . . . . ., ... . •. . 265(c) g.e.t. = 77,: 1*5:00, . . . v,.. . .... . ,._ . . . . . 265

9.3-2 Scanning telescope -ri.rev 2 -• :. . .

(a) g.e.t. = 79:15:00 266(b) g.e.t. = 79:35:00 . . . . . . . . . ,. .. :. .. ; . . . 266(c) g.e.t. = 79:55:00 266

~~V"

xv

Figure Page

9-3-3 Scanning telescope - rev h

(a) g.e.t. = 83:10:00 . 267(b) g.e.t. = 83:30:00 267(c) g.e.t. = 83:50:00 .267

9-3-U Scanning telescope - rev 10

(a) g.e.t. = 95:05:00 . . . . . . . . . 268(b) g.e.t. = 95:25:00 268(c) g.e.t. = 95: UO: 00 268

9-3-5 Scanning telescope - rev 12

(a) g.e.t. = 99:00:00 269(b) g.e.t. = 99:20:00 269(c) g.e.t. = 99: 0:00 ; 269

9.3-6 Scanning telescope - rev 13

. (a) g.e.t. = 101:00:00 270(b) g.e.t. = 101:20:00 270(c) g.e.t. = 101:35:00 . . . . . ' . . 270

9-3-7 Scanning telescope - rev lU

(a) g.e.t. = 103:00:00 271(b) g.e.t. = 103:15:00 271(c) g.e.t. = 103:30:00 271


(a) g.e.t. = 12H:UO:00 . . . . . . . . . . . . . . . 272(b) g.e.t. = 125:00:00 . 272(c) g.e.t. = 125:15:00 272


(a) g.e.t. = 13^:35:00 . . . . . . . 273(b) g.e.t. = 13>i:55:00 273(c) g.e.t. = 135:10:00 273

9-^-2 Scanning telescope - PTC attitude (g.e.t . =lU8:00:00)

(a) Roll = 0° . . . . . . . . . . 277

xvi

Figure

(b) Roll = 60° .".'..' 277(c) Roll = 120° . .-..-.• ; •'. . . ... . . . 277(d) Roll = 180° :. .--. .'.--. .-.-'. . . . . . 277(e) Roll = 2kO° •-. . . . . . . . .'•.... 277

. (f) Roll =.300° . .-.-. .'.'. . . . . . . .277

9.H-3 Scanning telescope - PTC .attitude-(g.e.t..--'•' .172:00:00)

(a) Roll =0° • 278(b) Roll =60° 278(c) Roll = 120° . 278(d) Roll = 180° 278(e) Roll = 2itO° 278(f) Roll = 300° 278

9.*t-^ Scanning telescope - El - ?b hours (g.e.t. =191:15:00)

(a) Roll =0° . . . . 279(b) Roll =60° 279(c) Roll = 120° 279(d) Roll = 180° . 279(e) Roll = 2 0° 279(f) Roll = 300° 279

9.U-5 Scanning telescope - El - 1.5 hours (g.e.t. =193:30:00)

(a) Roll = 0° . 280(b) Roll =60° 280(c) Roll = 120° 280(d) Roll = 180° 280(e) Roll = 2 0° 280(f) Roll = 300° 280

10.0-1 Attitude constraint geometry of AOT viewing >positions 285

10.0-2 AOT views 2 hours after lunar landing

(a) AOT front detent position . 286(b) AOT left front detent position 286(c) AOT left rear detent position . . . . 286(d) AOT rear detent position 286(e) AOT right detent position 286(f) AOT right front detent position •. 286

xvii

Figure Page

10.0-3 AOT views 2 hours prior to lunar lift-off

(a) AOT front detent position 287(b) AOT left front detent position 28?

. (c) AOT left rear detent position . 287(d) AOT rear detent position 287(e) AOT right rear detent position 287(f) AOT right front detent position . 287

xviii

1.0 SUMMARY AND INTRODUCTION

2.0 SYMBOLS AND NOMENCLATURE

3.0 DISCUSSION OF DATA

4.0 MISSION GEOMETRY

VIEWS FROM CSM DURINGTRANSLUNAR PHASE

5.2 TRANSLUNAR COAST

"Page missing from available version"

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VIEWS FROM THE CM AND LM DURING THE.FLIGHT •

OF APOLLO 11 (MISSION G) - REVISION 1 ,

. B y Alfred N . Lunde

1.0 SUMMARY AND.INTRODUCTION

1.1 Summary

This report supersedes MSC IN 69-FM-168, Views from the CSM and LMDuring the Flight of Apollo 11 (Mission G) ;(ref. l).'. The data presentedin this report is identical to the above mentioned report up to aground elapsed time of 99 hours. Due to the recently added revolutionprior to.DOI, the g.e.t. changes by about 2 hours. This report reflectsall changes that have been made to date, and conforms with the-latestnominal mission profile.

The purpose of this report is to visually depict various aspects .of the Apollo 11 (Mission G) lunar landing mission. Out-the-windowviews are shown for most critical maneuvers executed by the CSM and bythe LM. Detailed views of the earth and the moon are shown for thetranslunar and transearth coast phases of the flight. Views throughthe scanning telescope are presented for earth parking orbit, translunarcoast, moon parking orbit, and transearth coast. Views through the ,-alinement optical telescope are presented for the lunar surface stay.

These views will prove valuable to the crew as onboard data andfor simulation purposes in preparation for the flight. Some of thedata presented in this report are a result of crew requests and willbe incorporated into the crew flight plan.

1.2 Introduction . , . : .

V • '

Because of the complex geometry associated with a lunar mission,it is difficult to visualize the various aspects of such a mission.The objective of -this document .is to depict what the crew will see duringmaneuvers and coast periods during the flight of Apollo 11 (Mission G).

Because this mission is the first lunar landing mission, considerableattention has been given to LM maneuvers while in lunar orbit. Views

through the LM commander's front and docking windows have been shownfor most maj or LM burns.

All critical CSM maneuvers have been depicted. The CM leftrendezvous window has been superimposed on these views to indicate theview available to the commander while he is in a restrained couch positionduring a burn.

For the translunar and transearth coast periods, views are shownof the earth and the moon. Most of these are close-up views of thetwo celestial bodies. These views should prove useful for photographypurposes.

The sections that concern views through the scanning telescope andalinement optical telescope have been added at the request of thecrew.

The sequence of major events are listed in table I, and the missionREFSMMAT's are presented in table II.

The major analytical tool used to produce this report was developedby Mr. G. B. Roush of the Computation and Analysis Division.

This document and its relation to other Apollo 11 (Mission G) mile-stones for the Contingency Analysis Section are shown in the appendix.

The apparent motion of the earth terminator relative to the space-craft view is caused by the assumed .attitude of the spacecraft. Thisattitude assumes the spacecraft is pitched down 90° from the local hori-zontal in a plane defined by the radius vector to the spacecraft and theinertial velocity vector relative to the body being observed. As thespacecraft approaches the moon, the trajectory is warped by the moon andcauses the effect depicted. The crew will not necessarily have thespacecraft oriented as stated previously. The x in the center of eachview merely centers the view, except for CSM critical maneuver viewswhere the x also denotes the projection of the CM X-axis. All X andY scales are referenced from the center of the view, and their onlypurpose is to indicate the field of view. This XY coordinate system isnot necessarily parallel to the CSM- or LM-body axis.

This report has the following additions or changes to MSC IN 69-FM-168:

1. New descent and ascent burn views with craters are shown.

2. Updated DOI, CSI, CDH, TPI, TEI, and post-TEI burn viewsare shown.

3. Transearth coast views, scanning telescope views in lunarorbit after 99 hours g.e.t. , and alinement optical telescope views whileon lunar surface have been updated.

2.0 SYMBOLS

AOT alinement optical telescope

e.g. center of gravity

CDH constant delta height

CM . command module

CSI concentric sequencing initiation

GSM command and service modules

DOI descent orbit insertion

El entry interface

g.e.t. ground elaps ed t ime

h altitude above earth's surface

h^ altitude above moon's surface

LOI lunar orbit insertion

LM lunar module

PDI' powered descent initiation

PTC passive thermal control

R radius from center of earth£j

RM radius from center of moon

SCT scanning telescope

SEQ star identification number

SM service module

10

TEC transearth coast

TEI transearth injection

TLC . translunar coast

TLI translunar injection

TPI terminal phase initiation.

V. inertial velocity

3.0 DISCUSSION OF DATA

3.1 General Information

For a :better understanding; of the data presented in this report,a brief explanation follows. '

All the views 'Of the critical maneuvers have a field of view of100°, although the crew does not have such a large field of view.

All navigation stars, four of the largest planets' (Venus,'Mars,Jupiter, and Saturn), the sun, moon, and earth are named on all viewswhere they appear. Other stars with a magnitude of +3 have been shownbut are not named on the views. In views for some of the criticalmaneuvers and in various other views, all of the stars can be identifiedby the number on top of the view. The star name and location can befound in the star catalogue.

To show a close-up view of the earth and moon during the translunarand transearth coast phases, the field of view has been varied.

The CM window configuration data were obtained from the commandmodule manufacturer and from reference 1. The LM window configurationdata were obtained from reference 2.

The field of view is indicated on all views. The velocity infps and mph as well as the radius in n. mi. and altitude in stat. mi.are indicated on many of.the views.

During the descent and ascent burny.phases, the outline of both theLM front windows are shown projected on the lunar surface or on thecelestial sphere. Only the portion within the window outline is visibleto the crew at the particular time indicated, although areas outside thewindow are also shown. Due to a combination of the extremely wide fieldof view used and the mathematical model involved, the surface of the moonappears to take on a fish-eye view in some cases. However, the distortionin these big fields of view is very minimal. The smallest cratersdepicted in this report have a size of 1 minute of arc (1658 ft).

3.2 Mission Geometry

The relationship of the ecliptic, equatorial, and lunar planesas they appear in the year 1969 are shown in figure U.0-1.

The position of the earth's equatorial plane in the ecliptic planefor the month of July is shown in figure 4.0-2. The location of thesun and the moon during the major phases of the mission is depictedin figure U.0-3.

A schematic diagram of the maneuver attitude and lighting conditionsat TLI, LOI, and-.TEI is presented in figure 4.0-U. The Apollo 11 (Mission G)trajectory has been plotted on a map of the celestial sphere and showsthe inertial position of the spacecraft with respect to the stars,sun, and moon (fig. U.0-5).

For a comparision of the mission geometry for the two previouslunar missions, refer to references 3 and h.

