Source Code
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These source-code files are part of a reconstructed copy of Luminary 69/2,
the flown, final release of the Apollo 10 Lunar Module (LM) Apollo Guidance Computer (AGC) software.
The reconstruction is based on the source code of Luminary 69 — i.e., the
initial, unflown version, "revision 0" — of which
a contemporary listing was available. The code was then updated by incorporating the
differences between Luminary 69 and Luminary 69/2, known from other contemporary
documentation. The only such difference is the implementation in
Luminary 69/2 of the "R-2 Lunar Potential Model", the source code for which was taken
from program Luminary 99/1 (Apollo 11 LM), of which a contemporary listing was also available.
Finally, the now-reconstructed Luminary 69/2 was then validated by assembling it to
executable form and verifying that its memory banks had the correct checksums,
known from still other contemporary documentation.
Note that page numbers in the reconstructed code match those in the original Luminary 69
program listing, or in the ORBITAL INTEGRATION log section, in Luminary 99/1. Page numbers
would certainly differ somewhat in a contemporary Luminary 69/2 listing.
Moreover, annotations that were not present in the contemporary source code have been added
to the reconstructed code to justify each change in Luminary 69/2 relative to
Luminary 69. Here's a guide to the Apollo documentation referenced in those annotations:
Comments from the original source code are prefixed with a single '#' symbol,
whereas comments added later are prefixed by "##" or "###". Report any errors
noted by creating an
issue report at the Virtual AGC
project's GitHub repository.
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001429,000002: ## Copyright: Public domain.
001430,000003: ## Filename: PADLOADS.agc
001431,000004: ## Purpose: A section of LUM69 revision 2.
001432,000005: ## It is part of the reconstructed source code for the flown
001433,000006: ## version of the flight software for the Lunar Module's (LM)
001434,000007: ## Apollo Guidance Computer (AGC) for Apollo 10. The code has
001435,000008: ## been recreated from a copy of Luminary revsion 069, using
001436,000009: ## changes present in Luminary 099 which were described in
001437,000010: ## Luminary memos 75 and 78. The code has been adapted such
001438,000011: ## that the resulting bugger words exactly match those specified
001439,000012: ## for LUM69 revision 2 in NASA drawing 2021152B, which gives
001440,000013: ## relatively high confidence that the reconstruction is correct.
001441,000014: ## Reference: pp. 37-52
001442,000015: ## Assembler: yaYUL
001443,000016: ## Contact: Ron Burkey <info@sandroid.org>.
001444,000017: ## Website: www.ibiblio.org/apollo/index.html
001445,000018: ## Mod history: 2019-07-27 MAS Created from Luminary 69.
001446,000019:
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001448,000021: # ****** FORMAT ******
001449,000022:
001450,000023: # NAMETAG LENGTH TYPE ?? (GSOP NAME) PROGRAMS SAMPLE VALUE / UNITS
001451,000024: # DESCRIPTION
001452,000025: # MORE DESCRIPTION
001453,000026: # INCRE PRESENT ESTIMATED LGC SCALING SOURCE OF VALUE
001454,000027: # -MENT LENGTH AND VALUE
001455,000028:
001456,000029:
001457,000030: # ????? POSSIBLE TYPES ?????
001458,000031:
001459,000032: # HOW INITIATED: P = PADLOADED
001460,000033: # U = UPLINKED
001461,000034: # D = DSKY (ASTRONAUT)
001462,000035: # IF MODIFIED, HOW: (I) = INVARIANT
001463,000036: # (PGM)= PROGRAM GENERATED
001464,000037: # (F) = FRESH START REINITIALIZED
001465,000038: # (U) = UPLINKED
001466,000039: # (D) = DSKY (ASTRONAUT)
001467,000040:
001468,000041:
001469,000042:
001470,000043: # ****** EXAMPLE ******
001471,000044:
001472,000045: # FREAKOUT (2D) P(I) (F-OMEGA) P88'S-RENDESVOUS AVOIDANCE (2 MICROGRAMS)
001473,000046: # RESULTANT QUANTITY AFTER LONG EXPOSURE
001474,000047: # TO A 'STATUS QUO' PHILOSOPHY
001475,000048: # +0 1OCT 00534 E3 B-12 (SUN)LITE DAWNS
001476,000049: # +1 1OCT 07381 E-4 B-12
001477,000050:
001478,000051:
001479,000052: # *************
001480,000053:
001481,000054:
001482,000055: # FLGWRD10 (1D) P(PGM) MANY PROGRAMS, DAP-R03 (00000 FOR DESCENT, 10000 FOR ASCENT )
001483,000056: # MUST BE SET TO ONE VALUE OR OTHER DEPEND
001484,000057: # ING ON MISSION PHASE BECAUSE APSFLAG IS
001485,000058: # NOT INITIALIZED IN FRESH START AS ARE
001486,000059: # OTHER FLAGBITS. MUST USE DSKY OR R03
001487,000060: # OCT 00000
001488,000061:
001489,000062:
001490,000063: # FLAGWRD3 (1D) P(PGM) MANY PROGRAMS (10000 FOR REFSMMAT GOOD; 00000 FOR NO
001491,000064: # GOOD) REFSMFLG IS NOT INITIALIZED BY
001492,000065: # FRESH START AS OTHER BITS ARE.
001493,000066: # OCT 00000
001494,000067: # OR OCT 10000
001495,000068:
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001497,000070: # FLAGWRD8 (1D) P(PGM) MANY PROGRAMS (THERE ARE 8 POSSIBLE CONFIGURATIONS)
001498,000071: # CMOON, LMOON, & SURFFLAG ARE NOT INITIAL
001499,000072: # IZED BY FRESH START AS OTHER BITS ARE.
001500,000073: # OCT; BITS 8,11,12 NEED TO BE SET AS YOU DESIRE
001501,000074:
001502,000075:
001503,000076: # HIASCENT (1D) P(F) (HIASCENT) DIGITAL AUTOPILOT (5000 KG.; 11,100 LBS.)