3.3 TLI Burn

The beginning, middle, and end of the TLI burn are shown infigure 5-1-1. The horizon is dark until shortly before the end of theburn, at which time the terminator can be seen.

3.U Translunar Coast

Views of the' earth and the moon during the translunar coastphase of the mission are presented in figures 5.2.1 and 5.2.2.In figure 5.2.1-1, the earth is shown as it would appear, as the space-craft recedes from it on .the lunar trajectory. To show details of theearth such as continents and the terminator, the view has .been enlargedin figure 5-2.1-2. These views are shown every hour during the coastperiod and should be helpful to determine which part of the world canbe seen from the spacecraft. In figure 5.2.2-1, the moon is shown as itappears to the crew at various times on the translunar trajectory. Notethat the moon is almost totally dark and that the sun is occulted bythe moon for a period of time during the coast. In figure 5.2.2-2,,,afew enlarged views of the moon are shown. Vectors used were obtainedfrom reference 5.

3.5 Views From the GSM During LOI Burn

The beginning, middle, and end of the LOI burn are depicted infigure 6.1-1. Because of,the obstruction caused by the •.docked. LM,the views from the rendezvous windows are severely limited. Thecrewmen are in the heads-down position during this burn, and the burnis performed in a retrograde attitude to brake the trajectory speedso that a lunar orbit may be achieved..(See page 99 for orientation.)

3.6 Views from the LM During Descent

The geometry .associated with the LM descent phase is presentedin figure 6.2.0-1. Initiation of the DOI burn is shown in figure.6.2.1-1.The docking window is mostly covered by thfe dark moon. However, note ;.hot-that the horizon of the moon can be monitored on the scribe on thewindow. (See page 102.)

'The powered descent burn is shown in figure 6.2.2-1. The lightedlunar surface and horizon can be monitored through either the frontwindows or the docking window for the first l80 seconds of the burn.After completing the yaw maneuver, the crew loses sight of the moonuntil about UUU seconds into the PDI burn. . After the lunar, horizioh .is visible through the front'windows, very few.craters are visiblebecause of the flatness of the approach area to landing site 2 andbecause of the oblique look angle to the horizon. It is of interestto note the apparent motion of the sun through the docking window. Atthe end of the burn, both the earth and Saturn are visible through thedocking window.

16

3.7 Views from the LM During Ascent Phase

The geometry of the ascent phase is shown in figure 6.3.0-1. Theascent burn is depicted in figure 6.3.1-1. Again, shortly after leavinglanding site 2, very few craters are visible due to the scarcity oflarge craters close to the landing site. However, due to the LM attitudeduring the ascent phase, the lunar surface and horizon can be monitoredthrough the front windows and docking window, respectively.

3.8 TEI Burn

The beginning, middle, and end of the TEI burn are shown in thecorrect burn attitude in figure 7.1-1. This maneuver is a posigradeburn designed to free the spacecraft from the lunar gravitationalattraction.

.3.9 Post-TEI

The two post-TEI views (figs. 7.2-1 and 7.2-2) depict the viewfrom the spacecraft as the earth comes into view after the TEI maneuver.At this time, the crew are looking at the .middle of the Pacific Ocean.

3.10 Transearth Coast

As with the translunar coast, the views of the earth and moon areshown at various times during the transearth coast period (figs. 7-3.1-1,7-3.1-2, 7-3.2-1, and 7-3.2-2). The moon is nearly three-quartersfull as seen by the crew, and half of the earth facing the crew isin darkness.

3.11 Views from the CM During Entry- Phase

The entry phase is shown in figure 8.0-1. The SM is jettisonedat approximately 15 minutes prior to entry interface, and the CM is in aheatshield-forward attitude. The angle between the spacecraft X-axis andthe earth horizon is held at +31.7°, which can be monitored on the 31.7°scribe on the window. The entry is made in darkness, and the moon isvisible during part of the entry phase. The gimbal angles used for theentry phase were obtained from reference 6.

17

3.12 Views Through the Scanning Telescope

The times and location of the SCT sightings in this report areshown in figure 9.0-1. The SCT location and its field of view are shownin figure 9.0-2. The view along the CM X-axis during the PTC mode isshown in figure 9.0-3. The x in the middle of the view denotes the .spacecraft X-axis projected on the star field background. The CM leftrendezvous window outline is shown for a zero roll attitude.. .

In figure 9.1-1, the view is presented as seen.through the SCTapproximately at the beginning, middle, and end of the darkness periodduring earth parking orbit. The spacecraft is in a heads-down positionwith pitch 0°, yaw 0°, roll l80° with respect to the local horizontal.

The SCT views at indicated g.e.t. times during the translunar coastare shown in figures 9.2-1 through 9-2-9. In each case, a view as seenthrough the SCT is presented at a roll increment of 60°, while pitch andyaw remain at their initial value.

The SCT view from the evasive maneuver attitude is presented infigure 9-2-1. Because no attitude was available and because PTC was notstarted at a g.e.t. of 11 hours, an initial attitude of 0°,0°,0° was usedfor the inner, middle, and outer gimfcal angles.

The next five figures assume a PTC attitude with an initial attitudeof +90°,0°,6° for the inner middle and outer gimbal angles. A LOI-1attitude is assumed in figures 9.2-8 and 9.2-9.

The SCT views during lunar orbit are shown in figures 9 .'3-1 through9.3-12. All of these views are shown at the beginning, middle, and endof the darkness period in the revolution indicated. The REFSMMAT andthe gimbal angles used are stated on each view. The gimbal angles wereobtained from reference 7-

The view through the SCT during the transearth phase of the missionis shown in figures 9-U-l through 9.1t-5- Again, the views are presentedat a roll increment of 60°.

All times for the SCT were obtained from reference 8.

18

3.13 View Through Alinement Optical Telescope (AOT)

The attitude constraint geometry of the AOT is shown in figure 10.0-1,The various detent positions are shown as well as the location of theAOT (ref. 8).

The views through the AOT and the six detent positions at 2 hoursafter lunar landing and 2 hours prior to lunar lift-off are shown infigures 10.0-2 and 10.0-3, respectively. The quarter-moon shape ineach view is an, obstruction to the sightings. The lunar surface canbe seen at the extreme center bottom of each of the views.

19

TABLE-I.- SEQUENCE OF MAJOR EVENTS

Event

Earth parking. _ orbit

Translunar. injection

Lunar orbit insertion

DOI

PDI .

Ascent

CSI

CDH

TPI

• TEI

Entry interface

Time ,hr:min:sec, g.e.t.

00:11:2U

02:UU:l8. ,

75:55:03

101:38:U8

102:35: 0

12 :23:21 j

125:21:20

126:19: 0

126:58:26

135:2U:3U

195=05:03

Burn duration, sec

—

' .;' :- 321.0

365. U

28. U

692.0

• -:

hh.8

2.0

22.3

11*9.2

—

20

TABLE II.- MISSION REFSMMATSa

(a) Launch pad REFSMMATb

-.87505508 .1*0081*951 .27128990

-.0067739375 .5502921+2 -.831+9H52

-.1+8397589 -.7321+6016 . -.1+7882088

(b) PTC REFSMMAT0

.866025^01+ -.1+5872739 -.19892002

-.5000000 -.79^53916 -.31+1+53958

0.00000 .39781+OOU -.917^5^80

(c) Lunar landing site REFSMMAT

.78005170 .57655390 . .2U311512

.0037^215! -.3928313^ .9196029!;

.62570309 -.7161*2806 -.30858630

(d) CSM preferred plane change REFSMMAT

.002798289 -.39330923 .919^020

-.65180536 -.69797995 -.29660368

.75838113 -.598UU117 -.25831^21

(e) Lunar lift-off REFSMMAT5

.63^82512 .712711759 .29830852

.00595961* - -39058739 .9205lt658

• 77263288 ! - •58260827 - .252202^0

aAll REFSMMAT's are listed in the following format

xx xy xzyx yy yzzx zy zz

b.Ref. 10.°Ref. 11.

21

(f) Entry REFSMMAT5

.76825 50 .6U01216H

-.07168836 .63878201 -.T660U068

-.997 12 0 -.OU17 389 .0585316**

Q

All REFSMMAT's are listed in the folloving format,

xx xy xz

yx yy yzzx zy zz

bRef. 10.Ref. 11.

EQUATORIALPLANE

ECLIPTICPLANE

!pr ASCENDINGLUNAR ORBIT EQUATORIALPLANE NODE LINE

LINE OF INTERSECTION LUNARORBIT PLANE TO ECLIPTICPLANE (ASCENDING NODE) .

DIRECTION OF PRECESSIONIN ECLIPTIC PLANE

Figure 4.0-1.- Illustration of lunar orbit plane in year 1969 - inclinationangle (i)«28°, right ascension of ascending equatorial node (n) =5C

26

EQUATORIALPLANE

Figure 4.0-2.- Sun-centered inertial geometry of Apollo 11 (Mission GL

27

EQUATORIAL PLANE

ECLIPTIC PLANE

LUNAR PLANE

SUN AT TLI (116°)

SUN AT El (124°)

TLI (140°)

LUNAR PLANE

LOI (174°)

TEI (-159°)

El (-123°)

ECLIPTIC PLANE

EQUATORIAL PLANE

LUNAR AND SOLARLINE OF NODES

Figure 4.0-3.- Location of the sun and moon at major phases of Apollo (Mission G).

28

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RICH *

-50 -40 -20 0 .

X, deg

20 40

50

40

20

-20

-40

-5050

(a) Begin TLI burn (g.e.t. = 2:44:11).

Figure 5.1-1.- Translunar injection burn.

..... - .

SEQ , 9 10 ~1 * 5 " ... l 8 l 9 -.-p-.-$n.. -1.0- OI.-.- - X - - 8 .,3.---s---.rw'

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-?--: - 7 ... _ _ - - h _ = 127 stat. mi.

[b) Middle TLI bum (9.e.t. = 2:47:06).

Figure 5.1-1. - Continued.

~a*.

-57

SEQXY

SEQX

SEQ

I• 1

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20

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Field of view = 100°

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HE= 192 stat. mi.

V. = 24 282 mph

VKKL'g

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I

-40 -20 0

X, deg

20

(c) End TLI burn (g.e.t. = 2:50:02).

Figure 5.1-1.- Concluded.

50

40

20

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-40

-50

40 50

01<u

T3

SLQ 36 J7 IHb !**«•24 1 b -1 -19

R_ = 51 850 n. mi.

V. =8564fps25 '-

20

10

-10

-20

-25

-25 -20

Field of view=50°

HE= 55 704 stat.<mi.

V. = 5839 mph ,25

20

10

o g-

-10

-20

-25

-10 0,

X, de9 j

10 20 25

(a)g.e.t. = 10 hours.,

Figure 5.2.1-1.- Translunaivcoast-constant field of view (earth).

44':

SEQ 2 37* 21 IBY -J4 13

MS-121 -11

25

20

R£= 91 747 n. mi.

V. = 5875 fps .

10

-10

-20

-25

. Field of view=50°

h£= 101 617 stat. mi,

V. = 4006 mph25

20

10

Q-n>lO

-10

-20

-25

-25 -20 -10 0

X, deg

10 20 25

(b)g.e.t. = 20 hours.

Figure 5.2.1-1.- Continued.

45

T3

>

221

37 8*18 - I U

.U -22

Mb

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1*8

25

RE=:121.920n.

V. = 4697 fps~

20

10.

-10

,-20

-25

Field of view=50°

hE = 136;339stat.

V. = 3202 mphmi.

25

20

10

0 8-

-10

.-20

-25

-25 -20 -10 0 .-. 10

. X, deg

. . (c)g.e.t. = 30.hours.

- -Figure-5.2.1-l;-,C.ontinued.

20 , 25

.01<u

T3

25

20

10

-10

-20

-25

221• e

37 86 IH8Ie -ID -J 9IB -IV -&

RE = 146 817 n. mi.

V. =3961 fps Field of view=50°

hE = 164 990 stat. mi.

V. = 2701 mph25

20

10

0 S-.

-10

-20

-25

-25 -20 -10 0 10

X, deg

(d)g.e.t. = 40 hours.

Figure 5.2;1-1.-Continued.

20 25

Sfcg 2 37 8t Ml21 16 -10 -t»•A 20 -li -1

RP = 168 146 n. mi.t. . , f -

lv = 189 53.4 stat. mi.\

25

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(e).g.e.t.. = 50 hours..

Figure 5.2..1-1.- Continued..

•48: "•

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RE= 186861 n. mi. h£ = 211 071 stat. mi.

25

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25

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RM= 16 000 n. mi.

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20 -

-20

-25

Field of.view=50°

h.. = 17 332 stat. mi.M

V. = 2731 mph

-25 -20 -0 10

25

20

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-10.

-20

-2520 25

(g) g.e.t. = 70 hours.

Figure 5.2.1-1.- Concluded.

RE = 4727 n. mi.

V.= 31 059 fps

R£= 22 654 n. r

V. = 13 729 fps


50;hF= 1480 stat. mi. ' ,R£ = 14 566 n. mi

V= 21 177 mph ^.= 17392fos

X, nd

(a)g.e.t.=J) hours. .

Field of view - 20°

X, nd

(c)g.e.t. = 5 hours.

.Field of view = 30°

h£= 22 107 stat. mi. '\K^ = 29 601 n. mi.

V. = 9361 mph (V. = 11 853 fps

X, nd

(b)g.e.t. = 4 hours.'


h£= 12 801 stat. mi.

. V.= 11 858 mph

h£= 30 102 stat. mi.

V. = 8082 mph

X, nd

(d) g.e.t. = 6 hours.

Figure 5.2.1-2.- Translunar coast-variable field of view (earth).

RE= 35827 n. mi.

V.= 10644 fps

RE= 46 851 n. mi.

V. = 9103 fps

X, nd

(e)g.e.t. = 7 hours.

Field of view = 10"

X, nd

(g)g.e.t. = 9 hours.

h_ = 37 265-sUt. mi. '•51

Field of view =12- V. = 7257 mph

R£ = 41.536 n. mi.

V. = 9773 fps , *F.ield of view = 12"

HE= 49 953 stat. mi.

V. '= 6207 mph

RE= 51 850 n. mi.

V. = 8564 fos

X, nd


Field of view.=.10°

X, nd

(h)g.e.t. = 10 hours.

h_ = 43 836 slat. mi.

V. = 6663 mph

V. = 5839. mph

Fig lire's.2. l'-2'.- Continued.

RE= 56 586 n. mi.V. = 8115 fps

52hE= 61 154 slat, mi.' 'RE=61 098 n. mi.

Field of view = 8- V 5533 mph . ,y 7734 fps Field of view = 7

X, nd

(i)g.e.t. = 11 hours.

X, nd

(j)g.e.t. = 12 hours.

h = 66 348 stat. mi.

V. = 5273 mph

RE= 65418 n. mi.

V. = 7403 fps

(IE = 71 319 stat. mi. R = 69 568 n. mi.

Field of view = 8' V. = 5047 mph V.= 7112 fps

X, nd

(k)g.e.t. = 13 hours.

Field of view = 6°

h£= 76 094 stat. mi.

V. = 4849 mph


RE = 73 567 n. mi.

V. = 6854 fosField of view = 6°

h£= 80696 stat. mi.

V. = 4673 mph

RE= 77 430n..mi.

V.= 6621 fps Field of view = 6°

h£ = 85 141 stat. mi.

V. = 4514 mph

X, nd

(m)g.e.t. = 15 hours.

X, nd

(n) g.e.t. = 16 hours.

V. = 6410 fps

= 89445 stat. mi. R£ = 84 796 n. mi. h = 93 618 stat. mi.

Field of view = 5° Vi = 437° "">h V.= 6216 fps Field of view =5° V. = 4238 mph

X, nd

(o) g.e.t. = 17 hours.

X, nd

(p)g.e;t. = 18 hours.


5-JR_ = 88 320 n. mi.

V. = 6039 fps Field of view = 5°

X, nd

(q)g.e.t. = 19 hours.

V = 5722 fps

h£= 97 673 slat. mi.

V. = 4117 mph

RE= 91 747 n. mi.

V.= 587 5 fps Field of view = 5°

hE= 101 617 stat. mi.

V. = 4006 mph

X, nd

(r)g.e.t. = 20 hours.

r= 105459 stat. mi. RE = 98 341 n. mi.

Field of view =5" V. = 3901 mph V. = 5580 fps

h£= 109 205 stat. mi.

Field of view =5° V. = 3805 mph

X, nd

(s)g.e.t. = 21 hours.

X, nd

(t)g.e.t. = 22 hours.

Figure 5.2.1-2.-Continued.

RE= 101 519 n. mi.

V. = 5446 fpshE= 112 862 lUt. mi. i R = 104 623 n. mi.

Field of view = 4° V = 3713 mph V. = 5321 fos Field ot view = 4°

h£= 116434 stat. mi.

V. = 3628 mph

X, nd

(u)g.e.t. = 23 hours.

R£= 107 659 n. mi.

V. = 5203 fps

. = 119..928 stat. mi. Kf. - 110 629 n. mi.

Field of view =4- V. = 3547 mph V.= 5091 fps

X, nd

(w)g.e.C. = 25 hours.

X, nd

(v)g.e.t. = 24 hours.

(IE= 123 345 stat. mi.

Field of view =4° V.= 3471 mph

X, nd

(x)g.e.t..= 26 hours.


RE = 113 537 n. mi.


56h£ = 126 692 stat. mi. I R£= 116 387 n. mi.

V. = 3399 mph V. = 4884 fps Field of view =4°

HE= 129972 slat. mi.

V. = 3330 mph

RE= 119 180 n. mi.

V. = 4789 fps

X, nd

(y)g.e.t. = 27 hours.

Field of view = 4°

h = 133 186 stat. mi. R = 121 920 n. mi.

V.= 3265 mph V. = 4697 fps

X, nd

(z)g.e.t. = 28 hours.

Field of view = 4°

h£= 136 339 stat. mi.

V.= 3202 mph

X, nd

(aa)g.e.t. = 29 hours.

X, nd

(bb)g.e.t. = 30 hours.


R£= 124 609 n. mi.


X, nd

(cc)g.e.t. = 31 hours.

R_= 129 841 n. mi.

V. = 4445 fps

X, nd

(ee)g.e.t. = 33 hours.

hE= 139433'sUt. mi.

V. = 3143 mph'

57RE= 127 248 n. mi. h£ = 142 471 stat. mi.

V i =4526f P s ' • Field of view =4'- • V.= 3085 mph

Field of view ='4° V = 3031 mph

h_ = 145455 stat. mi. R = 132 389 n. mi.

V. = 4368 fps

X, nd

(dd)g.e.t. =32 hours.

. Field of view =4°

_-< i

§.;

X, nd

tff)g.e.t.= 34 hour's.

hE = 148 386 stat. i

V = 2978 mph

Figure 5.2.1-2,- Continued.

RE= 134 893 n. mi.

V. = 4294 fps Field of view = 4"

X, nd

(99'9.e.t. = 35 hours.

hE= 151 269 slat. mi.

V. = 2928 mph

58RE= 137 356 n. mi.


h£= 154 102 slat. mi.

V. = 2879 mph

X, nd

(hh) g.e.t. = 36 hours.


h_ = 156 889 slat. mi. RE = 142 162 n. mi.

V. = 2832 mph V. = 4087 fps

X, nd

(ii) g.e.t. = 37 hours.

Field of view = 3°

h_= 159 633 slat. mi.

V.= 2787 mph

X, nd

()i) g.e.t. = 38 hours.


RE= 144 508 n. mi.v i=4023fps Field of view = 3°

59h£ = 162 332 slat. mi. |R£ = 146 817 n. mi.

V,= 2743 mph V, = 3961 fps

- = 164 990 stat. mi.

Field of view =3° . V = 2701 mph

X, nd

<kk)g.e.t. = 39 hours.

RE= 149 091 n. mi.

V{ = 3900 fps Field of view =3°, ' V. - 2659 mph

HE= 167 608 stat. mi. RE = 151 332 n. mi.

V. = 3842 fps

X, nd

(ll)g.e.t. = 40 hours.

Field of view = 3"

h£= 170 185 stat. mi.

V.= 2620 mph

X, nd

(mm)g.e.t. = 41 hours.

X, nd

(nn)g.e.t. = 42 hours.

RE = 153 539 n. mi.


172 725 stat. mi.

2581 mph

60RE= 155 714 n. mi.

V.= 3731 fps

h£= 175 229 stat. mi.

Field of view =3° Vi = 2544 mPh

X, nd

(oo)g.e.t. = 43 hours.

RE= 157 859 n. mi.

V. = 3678 fps

HE= 177 696 stat. m.

Field of view= 3° V = 2508 mph

RE= 159 973 n. mi.

V. = 3626 fps

X, nd

(pp) g.e.t. = 44 hours.

Field of view = 3°

h£= 180 129 stat. mi.

V.= 2472 mph

X, nd

(qq) g.e.t. = 45 hours.