001504,000077: # INITIAL STAGED MASS
001505,000078: # 1DEC 5050 B-16 SUNLITER # 147
001506,000079:
001507,000080:
001508,000081: # DKTRAP (1D) P(F) (-THETA-MAX-C) DAP STATE ESTIMATOR PARAM. (.14 DEG SCALED AT 4.5 DEG OR -510 DEC)
001509,000082: # LEM-CSM DOCKED, THRESHOLD FOR MEASURE-
001510,000083: # MENT INCORPORATION
001511,000084: # 1OCT 77001 R557 GSOP SEC 3.3.2.3 JUNE68
001512,000085:
001513,000086:
001514,000087: # DKOMEGAN (1D) P(F) (N-OMEGA-C) DAP STATE ESTIMATOR PARAM. ( 10 DEC )
001515,000088: # LEM-CSM DOCKED, RATE GAIN CONSTANT
001516,000089: # 1OCT 00012 R557 GSOP SEC 3.3.2.3 JUNE68
001517,000090:
001518,000091:
001519,000092: # DKKAOSNN (1D) P(F) (N-ALPHA-C) DAP STATE ESTIMATOR PARAM. ( 60 DEC )
001520,000093: # LEM-CSM DOCKED, ACCELERATION GAIN
001521,000094: # CONSTANT
001522,000095: # 1OCT 00074 R557 GSOP SEC 3.3.2.3 JUNE68
001523,000096:
001524,000097:
001525,000098: # LMTRAP (1D) P(F) (-THETA-MAX-L) DAP STATE ESTIMATOR PARAM. (.14 DEG SCALED AT 4.5 DEG )
001526,000099: # LEM-ALONE, THRESHOLD FOR MEASUREMENT
001527,000100: # INCORPORATION
001528,000101: # 1OCT 77001 R557 GSOP SEC 3.3.2.3 JUNE68
001529,000102:
001530,000103:
001531,000104: # LMOMEGAN (1D) P(F) (N-OMEGA-L) DAP STATE ESTIMATOR PARAM. ( 0 DEC )
001532,000105: # LEM-ALONE, RATE GAIN CONSTANT
001533,000106: # 1OCT 00000 R557 GSOP SEC 3.3.2.3 JUNE68
001534,000107:
001535,000108:
001536,000109: # LMKAOSN (1D) P(F) (N-ALPHA-L) DAP STATE ESTIMATOR PARAM. ( 60 DEC )
001537,000110: # LEM-ALONE, ACCELERATION GAIN CONSTANT
001538,000111: # 1OCT 00074 R557 GSOP SEC 3.3.2.3 JUNE68
001539,000112:
001540,000113:
001541,000114: # DKDB (1D) P(F) DAP ( 1.4 DEGREES EXPRESSED IN RADIANS )
001542,000115: # WIDTH OF DEADBAND FOR DOCKED RCS AUTO-
001543,000116: # PILOT (PI/DKDB RADIANS = DEADBAND)
001544,000117: # 1OCT 00200 LUMINARY ERASABLES
001545,000118:
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001547,000120: # ROLLTIME (1D) P(D) (R-TRIM) D.A.P. AND R03 ( 3000 CENTISECONDS OR 30 SECS. )
001548,000121: # TIME TO TRIM DESCENT Z GIMBAL (ROLL)
001549,000122: # 1DEC 3000 SUNDANCE PADLOAD MEMO
001550,000123:
001551,000124:
001552,000125: # PITTIME (1D) P(D) (P-TRIM) D.A.P. AND R03 ( 3000 CENTISECONDS OR 30 SECS. )
001553,000126: # TIME TO TRIM DESCENT Z GIMBAL (ROLL)
001554,000127: # 1DEC 3000 SUNDANCE PADLOAD MEMO
001555,000128:
001556,000129:
001557,000130: # POSTORKP (1D) P(PGM) (POSTORKP) DAP ACCUMULATED JET TORQUE ABOUT +P AXIS
001558,000131: # SCALED AT 32 JET-SEC, OR ABOUT 2.0 JET-
001559,000132: # 1OCT 00000 PCR 616 MSEC PER BIT. PERMITTED TO OVERFLOW.
001560,000133:
001561,000134:
001562,000135: # NEGTORKP (1D) P(PGM) (NEGTORKP) DAP ACCUMULATED JET TORQUE ABOUT -P AXIS
001563,000136: # SCALED AS POSTORKP.
001564,000137: # 1OCT 00000 PCR 616
001565,000138:
001566,000139:
001567,000140: # POSTORKU (1D) P(PGM) (POSTORKU) DAP ACCUMULATED JET TORQUE ABOUT +U AXIS
001568,000141: # SCALED AS POSTORKP.
001569,000142: # 1OCT 00000 PCR 616
001570,000143:
001571,000144:
001572,000145: # NEGTORKU (1D) P(PGM) (NEGTORKU) DAP ACCUMULATED JET TORQUE ABOUT -U AXIS
001573,000146: # SCALED AS POSTORKP.
001574,000147: # 1OCT 00000 PCR 616
001575,000148:
001576,000149:
001577,000150: # POSTORKV (1D) P(PCM) (POSTORKV) DAP ACCUMULATED JET TORQUE ABOUT +V AXIS
001578,000151: # SCALED AS POSTORKP
001579,000152: # 1OCT 00000 PCR 616
001580,000153:
001581,000154:
001582,000155: # ZOOMTIME (1D) P(2) (TAU-T) P40'S , LUNAR LANDING ( 26 SEC )
001583,000156: # TIME BETWEEN ENGINE ON AND THROTTLE UP
001584,000157: # COMMAND IN ANY DPS BURN
001585,000158: # 1DEC 2600 CSEC. SUNDANCE PADLOAD MEMO
001586,000159:
001587,000160:
001588,000161: # MASS (2D) P(U) (M) ALL P40'S, SERVICER (FULL LOADED VALUE APPROX. 15,043.8 KG.)
001589,000162: # VALUE FOR DESCENT STAGE WITH VARYING
001590,000163: # FUEL LOADS
001591,000164: # 2DEC B-16
001592,000165:
001593,000166:
001594,000167: # PIPASCFX (1D) P(I) (SFE1) IMU COMPENSATION PARAMETERS ( PARTS PER MILLION)
001595,000168: # SCALE FACTOR ERROR CORRECTION FACTOR
001596,000169: # 1OCT 75155 B-9 SUNDANCE PADLOAD MEMO
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001598,000171:
001599,000172:
001600,000173: # PIPASCFY (1D) P(I) (SFE2) IMU COMPENSATION PARAMETERS ( PARTS PER MILLION)
001601,000174: # SCALE FACTOR ERROR CORRECTION FACTOR
001602,000175: # 1OCT 77403 B-9 SUNDANCE PADLOAD MEMO
001603,000176:
001604,000177:
001605,000178: # PIPASCFZ (1D) P(I) (SFE3) IMU COMPENSATION PARAMETERS ( PARTS PER MILLION)
001606,000179: # SCALE FACTOR ERROR CORRECTION FACTOR
001607,000180: # 1OCT 65532 B-9 SUNDANCE PADLOAD MEMO
001608,000181:
001609,000182:
001610,000183: # PBIASX (1D) P(I) (BIAS1) IMU COMPENSATION PARAMETERS (PIPA PULSES PER CSEC OR CM PER SEC**2 )
001611,000184: # PIPA BIASES
001612,000185: # 1OCT 04554 B-5 SUNDANCE PADLOAD MEMO
001613,000186:
001614,000187:
001615,000188: # PBIASY (1D) P(I) (BIAS2) IMU COMPENSATION PARAMETERS (PIPA PULSES PER CSEC OR CM PER SEC**2 )
001616,000189: # PIPA BIASES
001617,000190: # 1OCT 06433 B-5 SUNDANCE PADLOAD MEMO
001618,000191:
001619,000192:
001620,000193: # PBIASZ (1D) P(I) (BIAS3) IMU COMPENSATION PARAMETERS (PIPA PULSES PER CSEC OR CM PER SEC**2 )
001621,000194: # PIPA BIASES
001622,000195: # 1OCT 77220 B-5 SUNDANCE PADLOAD MEMO
001623,000196:
001624,000197:
001625,000198: # ADIAX (1D) P(I) (ADIAX) IMU COMPENSATION PARAMETERS ( GYRO PULSES PER PIPA PULSE)
001626,000199: # (MILLI-EARTH-RATE UNIT (MERU) / GRAVITY)
001627,000200: # GYRO DRIFTS DUE TO ACCELERATION ALONG
001628,000201: # INPUT AXIS
001629,000202: # 1OCT 00436 B-6 SUNDANCE PADLOAD MEMO
001630,000203:
001631,000204:
001632,000205: # ADIAY (1D) P(I) (ADIAY) IMU COMPENSATION PARAMETERS ( GYRO PULSES PER PIPA PULSE)
001633,000206: # (MILLI-EARTH-RATE UNIT (MERU) / GRAVITY)
001634,000207: # GYRO DRIFTS DUE TO ACCELERATION ALONG
001635,000208: # INPUT AXIS
001636,000209: # 1OCT 76277 B-6 SUNDANCE PADLOAD MEMO
001637,000210:
001638,000211:
001639,000212: # ADIAZ (1D) P(I) (ADIAZ) IMU COMPENSATION PARAMETERS ( GYRO PULSES PER PIPA PULSE)
001640,000213: # (MILLI-EARTH-RATE UNIT (MERU) / GRAVITY)
001641,000214: # GYRO DRIFTS DUE TO ACCELERATION ALONG
001642,000215: # INPUT AXIS
001643,000216: # 1OCT 00064 B-6 SUNDANCE PADLOAD MEMO
001644,000217:
001645,000218:
001646,000219: # ADSRAX (1D) P(I) (ADSRAX) IMU COMPENSATION PARAMETERS ( GYRO PULSES PER PIPA PULSE)
001647,000220: # (MILLI-EARTH-RATE UNIT (MERU) / GRAVITY)
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001649,000222: # GYRO DRIFTS DUE TO ACCELERATION ALONG
001650,000223: # SPIN REFERENCE AXIS
001651,000224: # 1OCT 00064 B-6 SUNDANCE PADLOAD MEMO
001652,000225:
001653,000226:
001654,000227: # ADSRAY (1D) P(I) (ADSRAY) IMU COMPENSATION PARAMETERS ( GYRO PULSES PER PIPA PULSE)
001655,000228: # (MILLI-EARTH-RATE UNIT (MERU) / GRAVITY)
001656,000229: # GYRO DRIFTS DUE TO ACCELERATION ALONG
001657,000230: # SPIN REFERENCE AXIS
001658,000231: # 1OCT 00116 B-6 SUNDANCE PADLOAD MEMO
001659,000232:
001660,000233:
001661,000234: # ADSRAZ (1D) P(I) (ADSRAZ) IMU COMPENSATION PARAMETERS ( GYRO PULSES PER PIPA PULSE)
001662,000235: # (MILLI-EARTH-RATE UNIT (MERU) / GRAVITY)
001663,000236: # GYRO DRIFTS DUE TO ACCELERATION ALONG
001664,000237: # SPIN REFERENCE AXIS
001665,000238: # 1OCT 00064 B-6 SUNDANCE PADLOAD MEMO
001666,000239:
001667,000240:
001668,000241: # NBDX (1D) P(I) (NBDX) IMU COMPENSATION PARAMETERS ( GYRO PULSES PER CSEC.)
001669,000242: # OR (MILLI-EARTH-RATE UNIT CALLED 'MERU')
001670,000243: # GYRO BIAS DRIFTS
001671,000244: # 1OCT 77332 B-5 SUNDANCE PADLOAD MEMO
001672,000245:
001673,000246:
001674,000247: # NBDY (1D) P(I) (NBDY) IMU COMPENSATION PARAMETERS ( GYRO PULSES PER CSEC.)
001675,000248: # OR (MILLI-EARTH-RATE UNIT CALLED 'MERU')
001676,000249: # GYRO BIAS DRIFTS
001677,000250: # 1OCT 77415 B-5 SUNDANCE PADLOAD MEMO
001678,000251:
001679,000252:
001680,000253: # NBDZ (1D) P(I) (NBDZ) IMU COMPENSATION PARAMETERS ( GYRO PULSES PER CSEC.)
001681,000254: # OR (MILLI-EARTH-RATE UNIT CALLED 'MERU')
001682,000255: # GYRO BIAS DRIFTS
001683,000256: # 1OCT 00000 B-5 SUNDANCE PADLOAD MEMO
001684,000257:
001685,000258:
001686,000259: # WRENDPOS (1D) P(D-V67) (W-RR) P20 - RENDEZVOUS NAVIGATION (2440 METERS)
001687,000260: # W-MATRIX INERTIAL DIAGONAL ELEMENT
001688,000261: # PRESELECTED ERROR TRANSITION
001689,000262: # VALUE UNCERTAIN
001690,000263:
001691,000264:
001692,000265: # WRENDVEL (1D) P(D-V67) (W-RV) P20 - RENDEZVOUS NAVIGATION ( .0244 METERS PER CSEC.)