X, nd

Or) g.e.t. = 46 hours.


61


hE= 182 528 stat. mi.

V. = 2438 mph • 'V. = 3527 fps

RE = 164 115 n. mi. ,hE = 184 896 stat. mi.

Field of view =3° V= 2405 mph

X, nd

(ss)g.e.t. = 47 hours.

R£= 166 144 n. mi.

V {= 3480 fps

X, nd

(uu)g.e.t. = 49 hours.

hE=. 187 196 stat. mi R£ = 168 146 n. mi.

Field of view = 3° V. = 2373 mph Vf = 3434 fps ,

X, nd

(tt)g.e.t. = 48 hours.

F.ield of view ='3°

X, nd

(vv)g.e.t. = 50 hours.

h£ = 189 534 stat. i

V.= 2341 mph-


62R_= 170 122 n. mi. h£ = 191 809 stat. mi.

V= 3389 fps Field of view =3° V = 2311 mph

RE = 174 000 n. mi.

V. = 3303 fps

- = 172 074 n. mi. h_ = 194 055 stat. mi.

V% 3345 fps Field of view = 3" V = 2281 mph

X, nd X, nd

(ww) g.e.t. = 51 hours. (xx) g.e.t. = 52 hours.

h£ = 196 271 stat. mi. R£ = 175 903 n. mi.

Field of view =3° V. = 2252 mph V. = 3262 fps Field of view = 3°

h£= 198461 stat. mi.

V.= 2224 mph

X, nd

(yy)g.e.t. = 53 hours.

X,nd

(zz)g.e.t. = 54 hours.


RE = 177783 n. mi.

V. = 3222 fps Field of view =3°

HE= 200'624 slat. mi.

V.= 2197 mph

63RE= 179 640 n. mi.

V. = 3183 fps-

RE= 181 476 n. mi.

V. = 3146 fps

X;nd

(aaa)g.e.t. = 55 hours.

Field of view = 3°

X, nd

(ccc)g.e.t. = 57 hours.

Field of view = 3°

HE = 202 761 stat. mi.

V. = 2170 mph

h£= 204 874 stat. mi. R = 183 291 n. mi.

V. = 2145 mph . v.= 3109fps'

X, nd

(bbb)g.e.t.'=56 hours.

Fieldof view= 3°-

h = 206 963 stat. mi.

V. = 2120 mph

X, nd

(ddd)g.e.t. = 58 hours.


RE= 185 085 n. mi,

V. = 3074 fps

64h£ = 209 027 slat. mi. RE = 186 861 n. mi.

Field of view = 3"V..= 2096 mph V. = 3040 fps Field of view = 3°

h£ = 211 071 stat. mi.

V. = 2073 mph

RE= 188 618 n. mi.

V. = 3007 fps

X, nd

(eee)g.e.t. = 59 hours.,

Field of view = 3°

HE = 213 094 stat. mi. A = 190 358 n. mi.

V. = 2050 mph V. = 2976 fps

X, nd

(fff)g.e.t. = 60 hours.

Field of view = 3° __

hE= 215 095 stat. mi.

V. = 2029 mph

X, nd

(ggg)g.e.t. = 61 hours.

X, nd

(hhh)g.e.t. = 62 hours.


RM= 31 974 n. mi.

V. = 3790 fpsField of view= 3°

65hM= 38 261 stat. mi. R = 29 731 n. mi.

V = 2584 mph . y. = 3805 fps .- Field of view = 3°

hM= 33 134 stat. mi.

V. = 2594 mph

R.. = 27 480 n. mi.M

V. = 3823 fps

X, nd

(Mi) g.e.t. = 63 hours.

Field of view = 3° ••

hM = 30.543 stat. mi. R M =25217n .

V =2607.mph . v.= 3845 fps

X, nd

(jjj) g.e.t. = 64 hours.

Field of view = 3°.

h. = 27 940 stat. mi.-M

V. = 2622 mph

X, nd

(kkk) g.e.t. = 65 hours.

X, nd

(III) g.e.t. = 66 hours.

/,Figure 5.2.1-2:- Continued.

RM = 22 942 n. mi.

V. = 3872 fpsField of view = 3°

V, = 3950 fps

X, nd

(mmm)g.e.t. = 67 hours.

Field of view = 3°

66

V. = 2640 mph

RM= 20 649 n. mi.


HM= 22 683 stat. mi.

V. = 2664 mph

h..= 20 349 stat. mi. R..= 16 000 n. mi.M M

V. = 2693 mph V. = 4006 fps

X, nd

(nnn) g.e.t. = 68 hours.

Field of view = 3°


V.= 2731 mph

X, nd

(ooo) g.e.t. = 69 hours.

X, nd

(ppp) g.e.t. = 70 hours.


RM= 13 629 n. mi.

Vf = 4082 fps I

RM= 8734 n. mi.

V. = 4359 m

X, nd

(qqq)g.e.t. = 71 hours.

Field of view= 3°

hM= 14 603 stat. mi. ^7|RM= H 213 n. mi

Field of view = 3« V. = 2783 mph V. = 4190 Fps Field of view = 3°

. stat. mi.

v"'= 8971 mph

RM= 6158 n. mi.

V. = 4662 fps

X, nd

(sss)g.e.t. = 73 hours.

X, nd

(rrr) g.e.t. = 72 hours.

Field of view= 3"

hM= 11 824 stat. mi

V. = 2857 mph

hM= 6007 stat. mi.

V. = 3179 mph

X, nd

(ttt) g.e.t. = 74 hours.


71

Ol01-a

25

20

10

-10

-20

-25

i t i J

AY

1 7

-ii-i

ra-i13

1U7

13 ' 2H

RE= 51 850 n. mi.

V. = 8564 fps Field of view=50°

h E =55 704 stat. mi.

V. = 5839 mph

•MOON

*FBOCTON

-25 -20 -10 0

X, deg

10 20

(a) g.e.t. = 10 hours.

Figure 5.2.2-1.- Translunar coast - constant field of view (moon).

25

20

10

-10

-20

.SUN .1 | | \ _25

25

22



Stu

25

20

10

-10

-20

-25

I / I *- <; t - i

i 'i i '

RE= 91 747 n. mi.

V. = 5875 fps

•43 Sii lUbJ A 6

• IV -22 16

Field of view=50°

hE= 101 617 stat. mi.

V. = 4006 mph

MOON

SUN

I . .

-25 -20 -10 0

X, deg

10

(b) g.e.t. = 20 hours.


25

20

10

o s-IQ

-10

-20

-25

20 25

73'

Ol<u-a

SEO 1'4 17 lil 10 VJ 105

Y -13 17 1' -17 -«>a 13

25

20

RE= 121 920 n. mi.

V. =4697fps

10

-10

-20

-25

nomx

-25 -20

Field of view=50"

hE= 136339 stat. mi.

V. =3202mpK' "

MOON

SUN

I I

-10 0

X, deg

10



25

20

10

a.n>in

-10

-20

-25

20 25

74

1H 17 13 HO ' J»5 ~ TOVx -j9 -*•* -I J 6 /Y -II 18 21 ' -"IS " -IB ~ "ZiJ

R = 146 817 n. mi. = 164 990 stat. mi.

25

20 -

10 -

0 -

-10 -

-20 -

-25



V. = 3961 fps Fje,d rf vjew=500 V. = 2701 mph

*_ . HBQLUiS • _

HUD

•MOON

rscciot

SUN •

*

I I i | | . . .

25 -20 -10 0 10 20 2

X, deg

OKC.J

20

10

-<0 k

-10

-20

f\ r-25

5

'•75

iEQX

18 Mvl Sb-J J 6^3 - 1J - JA

RE= 168 146 n. mi. hE= 189 534 stat. mi.

OK£D

20

10

Olo>

~°v 0

>

-10

-20

o c-25

V. =3434fps . _no V. =2341mphi ; Field or view=50° . i

*HUUIS *

' ' . ' ' '

MOON;

HUCVCM ^^, ^ . : '

SUN . ;

• •'

. . . . 1 1 : . . . 1 ; 1 1 . . . .

!5 -20 -10,., 0 10 20 2

X, deg

1 C25

20

:10

o £

rlO

-20

-255

(e) g.e.t. = 50 hours.

Figure 5.2.27!.- Continued.

76

IH HU-I* 3-/ -11

- l U

25

20

R = 186 861 n. mi.

V. =3040 fps

10

-10

-20

-25

ffODKM

-25 -20

I OS6

- "ft

Field of view=50°

SUN

HE= 211 071 stat. mi.

V. = 2073 mph

I

-10. 0X, deg

10

25

20

10

-10

-20

-25

20 25

(f) g.e.t. = 60 hours.


77'

CTl<1)-o

It HO 52 55| 9 3 -JO 6-5 •» -22 -12

25

20

R = 27 480 n. mi.M

V. =3823fps

10

-10

-20

-25

-25 -20

Field of view=50°

hM=.30 543 stat. mi.

V. = 2607, mph

SUN

-10 0

X,.deg

1.0

(g) g.e.t.,= 65 hours.

Figure 5.2.2-1 .r Continued.

25

20

10

<0 Q.

n>

-10

-20

-25

.20 25

78

01<u-u

S£9

XY

I t- I V

10 S2

2 -II-7 -20

bb4

-1U

25

20

RE= 16 000 n. mi.

V. = 4006 fps

10

-10

-20

-25

Field of view=50°

hE= 17332 stat. mi.

V. = 2731 mph

-25 -20 -10 0

X, deg

10 20

(h)g.e.t. ;= 70 hours.


25

20

10

n>LQ

-10

-20

-25

25

79

10

-10

-20

-25

StU it 40 52X -IV 2 «10Y -i -b -IV

R£= 13 629 n. mi.

bb6

.V

V = 4082 fps25 -1-

20 -

Field of view=50°

h = 14 603 slat. mi.

V. = 2783 mph25

20

10

0 Q:n>

LQ

-10

-20

-25

-25 -20 -10 0

X, deg

10 20 25

H) g.e.t. = 71 hours.


80/

25

20

10

-10

-20

-25

5E8 |H HO 52 b5X -IV 2 "10 6V U -H -I/ -7

R = 11 213 n. mi.

V. = 4190 fps Field of view=50°

(IE = 11 824 stat. mi.

V. = 2857 mph

-25 -20 -10 0

X, deg

10 20

(j)g.e.t.= 72 hours.


25

20

10

0 8-in

-10

-20

-25

25

81

1H Mb 52•MV -iU -10

25

R = 8734 n. mi.