001693,000266: # W-MATRIX INERTIAL DIAGONAL ELEMENT
001694,000267: # PRESELECTED ERROR TRANSITION
001695,000268: # VALUE UNCERTAIN
001696,000269:
001697,000270:
001698,000271: # WSHAFT (1D) P(I) (W-THETA) P20-RENDESVOUS NAVIGATION ( 10 MILLIRADIANS)
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001700,000273: # W-MATRIX INERTIAL DIAGONAL ELEMENT
001701,000274: # SHAFT PRESELECTED ERROR TRANSITION
001702,000275: # VALUE UNCERTAIN
001703,000276:
001704,000277:
001705,000278: # WTRUN (1D) P(I) (W-BETA) P20-RENDESVOUS NAVIGATION ( 10 MILLIRADIANS -MR- )
001706,000279: # W-MATRIX INERTIAL DIAGONAL ELEMENT
001707,000280: # TRUNNIUN PRESELECTED ERROR TRANSITION
001708,000281: # VALUE UNCERTAIN
001709,000282:
001710,000283:
001711,000284: # RMAX (1D) P(I) (DELTA-RMAX) P20-RENDESVOUS NAVIGATION ( 9.26 TIMES 10 TO 4TH POWER)
001712,000285: # THRESHOLD LIMIT FOR POSITION CORRECTION
001713,000286: # VALUE UNCERTAIN
001714,000287:
001715,000288:
001716,000289: # VMAX (1D) P(I) (DELTA-VMAX) P20-RENDESVOUS NAVIGATION (9.144 TIMES 10 METERS PER SECOND)
001717,000290: # THRESHOLD LIMIT FOR VELOCITY CORRECTION
001718,000291: # VALUE UNCERTAIN
001719,000292:
001720,000293:
001721,000294: # SHAFTVAR (1D) P(U) (VAR-BETA) P22-RENDESVOUS RADAR ( 10 TO 6TH POWER SQUARE RADIANS)
001722,000295: # RR SHAFT ANGLE ERROR VARIANCE
001723,000296: # VALUE UNCERTAIN
001724,000297:
001725,000298:
001726,000299: # TRUNVAR (1D) P(U) (VAR-THETA) P22-RENDESVOUS RADAR ( 10 TO 6TH POWER SQUARE RADIANS)
001727,000300: # RR TRUNNION ANGLE ERROR VARIANCE
001728,000301: # VALUE UNCERTAIN
001729,000302:
001730,000303:
001731,000304: # WSURFPOS (1D) P(D-V67) (W-LR) P20'S-LUNAR SURFACE NAVIGAT
001732,000305:
001733,000306: # W-MATRIX INERTIAL DIAGONAL ELEMENT
001734,000307: # LUNAR ANALOG OF WRENPOS
001735,000308:
001736,000309:
001737,000310: # WSURFVEL (1D) P(D-V67) (W-LV) P20'S-LUNAR SURFACE NAVIGAT
001738,000311:
001739,000312: # W-MATRIX INERTIAL DIAGONAL ELEMENT
001740,000313: # LUNAR ANALOG OF WRENVEL
001741,000314:
001742,000315:
001743,000316: # RANGEVAR (2D) P(I) (VAR-R)) P20 NAVIGATION'S STATE VECTOR INCORPORATION ROUTINE
001744,000317: # (1/3 % QUANTITY SQUARED OR .11111111 E-4
001745,000318: # RANGE ERROR VARIANCE CORRESPONDING TO
001746,000319: # A PERCENTAGE ERROR
001747,000320: # 2DEC* .111111111 E-4 B12* GSOP
001748,000321:
001749,000322:
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001751,000324: # RATEVAR (2D) P(I) (VAR-V)) P20 NAVIGATION'S STATE VECTOR INCORPORATION ROUTINE
001752,000325: # (1.3/3 % QUANTITY SQUARED OR 1.8777 E-5
001753,000326: # VELOCITY ERROR VARIANCE CORRESPONDING TO
001754,000327: # A PERCENTAGE ERROR
001755,000328: # 2DEC 1.87777 E-5 B12 GSOP
001756,000329:
001757,000330:
001758,000331: # RVARMIN (1D) P(I) (VAR-RMIN) P20 NAVIGATION'S STATE VECTOR INCORPORATION ROUTINE
001759,000332: # (80/3 FT QUANTITY SQUARED)
001760,000333: # MIN. RENDESVOUS RADAR POSITION VARIANCE
001761,000334: # 1DEC 66.0 B-12 METERS**2 GSOP
001762,000335:
001763,000336:
001764,000337: # VVARMIN (1D) P(I) (VAR-VMIN) P20 NAVIGATION'S STATE VECTOR INCORPORATION ROUTINE (METERS/CSEC)**2
001765,000338: # (1.3 /3 FT PER SEC QUANTITY SQUARED)
001766,000339: # MINIMUM VELOCITY VARIANCE
001767,000340: # DEC .17445 E-5 B12 GSOP
001768,000341:
001769,000342:
001770,000343: # X789 (6D) P(PGM) (DELTA-BETA,DELTA-THETA,ZERO) P20S, MEAS.INCORP2 (MILLIRADIANS)
001771,000344: # 7,8,9TH COMPONENT NAVIGATION STATEVECTOR
001772,000345: # ALSO SHAFT + TRUNNION BIAS ESTIMATES
001773,000346: # +0 2DEC 0 INITIALLY
001774,000347: # +2 2DEC 0 INITIALLY LUMINARY LISTING
001775,000348: # +4 2DEC 0 ALWAYS
001776,000349:
001777,000350:
001778,000351: # ATIGINC (2D) P(I) (DELTA-TAU-3) P35 ( 7 MINUTES )
001779,000352: # ACTIVE VEHICLE TIME REQUIRED TO PREPARE
001780,000353: # FOR A TPM MANEUVER
001781,000354: # 2DEC 42000 B-28 (CSEC) SUNDANCE PADLOAD MEMO
001782,000355:
001783,000356:
001784,000357: # PTIGINC (2D) P(I) (DELTA-TAU-7) P75 (12 MINUTES )
001785,000358: # PASSIVE VEHICLE TIME REQUIRED TO PREPARE
001786,000359: # FOR A TPM MANEUVER
001787,000360: # 2DEC 72000 B-28 (CSEC) SUNDANCE PADLOAD MEMO
001788,000361:
001789,000362:
001790,000363: # AOTAZ (3D) P(I) (AZ1,AZ2,AZ3) AOTMARK (ALIGNMENT OPTICAL TELESCOPE) (-60 DEG, 0, +60 DEG)
001791,000364: # ANGLES BETWEEN THE LM NAVIGATION BASE Z
001792,000365: # AXIS AND AOT LINE OF SIGHT FOR DETENT1,
001793,000366: # 2,3. (AZIMUTH, 3 FORWARD VIEWING POSIT.)
001794,000367: # +0 OCT 65252
001795,000368: # +1 OCT 0 SUNDANCE PADLOAD MEMO
001796,000369: # +2 OCT 12525
001797,000370:
001798,000371:
001799,000372: # AOTEL (3D) P(I) (EL1,EL2,EL3) AOTMARK (ALIGNMENT OPTICAL TELESCOPE) (EACH IS 45 DEGREES)
001800,000373: # ANGLES BETWEEN THE LM NAVIGATION BASE
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001802,000375: # Y-Z PLANE & AOT LINE OF SIGHT FOR
001803,000376: # DETENT1,2,3. (ELEVATION, 3 FORWARD POS.)
001804,000377: # +0 OCT 10000
001805,000378: # +1 OCT 10000 SUNDANCE PADLOAD MEMO
001806,000379: # +2 OCT 10000
001807,000380:
001808,000381:
001809,000382: # DUMPCNT (1D) P(I) DOWNLINK TELEMETRY HOLDS THE NUMBER 'N' INDICATING THAT A
001810,000383: # DOWNLINK ERASABLE DUMP WILL SEND ALL OF
001811,000384: # ERASABLE STORAGE N TIMES (N=1 TO 4)
001812,000385: # OCT 20000 IF 4 ERASABLE DUMPS DESIRED
001813,000386: # OCT 10000 IF 2 COMPLETE DUMPS DESIRED LUMINARY
001814,000387: # OCT 04000 IF 1 COMPLETE ERASABLE DUMP LISTING
001815,000388:
001816,000389:
001817,000390: # AGSK (2D) P(U) V47(R47) AGS INITIALIZATION ( MINS ?)
001818,000391: # GROUND ELAPSED TIME OF LATEST AGS CLOCK
001819,000392: # ZERO
001820,000393:
001821,000394:
001822,000395: # RBRFG (6D) P(I) (R-OFG) LUNAR LANDING TARGET PARAMETERS ( METERS )
001823,000396: # RANGE VECTOR, BRAKING PHASE, HIGHGATE
001824,000397: # +0 2DEC* +2.92362643 E+ 3 B-24 *
001825,000398: # +2 2DEC* +0.00000000 E+ 0 B-24 * 23A LUMAR LANDING PGM
001826,000399: # +4 2DEC* -1.00839629 E+ 4 B-24 *
001827,000400:
001828,000401:
001829,000402: # VBRFG (6D) P(I) (V-OFG) LUNAR LANDING TARGET PARAMETERS ( METERS PER CSEC )
001830,000403: # VELOCITY VECTOR, BRAKING PHASE, HIGHGATE
001831,000404: # +0 2DEC* -4.83907728 E- 1 B-10 *
001832,000405: # +2 2DEC* +0.00000000 E+ 0 B-10 * 23A LUNAR LANDING PGM
001833,000406: # +4 2DEC* +1.71785605 E+ 0 B-10 *
001834,000407:
001835,000408:
001836,000409: # ABRFG (6D) P(I) (A-OFG) LUNAR LANDING TARGET PARAMETERS ( METERS PER CSEC SQUARED ) HIGHGATE
001837,000410: # ACCELERATION VECTOR, BRAKING PHASE
001838,000411: # +0 2DEC* -5.22722473 E- 5 B+04 *
001839,000412: # +2 2DEC* +0.00000000 E+ 0 B+04 * 23A LUNAR LANDING PGM
001840,000413: # +4 2DEC* -2.86621213 E- 4 B+04 *
001841,000414:
001842,000415:
001843,000416: # VBRFG* (2D) P(I) LUNAR LANDING TARGET PARAMETERS ( METERS PER CSEC )
001844,000417: # VELOCITY SCALAR, BRAKING PHASE, HIGHGATE
001845,000418: # 2DEC* +3.86517612 E+ 0 B-10 * 23A LUNAR LANDING PGM
001846,000419:
001847,000420:
001848,000421: # ABRFG* (2D) P(I) LUNAR LANDING TARGET PARAMETERS ( METERS PER CSEC SQUARED ) HIGH GATE
001849,000422: # ACCELERATION SCALAR, BRAKING PHASE
001850,000423: # 2DEC* -1.71972727 E- 3 B+04 * 23A LUNAR LANDING PGM
001851,000424:
001852,000425:
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001854,000427: # JBRFG* (2D) P(I) (J-OFZG) LUNAR LANDING TARGET PARAMETERS ( METERS PER CSEC CUBED )
001855,000428: # JERK SCALAR, BRAKING PHASE, HIGHGATE
001856,000429: # 2DEC* -2.90216724 E- 8 B+18 * 23A LUNAR LANDING PGM
001857,000430:
001858,000431:
001859,000432: # RAPFG (6D) P(I) (R-1FG) LUNAR LANDING TARGET PARAMETERS ( METERS )
001860,000433: # RANGE VECTOR, APPROACH PHASE, LOWGATE
001861,000434: # +0 2DEC* +2.35092239 E+ 1 B-24 *
001862,000435: # +2 2DEC* +0.00000000 E+ 0 B-24 * 23A LUNAR LANDING PGM
001863,000436: # +4 2DEC* -5.28319999 E- 1 B-24 *
001864,000437:
001865,000438:
001866,000439: # VAPFG (6D) P(I) (V-1FG) LUNAR LANDING TARGET PARAMETERS ( METERS PER CSEC )
001867,000440: # VELOCITY VECTOR, APPROACH PHASE, LOWGATE
001868,000441: # +0 2DEC* -9.44879999 E- 3 B-10 *
001869,000442: # +2 2DEC* +0.00000000 E+ 0 B-10 * 23A LUNAR LANDNNG PGM
001870,000443: # +4 2DEC* +3.96239999 E- 3 B-10 *
001871,000444:
001872,000445:
001873,000446: # AAPFG (6D) P(I) (A-1FG) LUNAR LANDING TARGET PARAMETERS ( METERS PER CSEC SQUARED ) LOW GATE
001874,000447: # ACCELERATION VECTOR, APPROACH PHASE
001875,000448: # +0 2DEC* +1.52399999 E- 6 B+04 *
001876,000449: # +2 2DEC* +0.00000000 E+ 0 B+04 * 23A LUNAR LANDING PGM
001877,000450: # +4 2DEC* -1.98119999 E- 5 B+04 *
001878,000451:
001879,000452:
001880,000453: # VAPFG* (2D) P(I) LUNAR LANDING TARGET PARAMETERS ( METERS PER CSEC )
001881,000454: # VELOCITY SCALAR, APPROACH PHASE, LOWGATE
001882,000455: # 2DEC* +8.91539999 E- 3 B-10 * 23A LUNAR LANDING PGM
001883,000456:
001884,000457:
001885,000458: # AAPFG* (2D) P(I) LUNAR LANDING TARGET PARAMETERS ( METERS PER CSEC SQUARED ) LOW GATE
001886,000459: # ACCELERATION SCALAR, APPROACH PHASE
001887,000460: # 2DEC* -1.18871999 E- 4 B+04 * 23A LUNAR LANDING PGM
001888,000461:
001889,000462:
001890,000463: # JAPFG* (2D) P(I) (J-1FZG) LUNAR LANDING TARGET PARAMETERS ( METERS PER CSEC CUBED )
001891,000464: # JERK SCALAR, APPROACH PHASE, LOWGATE
001892,000465: # 2DEC* +8.37249023 E- 8 B+18 * 23A LUNAR LANDING PGM
001893,000466:
001894,000467:
001895,000468: # VIGN (2D) P(I) (V-IGG) LUNAR LANDING TARGET PARAMETERS (16.99 METERS PER SECOND )
001896,000469: # DESIRED SPEED FOR IGNITION
001897,000470: # 2DEC* +1.69952182 E+ 1 B-10 * 23A LUNAR LANDING PGM
001898,000471:
001899,000472:
001900,000473: # RIGNX (2D) P(I) (R-IGXG) LUNAR LANDING TARGET PARAMETERS ( 40127 METERS )
001901,000474: # DESIRED X-COMPONENT IN GUIDANCE COORDIN-
001902,000475: # ATES FOR IGNITION ("ALTITUDE")
001903,000476: # 2DEC* -4.09432231 E+ 4 B-24 * 23A LUNAR LANDING PGM
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001905,000478:
001906,000479:
001907,000480: # RIGNZ (2D) P(I) (R-IGZG) LUNAR LANDING TARGET PARAMETERS ( 437347 METERS )
001908,000481: # DESIRED Z-COMPONENT IN GUIDANCE COORDIN-
001909,000482: # ATES FOR IGNITION ("GROUND RANGE")
001910,000483: # 2DEC* -4.40014934 E+ 5 B-24 * 23A LUNAR LANDING PGM
001911,000484:
001912,000485:
001913,000486: # KIGNX/B4 (2D) P(I) (K-X) LUNAR LANDING TARGET PARAMETERS
001914,000487: # IGNITION ALGORITHM SENSITIVITY COEF.