V. = 4359 fps

20 -

10

OlOJ

-10

-20

-25

-25 -20

jb 7U tUU6 17 V

Field of view=50°

HE = 8971 stat. mi.

V. =2972-mph .-

_L

-10 0

X,deg

10

(k) g.e.t. = 73 hours.


25

20

10

(DLD

-10

-20

-25

20 25

82

25

20

10

0)•° o

-10

-20

-25

Sea ii *<&X -19 -20r / -1 v

R = 6158 n. mi.

V = 4662 fpsi

-10

7u

1?

IUO

-»-18

-25 -20

Field of view=50°

h = 6007 stat. m i .

V. =3179 mph

I

-10 0

X, deg

10

(Dg.e.t. = 74 hours.


25

20

10

0n>

-10

-20

-25

20 25

83

01-a

25

10

-10

-20

-25

SES II M MO • Hb H7 70 '3 1X Id -20 3 -20 -21 .17 6 -6Y -12 2U 17 -6 -13 -b -la -20

Field of view=50°

n. mi.

V. = 5399 fps

h£= 2853 stat. mi.

V. =3681 mph

20 -

-25 -20

SUN

-10 0 [

X, deg]

10

(m) g.e.t. = 75 hours.

'Figure 5.2.2-1 .-.Concluded.

. .25

20

10

0. n>

IQ

-10

-.20

-25

20 • -25

RE= 51 850 n. mi.


h£ = 55 704 stat. mi.

V = 5839 mph

84 = 91747 n. mi.


:(!,= 101 617 slat. mi.

V. = 4006 mph

V. = 4697 fps

X, nd

(a) g.e.t. = 10 hours-

Field of view = 2°

h£ = 136 339 stat.

V. = 3202 mph

R£= 146817 n. mi.

V. = 3961 fps

X, nd

(b) g.e.t. = 20 hours.

Field of view = 2°

hE= 164 990 stat. mi.

V. = 2701 mph

X , n d . X , n d

(c) g.e.t. = 30 hours. . (d) g.e.t. = 40 hours.

Figure 5.2.2-2.- Translunar coast - variable field of view (moon).

85

Y, nd

6

|

? •§.

II II

•4J _i

2 S

Y, nd

.1u.

P" 'A

87

VIEWS FROM CSM AND LM DURINGLUNAR ORBIT PHASE

VIEWS FROM CSM DURING LOI BURN

6.2 VIEWS FROM LM DURINGDESCENT PHASE

6.2.1 DOI BURN

6.2.2 PDI BURN

6.3.3 CDH MANEUVER

91

oQOa

oooa;

srorocu

-acuooCOocu3C

T)

La.

u

95.

2« 26 29 sa .34 43 44X -1< 21 14 12 -21 -24 -24 ,16 ,:23 -16 .18Y -20 -ll o 16 12 - 2 2 - 1 0 . -84 -16 . -Jft. -14

SEC 11? 120 £21 122 123 124 128 13i 133 135 ,4?* 5i 'I •*! ? "*3 10 19 24 -19 -1« 13y -22 -19 -14 -i? -it -14 ;» .7 ^ *•... J*

R = 1019 n. mi.

fps50

40

20

Ol

-20

-40

-5040 50

(a) Begin of LOI burn (g.e.t. = 75:55:02.8).

Figure 6.1-1. - Lunar orbit insertion burn.

96

SEQ 2M 26 113 H7 118 119 121 I22

x .16 19 -19 "I8 -20 18 -17 0Y -20 -16 -2<» 'I* "I1* ~22 ~13 "l7

SEO '2fl 131 133 135X 16 22 -21 -18Y -9 -8 0 0

'" 12<*-15 8

"" ~'5

50

40

R., = 999 n. mi.IVI

V. = 7029 fps

20

o-H

-20

-40

-50-50 -40


_L

h.. = 70 stat. mi.

V. = 4797mph

-20 0

X, deg

20

(b) Middle of LOI burn (g.e.t. = 75:58:02.8).

Figure 6.1-1.-Continued.

50

40

20

0 $

-20

-40

-5040 50

97

(EG 2* 26 30 *1 *3 83 113 U6 u? n8 tl9X -20 1-5 23 -14 -12 -13 "22 22 -21 -23 15y -20 -17 3 0 5 -4 -24 -23 -1§ -l3 -22

120 121 123 124 t25 i2« 128 131 133 !33-7 -21 •!« 3 -ii -7 13 18 -23 -20

-19 -i3 «IQ -15 --10 -10 -10 •» 1 1

RM = 1000 n. mi.

V. = 5469fps50

40

20

S1

•

-20

-40

-50-50 -40

Field of view= 100°

-20 0

X, deg

20

h.. = 70 stat. mi.M

V. = 3729mph

40

(c) End of LOI burn (g.e.t. = 76:01:08.2).


50

40

20

Q.n>to

-20

-40

-5050

100

Of.

ooooLUQ

8O

LU

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MEWKEMT

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GIENAH

JUPITER

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Docking window

Figure 6.3.2-1.- CSI burn (g.e.t. = 125:21:20).

Page i1Wentfo»a% left Wank

173


MENKAR

SATURN

DIPHDA

-H-H- - 10 8

•H-HeEARTH

FOMALHAUT

MIRFAK

AEPHERATZ

ENIF

Docking window

Figure 6.3.3-1.- CDH burn (g.e.t. = 126:19:40).

177


FOMALHAUT

PEACOCK

I - - 10 a

-zo,DABIH

NUWKI

ENIF

ALTAIR

• ' *RASALHAGUE

Docking window

Figure 6.3.4-1.- TPI burn (g.e.t. = 126:58:26).

VIEWS FROM CSM DURINGTRANSEARTH PHASE

7.3 TRANSEARTH COAST

7.3.1 MOON VIEWS

7.3.2 EARTH VIEWS

VIEWS FROM CM DURINGENTRY PHASE

VIEWS THROUGH SCANNINGTELESCOPE

.1 EARTH PARKING ORBIT PHASE

9.2 TRANSLUNAR COAST PHASE

9.3 LUNAR ORBIT COAST PHASE

9.4 TRANSEARTH COAST PHASE

185

50

40

20

-20

-50

SEQ It 16 |7x I* "? 18

la

"»*'

HO H23 - i 9

•fS -1213

7

52: 9

: 1

SB 60.1 -2M

T,» - I 822

8

7,0 --- 7b-1 '-17

5 -It

SEQ bjX -19Y -18

luo I0bo i& -23

R,,= 996 n. mi:- :

IVI

V.= ;5349fps' -

-40;;

. Field-of view= 100°

h.. - 66 stat. mi. .M

V. = 3646 mphI

SUN

I

-50 -40' -20 0

X/'deg

20

50

40

20

-20

-40

-5040 50

Q.ro10

(a) Begin TEI burn (g.e.t.'= 135:24:34).

Figure 7.1-1.- Transearth injection burn.

186:'

OlHI

ibU i if

X i*Y ••

iEQ| ,,X .t«Y -»<

. .1.6...•6

• 12

> §3• -18k -19

_.» ' . - _1Q_

20 6•23 -8

9Z . 18_22 8• 6

H2 16-17 16• 11 6

UJO-

03

H919

7

»o20

7

62110

bS 403 -23

-4 -19

4921

6

70.• 2

2

50

40

RM = 996 n. mi.M

V. = 6736 fps

20

-20

-40

-50

.Field of view = 100°

h.. = 66 stat. mi.M

V. = 4592 mph

SUN

— * •

I

-50 -40 -20 0

X, deg

20

50

40

20

-20

-40

-5040 50

(b) Middle of TEI bum (g.e.t. = 135:25:43.7).

Figure 7.1-1.-Continued.

187 .

SEQXY

SEQXY

5-23-1

5212-3

10238

55<t

-9

1 1-23

60-23-21

1 M17

-1 1

68205

[6-5

-IS

70-T0

406

-10

75-15-18

42-17-16

B3-18-21

4b162

97235

47166

9«93

485S

10020

49 5020 21s t

R,. = 1000 n. mi.M

V. = 8577 fps50

40

20

-20

-40

-50

bbARIS


h.. = 71 stat. mi.

V. = 5847 mph

* x

DNOCES

SUN

I

50

40

20

-20

-40

-50-50 -40 -20 0

X, deg

20 40 50

(c) End TEI burn (g.e.t. = 135:27:03).

J -s

191'

Y, d

eg

Y, d

eg

Es t

'A

eft blank

197:

SEQ' 27X -iY -3

61

-9

1 1-1612

63 BM

-7 0

22 : -10

8& 87 |17

-8 -II -2M

t2. '•' 13 .-.1 9

121 122 123 12S

-23 1Q -j8 -2.-| 5 • -2M • -10 ". -9

SEQ 12* !29 13o 132' 13M !3S 138 ' l 3 9X 3 ;. -2Y -J'o- -i

it-M,

10 -10 -22t i l 1 2

-221

223

-0-9

RM = 13 718 n. mi.

V. = 4 555Ips

25

20

10

-10

-20

-25


HM= 14 706stat. mi.

V. = 3 106 mph

-25 -20 -10- 0

X, deg

10 20

25

20

10

, 0 _

n>us

-10

;-20

-2525

(a).g.e.t. - 140:hours,..-

Figure 7.3.1-1.- Transearth coast - constant field of view (moon).

1981

Ol<l>

T3

SEQ:X »7 *» 62Y *l "10 -16

SEQ ,X •!»*Y J

25

20

10

-10

-20

-25

|2v•2

1

15

It

63 81 85 87 ||7 | 2 1 (22 |2J |2S-7 0 -8 -12 -23 -22 U -18 »221 -7 S 16 -J7 -13 -20 -7 -»

132 13H 135 13810 -10 -23

13 )<<-2

RE= 173 780 n. mi.

V. = 4 052 fpsField of view = 50°

hE = 196019 stat. mi.

V. = 2 763 mph

-25 -20 -10 0X,deg

10

25

20

10

-10

-20

-2520 25

CLn>

(b) g.e.t. = 150 hours.

199

. SEQ jX. . 21* 27. 61 62

Y ""• • " l"'.'"i° • "'V-' -2H I ib 16

8? 8b. 87 1|7 1*0 (21 142 [23\ -cl -12- -22 \J. -22 11 -IB

-b 6 |7 -16 -23 -12 -18 -6

SEQXY

|2b |26 |2V"2 •* -*-* *$ J

Uu

I1*0

;

M2

1 J,,9

l^H-1 1.

Ib

. -I Jb ,-2J

Ib

2

Q-b

RE= 148 825 n. mi.

.V~ = 4 537-fps - •

= 167 301 stat. mi.

25

20

10;

-10

-20

-25

- " - : ' ' V.'=3 093 mphField of view = 50° '

-25 -20

. I .

-10 0'X,deg

10 20

25

20

10

Q.m

-10

-20

-2525

.(c) g.e.t. = 160 hours.


200..

o>(U

T3

SEQ 21X .,9Y -*3

SEQ'X l«*Y i

•3

27-13

|29

-3"»

6!-II17

I3U

I1*3

62-1717

—

132

10i.r

at1

-3

|3<4

• II16

8b-H8

— • •

136• 21.»6

87-I 3l»

20•3

H7 |20 )2| |22 |jj-22 3 »2| |2 -17-J5 -21 -II -j6 .5

•

126

•3

25

20

10

-10

-20

-25

REs l20459 n. mi.


HE = 134 659 stat. mi.

V. = 3 593 mph

I .

-25 -20 -10 0

X,deg10

25

20

10

' Q.fDIQ

-10

-20

-2520 25

(d)g.e.t. = 170 hours,

figure 7.3.1-1.- Continued.

201;

SEQx a*Y * 1 3

y i"« 1

SEQX ' 2&

Y "2•I

27

-1

126H0

61- 1 1

129-J7

62-1 7

1 O1 T

1 JO115

an. . i

_ i1

132*11

as-• .-9

i .-»1 u

l3H-12IB

67 l,J7 - (20 121-U ,-2 1 -• 1 ..-21

US • ; -

-21• 17 •

121 12312 -17

.

25

20

R E ±=86 662 n. mi.

V. = 6534fpsField of view.= 50°

hE= 95 766 stat. mi.

V. = 4 455 mph .

10

*> ~-° o

-10

-20

-25

25

20

10

CL.n > ,tn

-10

-20

,-25-25 -20 -10 0

X, deg

10 20 25

(e) g.e.t. = 180 hours.


S1

-a

202 :

SEQ'XY ;

SEQ;XY '

2H 27• | 6 -2• J» 9

)2S 126•2 •«2 3

M•132 |

129-«t10.

62

21_ J*.

1301310

84....

2

1Ma18

85-10

i }1 *

I JH-U21

—

87

-1523

117•10

120S

121-20

•-... ...

12213

123•17

R,- = 41 589 n. mi. 43 898 stat. mi.

25

20 -

10 -

0 -

-10 -

-20 '

-25

25

- 20

-25

-25 -20 -10 0X, deg

10 20 25



RM= 13 718 n. mi.

V. = 4 555 fps

203k i^-,nt . , R_ = 173 780 n. m).h.. = 14 706 stat. ml. E

Field of view = 8°

..Wl

V. = 3 106 mph4052 fps Field of view = 4° = 2 763 mph

I'-- ' ; - • • * , , = *•-•**. - ° „I'.'-*----- i jr c- ?: ° /i""/i:--" • --V f >^-1 [ •

RE = 148 825 n. mi.

V = 4 537 fps

X, nd

(a) g.e'.t. = 140 hours.

Field of view = 2°

- = 167 30l"stat. mi. R£ = 120 459 n. mi.

V( = 3 093 mph V. = 5 270 fps

X, nd

(b) g.e.t. = 150 hours.

Field of view = 2°

hE = 134 659 stat. mi.

V. = 3 593 mph

X, nd X, nd

(c) g.e.t. = 160 hours. (d) g.e.t. = 170 hours.

Figure 7.3.1-2.- Transearth coast - variable field of view (moon).

204

662 n. mi.

V. = 6 534 fpsField of view= 1°

h_ = 95 766 stat. mi.

. V. * 4 455 mph

X, nd

(e) g.e.t. = 180 hours.


207'. ;

SE8 H 7 HI 63 75 80 108 1082X -2t -IH -19 -I -2 20 2J 1

Y U 10 -13 -11 -IS 0 -13 -II

RM= 13 718 n. mi.

V. = 4 555 fps25

20 -

10

Ol(U

T3

-10

-20

-25

Field of view = 50C

HM= 14 706 stat. mi.

V. = 3106mph ;

-25 -20 -10

J_

0

X, deg

25

20

10

(DIQ

--10

-20

-2510 20 25

(a)g.e.t. = 140 hours.

Figure 7.3.2-1.- Transearth coast - constant field of view (earth).

J 7 38 66.___JL?__J* ?* 4

X -2H 20 -2 -20 -16 -J«t -2 9Y A- .-LI.... -I 3 -U... 23_.-_ll r'---l9

25

20

RE = 173 780 n. mi.;

V. = 4 052 fps

10

-10

-20

-25-25 -20


=196 019 stat. mi.

V. = 2 763 mph

_L-10 0 10

X,deg

(b)g.e.t. = 150 hours.


25

20

10

-10

-20

-2520 25

209!

S£Q 1 7 38 66 67. 36 89 . 4X -21 20 -3 -20 -19 -13 -2 VY •» -1 1 -1 1 - 9 - 2 1 1H -7 -9

25

20

RE = 148 825 n. mi.

V. = 4 537 fps

10

-10

-20

-25-25 -20


,hE= 167301 stat. mi.

V. = 3 093 mph

-10 0

X, deg

10


Figure7.3.2-1.- Continued.

25

20

10

0 g-<£>

-10

-20

-2520 25

. 2 1 0 • —

A 7 3JL _6j6 67 86 89-2M 20 - 3 - 2 0 :-19 -13 -2~_7 -.?.._. rS_ —=.4__^1? J6_ -B -6

25

R£=120459 n. ml.

V. s 5 270 fps

20 -

10

-10

-20

-25-25 -20


= 134 659 stat. mi.

= 3 593 mph

_L

MTl'KN

-10 0 10

X, deg



25

20

10

-10

-20

-2520 25

211

SEU 1 7 38 66 67 86 89 HX -ZH 20 -3 -20 -18 -l4 -2 9Y 11 -5 -S -2. -15 20 -1 -2

RE = 86 662 n. mi.

V. = 6 534 fps25

20

10

S1

•

-10

-20

-25


hE;=95 766 stat. mi.

V. = 4,455 mph

-25 -20 -10 0

X, deg

10

•(e):g.e.t. ='180 hours.

' Figure 7.3.2-1.- Continued.

i 25

20

10

-10

-20

-2520 -. 25

2121

-...I _8 ._?___ 36 66 47 89 90 9^ 92 t2 0 - 1 7 1 9 - 3 - 2 0 - 1 8 - 2 7 ~ 1 - 5 W ~

&-.-2Q.... -20 A 8 -5 1.0_.-i3 -1.8 _-22 8....

RE = 41 589 n. mi.

V. = 10030fps

i h 898 stat. mi.

25

20

10

-5 0

-10

-20

-25

Field of view= 50°V. * 6839 mph

\

_L-25 -20 -10 0

X, deg

10

i 25

20

10

-10

-20

-2520 25

(0 g.e.t. = 190 hours.



HM= 1 628 stat. mi.

V. = 4 354 mph

'213-

RM = 5394 n. mi.


h.. = 5 127 stat. mi.MV = 3 552 mph

R =8 259 n. mi.

V. = 4 845 fps

X, nd

(a) g.e.t. = 136 hours.

Field of view = 3°

h.. = 8 425 stat.-mi.M

V = 3 303 mphRM= 11 021 n. mi.

V. = 4 664 fps

X, nd .

(b) g.e.t. = 137 hours.

Field of view= 3° .

hM = 11 602 stat. mi.

V. = 3 180 mph

X, nd X, nd

fc) g.e.t. = 138 hours. • (d) g.e:t. = 139 hours.'

Figure 7.3.2-2.- Transearth coast - variable field of view (earth).

RM = 13 718 n. mi,

V. = 4 555 fps Field of view = 3°

hM= 14 706 slat. nil.

V. = 3 106 mph

214

RM=16372 n. mi.

V. = 4 482 fps Field of view =3"


V. = 3 056 mpn

V. = 4 430 fps

X, nd

(e) g.e.t. = 140 hours.

Field of view= 3°

hM= 20778 stat. ml.

V. = 3 020 mph

RM = 21 595 n. mi.

V. = 4 392 fps

X, nd

(f) g.e.t, = 141 hours.

Field of view = 3°

HM = 23 770 stat. mi.

V. = 2 995 mph

-< I

a. '

X, nd

(g) g.e.t. = 142 hours.

X, nd

(h) g.e.t. = 143 hours.

V. = 4 363 fps Field of view= 3°

X, nd

(i)g.e.t. = 144 hours.

215

HM= 26 743 stat. ml.

V, = 2 975 mph

746 n. mi.

V, = 4 340 fps Field of view = 3*

X, nd

(j)g.e.t. = 145 hours.

hM = 29 699 stat. ml.

V. = 2 959 mph

-<

§.

V. = 4 323 fps Field of vie»=3° V. = 2 947 mph V, = 4 310 fps Field of view = 3°V. = 2 939 mph

X, nd

(k)g.e.t. = 146 hours. .


X, nd

(l)g.e.t. = 147 hours.

RM = 34 400 n. mi.

V. = 4 300 Fps Field of view =3°

h.. = 38 506 stat. mi.M

V. = 2 932 mphRE = 176 138 n. mi.

V, = 4 015 fps

h_= 198 731 stat. mi.

Field of view = 3° • iV = 2 737 "*h

RE = 173 780 n. mi.

V. = 4 052 fps

X, nd

(m)g.e.t. = 148 hours.

Field of view= 3°

h = 196 019 stat. mi. R = 171 401 n. mi.

V. = 2 763 mph V. = 4 092 fps

X, nd

(o)g.e.t. = 150 hours.

X, nd

(n)g.e.t. = 149 hours.

Field of view = 3°

X, nd

(p) g.e.t. = 151 hours.


217

RE = 168 997 n. mi.


h£= 190526 slat. mi.

V. = 2 819 mph

RE = 166574 n. mi.


h£= 187 726 slat. mi.

V. = 2 848 mph

R_ = 164 123 n. mi.

V. = 4 222 fps

X, nd

(q)g.e.t. = 152 hours.

h£= 184 906 stat. mi.

V. = 2 879 mphField of view =3° I

R£= 161 646 n. mi.

V. = 4 270 fps

X, nd

(r)g.e.t. = 153 hours.

Field of view = 3°

hE= 182 055 stat. mi.

V. = 2 911 mph

X, nd

(s)g.e.t. = 154 hours.

X, nd

(Og.e.t. = 155 hours.


218

RE = 159 141 n. mi.

V. = 4 319 fps

h£= 179 173 stat. mi. R£= 156 608 n. mi.