001915,000488: # 2DEC -.022499999 23A LUNAR LANDING PGM
001916,000489:
001917,000490:
001918,000491: # KIGNY/B8 (2D) P(I) (K-Y) LUNAR LANDING TARGET PARAMETERS
001919,000492: # IGNITION ALGORITHM SENSITIVITY COEF.
001920,000493: # 2DEC -.174716605 23A LUNAR LANDING PGM
001921,000494:
001922,000495:
001923,000496: # KIGNV/B4 (2D) P(I) (K-V) LUNAR LANDING TARGET PARAMETERS
001924,000497: # IGNITION ALGORITHM SENSITIVITY COEF.
001925,000498: # 2DEC -.165939331 23A LUNAR LANDING PGM
001926,000499:
001927,000500:
001928,000501: # LOWCRIT (1D) P(I) LUNAR LANDING TARGET PARAMETERS (2.7 LBS/BIT) (57% NOMINAL MAX THRUST )
001929,000502: # LOWER LIMIT BEYOND WHICH THROTTLE SET TO
001930,000503: # EITHER MAXIMUM OR TRUE VALUE
001931,000504: # 1OCT 04251
001932,000505:
001933,000506:
001934,000507: # HIGHCRIT (1D) P(I) LUNAR LANDING TARGET PARAMETERS ( LBS / BIT : 63% NOMINAL MAX THRUST)
001935,000508: # UPPER LIMIT BEYOND WHICH THROTTLE SET TO
001936,000509: # EITHER MAXIMUM OR TRUE VALUE ?
001937,000510: # 1OCT 04622
001938,000511:
001939,000512:
001940,000513: # TENDAPPR (1D) P(I) LUNAR LANDING TARGET PARAMETERS ( 10 SECONDS )
001941,000514: # TIME CRITERION FOR SWITCHING OUT OF
001942,000515: # APPROACH PHASE QUADRATIC GUIDANCE
001943,000516: # DEC +10 E2 B-17 (BOTH ONEAND TWO-PHASE)
001944,000517: # LUM MEMO # 45
001945,000518:
001946,000519: # TENDBRAK (1D) P(I) LUNAR LANDING TARGET PARAMETER ( 200 SECONDS )
001947,000520: # TIME CRITERION FOR SWITCH TO APPROACH
001948,000521: # PHASE (P64 )
001949,000522: # DEC +20 E2 B-17 (TWO-PHASE LANDING MODE) LUM MEMO
001950,000523: # DEC +200 E2 B-17 (ONE-PHASE LANDING MODE) #45
001951,000524:
001952,000525:
001953,000526: # RPCRTIME (1D) P(I) LUNAR LANDING TARGET PARAMETERS (300 SECONDS )
001954,000527: # TIME CRITERION FOR REPOSITIONING LR
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001956,000529: # ANTENNA
001957,000530: # DEC +5 E2 B-17 (TWO-PHASE LANDING MODE) LUM MEMO
001958,000531: # DEC +300 E2 B-17 (ONE-PHASE LANDING MODE) #45
001959,000532:
001960,000533:
001961,000534: # RPCRTQSW (1D) P(2) LUNAR LANDING TARGET PARAMETERS ( COS 45 DEGREES SCALED AT B+1 )
001962,000535: # X COMPONENT OF X-AXIS OF VEHICLE IN
001963,000536: # STABLE MEMBER COORDINATES: CRITERION FOR
001964,000537: # REPOSITIONING LR ANTENNA
001965,000538: # DEC 00000 (TWO-PHASE LANDING MODE) SUNLITER
001966,000539: # DEC .35356 (ONE-PHASE LANDING MODE) # 260
001967,000540:
001968,000541:
001969,000542: # LRALPHA (1D) P(I) (ALPHA-1) LANDING RADAR P63-67 ( 6 DEGREES)
001970,000543: # POSITION 1, X ROTATION
001971,000544: # 1OCT 01042 SUNLITER # 168
001972,000545:
001973,000546:
001974,000547: # LRBETA1 (1D) P(I) (BETA-1) LANDING RADAR P63-67 ( 24 DEGREES)
001975,000548: # POSITION 1, Y ROTATION
001976,000549: # 1OCT 04210
001977,000550:
001978,000551:
001979,000552: # LRALPHA2 (1D) P(I) (ALPHA-2) LANDING RADAR P63-67 ( 6 DEGREES)
001980,000553: # POSITION 2, X ROTATION
001981,000554: # 1OCT 01042 SUNLITER # 168
001982,000555:
001983,000556:
001984,000557: # LRBETA2 (1D) P(I) (BETA-2) LANDING RADAR P63-67 ( 0 DEGREES)
001985,000558: # POSITION 2, Y ROTATION
001986,000559: # 1OCT 00000 SUNLITER # 168
001987,000560:
001988,000561:
001989,000562: # LRHMAX (1D) P(I) (H-M) LANDING RADAR P63-67 (50,000 FEET)
001990,000563: # ALTITUDE WEIGHTING FUNCTION PARAMETER
001991,000564: # 1DEC 15240 PCR # 253
001992,000565:
001993,000566:
001994,000567: # LRVMAX (1D) P(I) (V-M) LANDING RADAR P63-67 (2000 FT PER SECOND)
001995,000568: # VELOCITY WEIGHTING FUNCTION PARAMETER
001996,000569: # 1DEC .047625 SUNLITER # 168
001997,000570:
001998,000571:
001999,000572: # LRWH (1D) P(I) (K-H) LANDING RADAR P63-67 (.35 DEC)
002000,000573: # ALTITUDE WEIGHTING FUNCTION PARAMETER
002001,000574: # 1DEC .35 PCR # 253
002002,000575:
002003,000576:
002004,000577: # LRWVZ (1D) P(I) (K-VZ) LANDING RADAR P63-67 ( .7 DEC )
002005,000578: # Z VELOCITY WEIGHTING FUNCTION PARAMETER
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002007,000580: # 1DEC .7 SUNLITER # 168
002008,000581:
002009,000582:
002010,000583: # LRWVY (1D) P(I) (K-VY) LANDING RADAR P63-67 ( .7 DEC )
002011,000584: # Y VELOCITY WEIGHTING FUNCTION PARAMETER
002012,000585: # 1DEC .7 SUNLITER # 168
002013,000586:
002014,000587:
002015,000588: # LRWVX (1D) P(I) (K-VX) LANDING RADAR P63-67 ( .4 DEC )
002016,000589: # X VELOCITY WEIGHTING FUNCTION PARAMETER
002017,000590: # 1DEC .4 SUNLITER # 168
002018,000591:
002019,000592:
002020,000593: # DELQFIX (2D) P(I) DELQFIX R12 50 FEET
002021,000594: # LR ALT DATA REASONABLENESS TEST PARM.