Field of view= yV. = 2 945 mph V. = 4 370 fps .- ., , ,o .Field of view= 3° '

= 176 258 stat. mi.

.= 2980mph

X, nd X, nd

(u) g.e.t. = 156 hours. (v)g.e.t. = 157 hours.

R£=154 045 n. mi.

V. = 4 424 fps

hE = 173 308 stat. mi. RE = 151 451 n. mi.

Field of view = 3°V. = 3 016 mph V. = 4 479 fps

Field of view = 3°

t>E = 170323 stat. mi.

V. = 3 054 mph

X, nd X, nd

(w) g.e.t. = 158 hours.


(x) g.e.t. = 159 hours.

R£= 148825 n. i


219

h£ = 167301 slat. mi. R£ = 146 165 n. mi.

V. = 3 093 mph V. = 4 597 fps Field of view = 3°

HE = 164 240 slat. mi.

V. = 3 134 mph

RE= 143 470 n. mi.

V. = 4 659 fps

X, nd

(y) g.e.t. = 160 hours.

Field of view = 3°V. = 3 177 mph

RE= 140739 n. mi.

.V. =4 724 fps

X, nd

(z) g.e.t. = 161 hours.

Field of view = 4°

h£= 157 996 stat. mi.

V. = 3 221 mph

X, nd

(aa) g.e.t. = 162 hours.

X, nd

(bb) g.e.t. = 163 hours.


220

RE= 137 970 n. mi.

V. = 4 792 fps Field of view = 4"

X, nd

Ccc) g.e.t. = 164 hours.

hE=154810sUt. mi.

V; = 3267mph V. = 4863fps

h£= 151 577 slat. mi.

Field of view = 4° V. = 3 316 mph

X, nd

(dd) g.e.t. = 165 hours.

RE = 132 311 n. mi.

V. = 4 937 fps

h_= 148 298 slat. mi. RE = 129 418 n. mi.


X, nd

(ee) g.e.t. = 166 hours.


X, nd

(ft) g.e.t. = 167 hours.


RE= 126480 n. mi.

V. = 5 095 fps Field of view = 4°

X, nd

(gg)g.e.t. = 168 hours.

R£= 120459 n. mi.

V. = 5 270 fps

X, nd

(ii)g.e.t. = 170 hours.

221

h£ = 141 587 slat. ml. R = 123 494.n. ml.

V. = 3 474 mph V. = 5 181 fps Field of view =4°

h£= 138 151 slat.

V. = 3 532 mph

X, nd

(hh)g.e.t. = 169 hours.

h£= 134 659 slat. mi. R£ = 117 371 n. mi.

Field of view =4° V. = 3.593 mpir,. 'V = 5 364 fps

h= 131 105 slat. mi.

Field of view = 4° IV. = 3 657 mph

. X, nd

tjj) g.e.t. = 171 hours.


222:

RE = 114 229 n. mi.


hE = 127 489 slat. mi. R£ = ill 028 n. mi.

V. 3 725 mph V. = 5 569 fpsField of view = 4°

HE = 123 806 star., mi.

V. = 3 797 mph

X, nd X, nd

(kk)g.e.t. = 172 hours. {IDg.e.t. = 173 hours.

RE= 107 766 n. mi.

V. = 5 681 fps

= 120 052 slat. mi. R = 104 439 n. mi.


hE= 116 223 stat. mi.

V. = 3 954 mph

X, nd X, nd

(mm) g.e.t. = 174 hours. (nn)g.e.t. = 175 hours.


223

RE = 101 042 n. mi.

V. = 5 926 fps

= 112 314 stat. mi. R = 97 572 n. ml.

Field of view = 4- V, . 4 027 nph ' . V, = 6 061 fps- .' . Fieldof viw=

X, hd

(oo)g.e.t. = 176 hours.

h_= 108 320 stat. mi.

V. = 4 132 mph

X, nd

(pp)g.'e.t. = 177 hours.


hE = 104 237'stat. mi. RE = 90 388 n.'mi.

V. = 4 232 mph" V. = 6 364 fps

X, nd

(qq) g.e.t. = 178 hours. .

• Field of view = 5°

(IE= 100 054 stat. mi.

V. = 4 339 mph

X, hd ' '

<rr)g.e.t/= 179-hours!'

224

RE = 86 662 n. ml.

V. = 6 534 fps

V. = 6 924 fps

Field of view = 5°

hE = 95 766 slat. ml. RE = 82 836 n. mi.

V, = 4455mph V. = 6 720 fps

X, nd

(ss)g.e.t. = 180 hours.

Field of views 7°

86 836 slat. mi. R = 74 849 n. mi.

V. = 4 721 mph V. = 7 150 fps


X, nd

(tt)g.e.t. = 181 hours.

Field of view = 7°

hp= 82 172 stat. mi.

V. = 4 875 mph

X, nd X, nd

(uu)g.e.t. - 182 hours. (vv)g.e.t. = 183 hours.


-225

V. = 7 402 fps Field of view =.7°

r = 77356staf. ml. • R£= 66 331 n. ml.

V. = 5 047 mph V. = 7 685 fps. Field of view = 1°

h_ = 72 371 slat. mi.

V. = 5 240 mph

X, nd X, nd

V. = 8 009 fps

(ww) g.e.t. = 184 hours.

Field of view = 8°

h£ = 67 195 stat. mi. R£= 57 146 n. mi.

V = 5 461 mph v. = 8 383 fps

(xx) g.e.t. =.185 hours.

Field of view = 8°

h£ = 61 800 stat. mi.

V. = 5 716 mph

X, nd X.-ndj

Cyy) g'.e.t. = 186 hours.

Figure 7.3.2-2..- Continued.

(zz) g.e.t. = 187 hours.

RE = 52 238 n. ml.


226;

56 153 stat. ml. Rr = 47 071 n. mi.

.1*1"V. = 6 018 mph ;v: = 9 361 fps Field of view = 10°

hE = 50207 stat. mi.

V. = 6 382 mph

X, nd X, nd

R£ = 41 589 n. mi.

V. = 10030 fps

(aaa) g.e.t. = 188 hours.

Field of view = 10"

(bbb)g.e.t. = 189 hours.

h£ = 43 898 stat. mi. R = 35 103 n. mi

V. = 6 839 mph V. = 7 436 mph

X, nd X, nd

(ccc) g.e.t. = 190 hours.


(ddd) g.e.t. = 191 hours.

RE = 29 310 n. mi.

V. = 12 135 fps

227 '

Field of view =15°= 8 274 mph

X, nd

(eee)g-e-t. = 192 hours.

RE = 22 169 n. ml.


hE= 21 552 stat. mi. R£ = 13 839 n. mi.

Y! = 9 599 mph V. = 18 000 fpsField of view = 50°

V. = 12 273 mph

X, nd X, nd

(fff)g.e.t. = 193 hours.


(ggg)g.e.t. = 194 hours.

.231;

SEQXY

17

7*2116 ..

19

-2

1 1

2U 2)7 S.2

- 1. -IK

22 23U -21*

-* 12-16'"I

H.') S 6 J, 8 b V 6 L

I"' -18 21 21 -2J•I'1 -22 --16 .-18 IB

SEQ

X

Y

21 aZS.. «7. 16

I 17 lib 1 IV 12U0 10 -21 -1

-21 -22 U -It

? -V

3 - .!?.J.b..

RF = 5404 n. mi.


stat. mi.

V. = 19 809 mph

(a) 15 minutes prior to entry (g.e.t. = 194:46:12).

Figure 8.0-1.- Entry phase.

232

SEQ 17 19 20 2| 22 21 25 27 S3 SS M6 5a 59X I 8 «2 7 22 0 6 -16 «S |7 16 | 7 20 20Y 19 IS 2 -IS -2 -13 2 -2S -10 -21 "|9 -(2 -JS

SEQ 60 8SX -2S - -5Y 21 -20 •f

108 IQ9 110 Ml It2 |13 1JS jiS jj6- 8 ~jrif~ " Q- '-j7 i7 9 J 5" »JS -2**-I -!7 5 16 7-9 -15 S 8

SEQ 117 118 119 120 121 122 123 12S 125 126 130 2 3X 7 -10 -21 -S 7-9 H -17 -3 -7 -|3 -5 1Y -17 -IB 2 -11 -19 -12 -22 -10 »2I -20 -21 -21 9

RE= 5067 n. mi.

V. = 30 019 fps

50

40

20

S1

-o

-20

-40

-50


h = 1872 stat. mi.

V. = 20 467 mph

MOON .

J.

-50 -40 -20 0

X, deg

20

• *tew*

50

40

20

0 Q-fD

-20

-40

-50

40 50

(b) 13 minutes prior to entry (g.e.t. = 194:48:12).

Figure 8.0-1.- Continued.

233,

SEQ 20 21 22 ZM 25 27 28 HjX 7 22 0 6 - 1 6 - 5 |7 16

"8

M6 t8 59 6H16 JO

7 -19 -2H -6 -17 -1H «8 -J J5

SEOXY

SEQXY

85•1• 23

120y

1062H0

12)7

-I1*

10883

122m OT

10923

-13

123..

1 10010

12*

1 12• 7

'!

125

1139

V..

126

1 It• is-11

12»

1 l&-J1*8

130

116"2-»1 1

1)2

1177

•12

137

1 1*»

-1«

2

— — T

1 19-2 16

31

1 4

R_ = 4742 n. mi.

V. = 31 045 fps50 Field of view = 100°

h_= 1497 stat. mi.

V. = 21 167, mph

40 -

20 -

01<u

T3 0 -

-20 -

-40

-50

- -40

-50-50 -40 -20 0

X, deg20 40, 50

(c) 11 minutes prior to entry (g.e.t. = 194:50:12).

234

SEQXY

SEOXY

SEOXY

207

12

8t-&• 10

-9

2121

-4

as-i

-17

T?2_ a^ O

-2

22Ue

870

-23

uT

'12

2t6

-3

106

3

v i 71 '

-I

" 2S-16H

108

88

—T2S

-1 1

2T-M

-rt

109

22-9

— -fa

2B16

-20"

1 10015

T29~

i|5 '

"fj16

Us90

730

-12

HtIS

-12

litIt-6

" T32~

-16

t6

16-10

1 IS

-1<413

T3-3-

-22

" b8

19" -t

1 1 17• 7

—pi,-

"I

- &919-6

118"9

-9

-,-35-

5-22

61-1-22

"119-2110

137-23-16

62

2-23

120-t-1

2-*(

-11

50

20

S1

-20

-40

-50

RE = 4436 n. mi.