002022,000595: # 2DEC 15.24 B-24 PCRS 639 &248
002023,000596:
002024,000597:
002025,000598: # TBRKPNT (1D) P(I) P70-71 ASCENT (540 SEC OR 54000 CSEC )
002026,000599: # TFI BRANCH TIME; ABORT TARGET
002027,000600: # 1DEC 54000 B-17 PCR # 133
002028,000601:
002029,000602:
002030,000603: # ABTVINJ1 (2D) P(I) P70-71 ASCENT (5551 FEET / SEC)
002031,000604: # DESIRED INJECTION VELOCITY FOR TFI
002032,000605: # BRANCH TIME LESS THAN TBRKPNT; VELOCITY
002033,000606: # REQUIRED TO GAIN 60 NM APOLUNE ORBIT
002034,000607: # 2DEC 16.91945 B-7 PCR # 133
002035,000608:
002036,000609:
002037,000610: # ABTVINJ2 (2D) P(I) P70-71 ASCENT (5510 FEET / SEC)
002038,000611: # DESIRED INJECTION VELOCITY FOR TFI
002039,000612: # BRANCH TIME GREATER THAN TBRKPNT; VEL
002040,000613: # REQUIRED TO GAIN 30 NM APOLUNE ORBIT
002041,000614: # 2DEC 16.79448 B-7 PCR # 133
002042,000615:
002043,000616:
002044,000617: # TLAND (2D) P(U) LUNAR LANDING TARGET PARAMETERS ( 2DEC 34573411 <CSEC>)
002045,000618: # BRAKING PHASE TIME OF LANDING ON MOON
002046,000619: # LAUNCH DATE DEPENDENT
002047,000620:
002048,000621:
002049,000622: # RLS (6D) P(U) (R-LS) P20-22 LUNAR SURFACE NAVIGATION (1.7 TIMES 10**6 METERS; 0 M; 0 METER)
002050,000623: # SAMPLE VALUE AT 0DEG LATITUDE & LONGITUD
002051,000624: # LANDING SITE VECTOR, MOON REFERENCE
002052,000625: # LAUNCH DATE DEPENDENT
002053,000626:
002054,000627:
002055,000628: # 504LM (6D) P(I) (L-M) PLANETARY INERTIAL ORIENTATION ( RADIANS) 8.5 X 10**-5
002056,000629: # 73.9 X 10**-5
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002058,000631: # 6.6 X 10**-5
002059,000632: # MOON LIBRATION VECTOR EXPRESSED AT MID-
002060,000633: # POINT OF MISSION IN MOON FIXED COORDIN.
002061,000634: # LAUNCH DATE DEPENDENT
002062,000635:
002063,000636:
002064,000637: # TEPHEM (3D) P(U) (T-0) LUNAR + SOLAR EPHEMERIDES,P50S (2.23452 X 10**9 CSEC )
002065,000638: # LAUNCH TIME - ELAPSED TIME BETWEEN MID-
002066,000639: # NITE JULY 1 UNIVERSAL TIME PRECEEDING
002067,000640: # LAUNCH AND THE TIME THAT THE COMPUTER
002068,000641: # CLOCK WAS ZEROED AT TIME OF LAUNCH
002069,000642: # +0 DEC LAUNCH DATE DEPENDENT
002070,000643: # +1 2DEC
002071,000644:
002072,000645:
002073,000646: # AXO (2D) P(I) (A-X-TLO) PLANETARY INERTIAL ORIENTATION ( 4.65 X 10**-5 RADIANS)
002074,000647: # EARTH ANALOGS OF 504LM
002075,000648: # FUNCTION OF LAUNCH TIME USED BY NAVIGA-
002076,000649: # TION PROGRAMS
002077,000650: # SMALL ANGLE ABOUT THE X-AXIS OF BASIC
002078,000651: # REFERENCE COORDINATE SYSTEM.....
002079,000652: # LAUNCH DATE DEPENDENT
002080,000653:
002081,000654:
002082,000655: # -AYO (2D) P(I) (A-Y-TLO) PLANETARY INERTIAL ORIENTATION ( 2.147 X 10**-5 RADIANS)
002083,000656: # SEE AXO COMMENTS
002084,000657: # SMALL ANGLE ABOUT THE Y AXIS OF BASIC
002085,000658: # REFERENCE COORDINATE SYSTEM THAT DES-
002086,000659: # CRIBES THE PRECESSION AND NUTATION OF
002087,000660: # THE EARTH'S POLAR AXIS
002088,000661: # LAUNCH DATE DEPENDENT
002089,000662:
002090,000663:
002091,000664: # AZO (2D) P(I) (A-Z-O) PLANETARY INERITAL ORIENTATION ( .7753 REVOLUTIONS)
002092,000665: # ANGLE BETWEEN THE X AXIS OF BASIC REF
002093,000666: # COORDINATE SYSTEM AND THE X AXIS OF THE
002094,000667: # EARTH-FIXED COORDINATE SYSTEM AT
002095,000668: # --,196- UNIVERSAL TIME
002096,000669: # LAUNCH DATE DEPENDENT
002097,000670:
002098,000671:
002099,000672: # REFSMMAT (18D) PGM P50'S COMPUTE; MOST MAJOR PGMS. ( ORTHOGONAL UNIT VECTORS ) SEE BELOW
002100,000673: # TRANSFORMATION MATRIX BETWEEN
002101,000674: # STABLE MEMBER COORDINATE SYSTEM AND
002102,000675: # INERTIAL COORDINATE SYSTEM
002103,000676: # A S V +0 2DEC +.155540134
002104,000677: # A A +2 2DEC -.441118568
002105,000678: # M L +4 2DEC -.176696562
002106,000679: # P U +6 2DEC -.001190874
002107,000680: # L E +10 2DEC -.186282563 23A LUNAR LANDING PGM
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002109,000682: # E . +12 2DEC +.464001495
002110,000683: # . . +14 2DEC -.475190328
002111,000684: # . . +16 2DEC -.143920862
002112,000685: # . . +20 2DEC -.058999463
002113,000686:
002114,000687:
002115,000688: # RRECTCSM (6D) U(PGM) (R-C0) INTEGRATION INITIALIZATION (METERS,B-29 OR B-27 IF EARTH OR MOON
002116,000689: # PERMANENT STATE VECTORS AND TIMES
002117,000690: # RECTIFICATION POSITION VECTOR FOR CSM
002118,000691:
002119,000692:
002120,000693: # RRECTLEM (6D) U(PGM) (R-L-0) INTEGRATION INITIALIZATION (METERS,B-29 OR B-27 IF EARTH OR MOON
002121,000694: # PERMANENT STATE VECTORS AND TIMES
002122,000695: # RECTIFICATION POSITION VECTOR FOR LEM
002123,000696:
002124,000697:
002125,000698: # VRECTCSM (6D) U(PGM) (V-C-0) INTEGRATION INITIALIZATION (M/CSEC, B-7 OR B-5 IF EARTH OR MOON)
002126,000699: # PERMANENT STATE VECTORS AND TIMES
002127,000700: # RECTIFICATION VELOCITY VECTOR FOR CSM