HE = 1145 stat. mi.

V. = 21 897 mph

MOON

* •HWS

•50

40

20

-20

-40

-50-50 -40 -20 0

X, deg

20 40 50

(d> 9 minutes prior to entry (g.e.t. = 194:52:12).

235'

SEQ 21X 21Y "'

220

21 256 -173 17

SEQ 61 <^X -i iY -15 -I*

SEQ n» 120X -22 "1Y 16 t

50

40

63•3-20

•3

3t 135 JJ7X 0 5 - 2 2Y -J5 -16 -U

R = 4154 n. mi.MV. = 33199fps

81*• 5-1

122

-63

27

-8

85"I

•11

123'i

-5

JJti J39-5 -7

-JO -20

28'15"It

870

-16

12H-17

110-i

"it

31>7-21

108' .8'

126•3-1

. SS H 58'IT 1.6 19'•« ."• 0

10922

1139

J.l« 11711 . 70 i 0

126 129 130 |32.•* -H -U »ll•H -9 -5 .JO

19-• U

9• 2

133.*

-16

-4»

20

-20

-40

-50


hE = 821 staU mi.

V. = 22 636 mph

MOON

50

40

20 .:

,0 g...IQ

-20.

-40.

-50-50 -40 -20 0

X, deg

20, 40.: 50'.

(e) 7 minutes.prior to entry.(g.e.t. --194:54:12).

Figure 8.p,-l,-.- Continued.

,236.

2121

H

621

122

"'

Ma-5

•13

2<46

10

6J•2

123

139._-..__-

"13

27m1j

0

8M-5

121

I u

no-5

•17

28 3 1 3Hr& -v? TO~"8 -J7 »2l

8b 87 109-1 o "22

I2& 126 |29

* " 1

2• M

2

<I3 «H <46 &8~r? yt " js I'10 0 1 7

• !•» UH 1»7 ||8"10"- 1H ' 7 9

130 1,32 133 13S

S9I?s

liO.H

i 1

!•»&

6(•1•8

1216

137

R_.= 3907 n. mi.

V. = 34246fps50

20

S1

0

-20

-40

-50

Field of view = 100C

h =f 535 stat. mi.

V. = 23 350 mph

IUHS

50

40

20

0 a.n>in

-20

-40

-50-50 -40 -20 0

X, deg'

20 40 50

(f) 5 minutes prior to entry (g.e.t. = 194:56:12).

Figure 8.0-1.-"Continued.

:237!

SEQ 21 27 28 Jl 32 33 3HX 2* "* 1& - -6 -24 -U IQY 1" 7 U »8 -J6 »19 -13

1-57

SB bV

.20-. 2U.11 12

61el0

621

-1

SEQ "is BO ""tt'TX "2 10 12Y ' "S -22 -21

BH aS 87 109 US 117 118 J2J

?&. -. -1 -0 22 _Ji . 7 . J .6II •« -I .7 13 is -12* .12

SEQ 126 12V 13U 132 133 13MX •"* --«-•• aU—aU. B u

l l 6 8 . M 0 0

135 137 138 139 ISO 116

"1 1 "S -b~ »9r~-l7

2.".3-10

50

40

RE = 3705 n. mi.

V. = 35 181 fps

'-'f';3Q2 statVmi.. ,

Field of view =100° *V. = 23387 mph

20

"^ 0 f->

-20

-40

-50-50 -40

* *

-20 0

, X,-deg:

20

50,

40

20

s

20

-40

-50

40 50

(g) 3 minutes prior to entry (g.e.t. = 194:58:12).


238'

SEQX

SEQ «?X -ft-- ...*3_Y 7 ***

33 " 3M...Tl3 -LQ » - ie_ _ b -i

-V -ii -'i -2H ~ -23~ "B

62 63 ~""6b"

12V

_0 ____ S -22 -b -78 7 8 3 ' 2"

y-J6

»^& 116__-& 1&

-20 -1U

RE = 3558 n. mi.

V. = 35 907 fps50

40


hE= 132 stat. mi.

V. = 24 482 mph

20

S1

•

-20

-40

-50-50 -40

I

50

40

20

-20

-40

-50-20 0

X, deg

20 40 50

(h) 1 minute prior to entry (g.e.t. = 195:00:12).


239 '-"' .

SEQXY

SEOXY

28is1 1

8i1 1

-l*

31-6S

87

UU

32-22-i.

13JB

1 1

33-ID-6

Jjlt

U

13

3'l9

U

13*'aU

36-IB

-io

j;

-2211

37L,

-IS

136-S

t»

61-1(3

i3»-7. 7

62I

12

H

-S

3

63-27

*2-ii.-&.

6Sj 7

-IV

•«S-b

-16-

8UV-9

i <461 •

-"-*

RE = 3509 n. mi.

V. = 36 160 fps

50

40 -

20

S1

•

-20

-40

-50 !—--50 -40


hF = 76 stat. mi.

V. = 24655 mph

-20 0

X, deg

20

(i) Entry interface (g.e.t. = 195:01:12).


50

40

20

0 S

-20

-40

-50

40 50

•243!

-8o

0)

O.

O(OoocoOl

iZ

24

4

01ooII—o2<ua.oO0)cO)

OiC\J

O£

245

50

40

View as seen along CMX-axis during the PTCattitudes (X-axis in centerof view)

20

-20

-40

-50


Gimbal anglesI =90.0°M = 0.0°0 = 0.0°

T T T

I

50

40

20

O kn>

-20

-40

-50 -40 -20 0

X, deg

20-50

40 50

Figure 9.0-3.- PTC mode.

50

40

20

"1 0

-20

-40

-50-50 -40

50

40 -

20

-20

249i

Orb rate- heads down

DABIH

PEACOCK

*ATRIA

*ACRUX'

-40

-50-50 -40 -20 0

X, deg

(a)g.e.t . = 00:45:00.

20

Orb rate - heads down

*DIPHDA

NUNKI

50

40

20

-20

-40

-50

* 'RIGEL

ALT/SIR

50

40

20

-20 0

X, deg

(b)g.e.t. = 01:00:00.

20 40 50 -50 -40

RASALHAGUE ° °-

-20

-40

-5040 50

Orb rate - heads down

*ALDEBARAN

MIRFAK

FOMALHAUT

f

ENIF

-20 0

X, deg

(c)g.e.l. = 01:15:00.

20

Figure 9.1-1.- Scanning telescope - earth parking orbit - rev 1.

NAVI

50

40

20

-20

-40

-5040 50

Y, deg253

Y, (leg

Y, dego

1—

*e

TS

?

°?s

o5.S" e>

YS

a §

Y, deg

6ap 'x

Y, deg254

»U-,tt

Y, deg

'*!

Y. deg

*!*!

Bap''AS'

Y, deg

Y, deg

Y, (teg

-S ^

x "9

6ap 'A

Y, deg? s

-NTS—i s255

s*.

V, deg

5UJ

*<

Y, deg3 s

f° 0 a

° O o

sY, deg

6sp 'A§

s

Y, deg

*olu

sR°)'s

i I01ccIm

s- -r

6ap 'A

Y, deg256

aT-

Y. deg?-T-

T—

T~

5< iY, deg

S3?

S.S.%8

X"Sa

- %

S1 L

Sor*S

'

S

§

Y, deg

is§

Y, degs

SKiiif:CO

y

257

S

§§

S

Ss

1 7

§ -

- "o

X

<*

f. •

S

Y.d

eg

o ^ =

Y, deg

88

258Y, deg

§

SS

§

Y.deg

? s

S

§

*1

Y, deg

X

CES

S „ » I'

j 1 s

Y, deg

Y, deg§

S

259

Y, deg8

a

Y, degs

a

•§ ii " ic: _

S o

*3'

g

8?

?,

Y, deg

fa

Y, deg

fa's§8s

oiS

1

•8

§

SB

ap'A

88ro

fcp'A

Y, deg

, deg

S3

—r—

Y, deg

261

•'•••• s

§

R '

Y, deg

Y. deg

S

§V, deg

S°

*i

. -sO

=3

o

"±:

Si

=

«

53

_iIccS

EfIE

Dap 'A

50Landing site REFSMMAT

.(265-

-20 -

-40 -

-50-50 -40

-50

la) g.e.t. = 77:00:00.

Gimbal anglesl=-177.5°M=.0°0= 180° . Landing site REFSMMAT

50

Gimbal angles1= -177.5°M = 0°

• 0= 180°

40 50

(Wg.e.t."= 77:25:00. fcj'g.'elt'. = 7'7:45:00.

Figure 9.3-1.- Scanning telescope - rev 1.' ~-' - ' '

-40 f~

-50 -50

-50 -40 40 50

(a)g.e.t. = 79:15:00.

Landing site REFSMMAT

Gimbal angles1= -120.7°M= -2.4°0= 0.1°

50

40


T

RASALHAGUEATRIA

20

-20

-40

-50

ALPHECCA" s

Gimbal anglesl = .-120.7°M= -2.4°0= 0.1°

/ *'ARCTURUS

JUPITER

-50 -40 -20 20

Cb)g.e.t. = 79:35:00.

40 50 -so -40

fcjg.e.t. = 79:55:00.

Figure 9.3-2.- Scanning telescope - rev 2.

50

40

20


*DABIH

-20

-40

.50 --50 -40 -20

267

50

40

20


Glmbal angles1= -150.2°M= 0°0= 135°

-20

-40

-50

DABIH

FOMALHAUT

" .- *ACHERNAR

DEARTH

-50 -40 -20 20 40

50

40

20

' S

-20

-40

—1-5050

(a)g.e.t. = 83:10:00.

Gimbal anglesI =-150.2° ;.. .-M'= 0°0=135° „„ Landing site REFSMMAT

50

40

Vs-

-20

-40

-50

Gimbal angles1= -150.2°M= 0°0= 135°

*DABIH

50

40

20

ACRUX

.. *ACHERNAR

•EARTH

-20

-40

0

X, deg

CUg.e . t . = 83:30:00.

20 40 50 •50 . -40-50

-20 20 40 50

(c)g.e.t. = 83:50:00.

Figure 9.3-3.- Spanning telescope - rev,4...

268

50

40

20



50

40

20

Gimbal angles1= -150.2°M= 0.0°0= 135.0°

-20

-40

-50 —-50

DABIH

50

40

20

-20

-40

-40 -20 0

X, deg

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REFERENCES

10.0 VIEWS THROUGH ALINEMENTOPTICAL TELESCOPE

285.

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REVISION 1 TO VIEWS FROM THE CM AND LM DURING THE … · 2018-08-08 · msc internal note no....

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