002128,000701:
002129,000702:
002130,000703: # VRECTLEM (6D) U(PGM) (V-L-0) INTEGRATION INITIALIZATION (M/CSEC, B-7 OR B-5 IF EARTH OR MOON)
002131,000704: # PERMANENT STATE VECTORS AND TIMES
002132,000705: # RECTIFICATION VELOCITY VECTOR FOR LEM
002133,000706:
002134,000707:
002135,000708: # RCVCSM (6D) U(PGM) (R-C-CON) INTEGRATION INITIALIZATION (METERS,B-29 OR B-27 IF EARTH OR MOON
002136,000709: # PERMANENT STATE VECTORS AND TIMES
002137,000710: # CONIC POSITION VECTOR FOR CSM
002138,000711: # EQUALS RRECTCSM IF TCCSM =0
002139,000712:
002140,000713:
002141,000714: # RCVLEM (6D) U(PGM) (R-L-CON) INTEGRATION INITIALIZATION (METERS,B-29 OR B-27 IF EARTH OR MOON
002142,000715: # PERMANENT STATE VECTORS AND TIMES
002143,000716: # CONIC POSITION VECTOR FOR LEM
002144,000717: # EQUALS RRECTLEM IF TCLEM =0
002145,000718:
002146,000719:
002147,000720: # VCVCSM (6D) U(PGM) (V-C-CON) INTEGRATION INITIALIZATION (M/CSEC, B-7 OR B-5 IF EARTH OR MOON)
002148,000721: # PERMANENT STATE VECTORS AND TIMES
002149,000722: # CONIC VELOCITY VECTOR FOR CSM
002150,000723: # EQUALS VRECTCSM IF TCCSM =0
002151,000724:
002152,000725:
002153,000726: # VCVLEM (6D) U(PGM) (V-L-CON) INTEGRATION INITIALIZATION (M/CSEC, B-7 OR B-5 IF EARTH OR MOON)
002154,000727: # PERMANENT STATE VECTORS AND TIMES
002155,000728: # CONIC VELOCITY VECTOR FOR LEM
002156,000729: # EQUALS VRECTLEM IF TCLEM =0
002157,000730:
002158,000731:
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002160,000733: # DELTACSM (6D) P(U) (DELTA-C) INTEGRATION INITIALIZATION (METERS, B-22 OR B-18 IF EARTH OR MOON)
002161,000734: # PERMANENT STATE VECTORS AND TIMES
002162,000735: # POSITION DEVIATION VECTOR FOR CSM
002163,000736: # = 0 IF TCCSM =0
002164,000737: # 6DEC 0 LUMINARY LIST, INT. INIT.
002165,000738:
002166,000739:
002167,000740: # DELTALEM (6D) P(U) (DELTA-L) INTEGRATION INITIALIZATION (METERS, B-22 OR B-18 IF EARTH OR MOON)
002168,000741: # PERMANENT STATE VECTORS AND TIMES
002169,000742: # POSITION DEVIATION VECTOR FOR LEM
002170,000743: # = 0 IF TCLEM =0
002171,000744: # 6DEC 0 LUMINARY LIST, INT. INIT.
002172,000745:
002173,000746:
002174,000747: # NUVCSM (6D) P(U) (UPSILON-C) INTEGRATION INITIALIZATION (M/CSEC, B-3 OR B-(-1) IF EARTH OR MOON
002175,000748: # PERMANENT STATE VECTORS AND TIMES
002176,000749: # VELOCITY DEVIATION VECTOR FOR CSM
002177,000750: # = 0 IF TCCSM =0
002178,000751: # 6DEC 0 LUMINARY LIST, INT. INIT.
002179,000752:
002180,000753:
002181,000754: # NUVLEM (6D) P(U) (UPSILON-L) INTEGRATION INITIALIZATION (M/CSEC, B-3 OR B-(-1) IF EARTH OR MOON
002182,000755: # PERMANENT STATE VECTORS AND TIMES
002183,000756: # VELOCITY DEVIATION VECTOR FOR LEM
002184,000757: # = 0 IF TCLEM =0
002185,000758: # 6DEC 0 LUMINARY LIST, INT. INIT.
002186,000759:
002187,000760:
002188,000761: # TCCSM (2D) P(U) (TAU-C) INTEGRATION INITIALIZATION ( 0 CSEC, B-28 )
002189,000762: # PERMANENT STATE VECTORS AND TIMES
002190,000763: # TIME SINCE RECTIFICATION FOR CSM
002191,000764: # TIME ASSOCIATED WITH CSM CONIC POSITION,
002192,000765: # CONIC VELOCITY, POSITION DEVIATION AND
002193,000766: # VELOCITY DEVIATION VECTORS
002194,000767: # 2DEC 0 LUMINARY LIST, INT. INIT.
002195,000768:
002196,000769:
002197,000770: # TCLEM (2D) P(U) (TAU-L) INTEGRATION INITIALIZATION ( 0 CSEC, B-28 )
002198,000771: # PERMANENT STATE VECTORS AND TIMES
002199,000772: # TIME SINCE RECTIFICATION FOR LEM
002200,000773: # TIME ASSOCIATED WITH LEM CONICS AS ABOVE
002201,000774: # 2DEC 0 LUMINARY LIST, INT. INIT.
002202,000775:
002203,000776:
002204,000777: # TETCSM (2D) U(PGM) (T-C) INTEGRATION INITIALIZATION ( CSEC, B-28 )
002205,000778: # PERMANENT STATE VECTORS AND TIMES
002206,000779: # THE TIME THAT STATE VECTOR IS VALID;
002207,000780: # LUNAR ORBIT DEPENDENCE ON REAL TIME
002208,000781:
002209,000782:
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002211,000784: # TETLEM (2D) U(PGM) (T-L) INTEGRATION INITIALIZATION ( CSEC, B-28 )
002212,000785: # PERMANENT STATE VECTORS AND TIMES
002213,000786: # THE TIME THAT STATE VECTOR IS VALID;
002214,000787: # LUNAR ORBIT DEPENDENCE ON REAL TIME
002215,000788:
002216,000789:
002217,000790: # XKEPCSM (2D) P(U) (X-C) INTEGRATION INITIALIZATION (M**1/2, B-17 OR B-16 IF EARTH OR MOON)
002218,000791: # PERMANENT STATE VECTORS AND TIMES
002219,000792: # ROOT OF KEPLER'S EQUATION FOR CSM
002220,000793: # = 0 IF TCCSM =0
002221,000794: # 2DEC 0 LUMINARY LIST, INT. INIT.
002222,000795:
002223,000796:
002224,000797: # XKEPLEM (2D) P(U) (X-L) INTEGRATION INITIALIZATION (M**1/2, B-17 OR B-16 IF EARTH OR MOON)
002225,000798: # PERMANENT STATE VECTORS AND TIMES
002226,000799: # ROOT OF KEPLER'S EQUATION FOR LEM
002227,000800: # = 0 IF TCLEM =0
002228,000801: # 2DEC 0 LUMINARY LIST, INT. INIT.
002229,000802:
End of include-file PADLOADS.agc. Parent file is MAIN.agc