GAP: ASSEMBLE REVISION 069 OF AGC PROGRAM LUMINARY BY NASA 2021112-011 19:02 NOV. 25,1968Note that the date is the date of the printout, not the date of the program revision.
Source Code
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These source-code files were transcribed from scans made from Don Eyles's personal
copy of Luminary 069. They were scanned at archive.org's Boston
facility, and the scanning was sponsored by Onno Hommes. The code was transcribed
from these scans by a team of volunteers who are referenced in the program
comments. Comments from the original source code are prefixed with a single '#' symbol,
whereas comments added later are prefixed by "##" or "###". In some cases, where
similar code blocks exist in previously-transcribed AGC programs (primarily
Luminary 99, from Apollo 11) those code blocks were used as a starting point and
then corrected to agree with the Luminary 69 scans. The full scans are available
at the Virtual AGC
project's collection at archive.org, while more-convenient reduced-size (but reduced-quality)
images are available at
the main Virtual AGC website. Report any errors noted by creating an
issue report at the Virtual AGC
project's GitHub repository. Notations on the program listing read, in part:GAP: ASSEMBLE REVISION 069 OF AGC PROGRAM LUMINARY BY NASA 2021112-011 19:02 NOV. 25,1968Note that the date is the date of the printout, not the date of the program revision. |
001413,000002: ## Copyright: Public domain.
001414,000003: ## Filename: PADLOADS.agc
001415,000004: ## Purpose: The main source file for Luminary revision 069.
001416,000005: ## It is part of the source code for the original release
001417,000006: ## of the flight software for the Lunar Module's (LM) Apollo
001418,000007: ## Guidance Computer (AGC) for Apollo 10. The actual flown
001419,000008: ## version was Luminary 69 revision 2, which included a
001420,000009: ## newer lunar gravity model and only affected module 2.
001421,000010: ## This file is intended to be a faithful transcription, except
001422,000011: ## that the code format has been changed to conform to the
001423,000012: ## requirements of the yaYUL assembler rather than the
001424,000013: ## original YUL assembler.
001425,000014: ## Reference: pp. 37-52
001426,000015: ## Assembler: yaYUL
001427,000016: ## Contact: Ron Burkey <info@sandroid.org>.
001428,000017: ## Website: www.ibiblio.org/apollo/index.html
001429,000018: ## Mod history: 2016-12-13 MAS Created from Luminary 99.
001430,000019: ## 2016-12-20 MAS Began transcription.
001431,000020: ## 2016-12-23 MAS Completed transcription.
001432,000021: ## 2017-01-25 RSB Proofed comment text using octopus/prooferComments
001433,000022: ## and fixed errors found.
001434,000023:
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001436,000025: # ****** FORMAT ******
001437,000026:
001438,000027: # NAMETAG LENGTH TYPE ?? (GSOP NAME) PROGRAMS SAMPLE VALUE / UNITS
001439,000028: # DESCRIPTION
001440,000029: # MORE DESCRIPTION
001441,000030: # INCRE PRESENT ESTIMATED LGC SCALING SOURCE OF VALUE
001442,000031: # -MENT LENGTH AND VALUE
001443,000032:
001444,000033:
001445,000034: # ????? POSSIBLE TYPES ?????
001446,000035:
001447,000036: # HOW INITIATED: P = PADLOADED
001448,000037: # U = UPLINKED
001449,000038: # D = DSKY (ASTRONAUT)
001450,000039: # IF MODIFIED, HOW: (I) = INVARIANT
001451,000040: # (PGM)= PROGRAM GENERATED
001452,000041: # (F) = FRESH START REINITIALIZED
001453,000042: # (U) = UPLINKED
001454,000043: # (D) = DSKY (ASTRONAUT)
001455,000044:
001456,000045:
001457,000046:
001458,000047: # ****** EXAMPLE ******
001459,000048:
001460,000049: # FREAKOUT (2D) P(I) (F-OMEGA) P88'S-RENDESVOUS AVOIDANCE (2 MICROGRAMS)
001461,000050: # RESULTANT QUANTITY AFTER LONG EXPOSURE
001462,000051: # TO A 'STATUS QUO' PHILOSOPHY
001463,000052: # +0 1OCT 00534 E3 B-12 (SUN)LITE DAWNS
001464,000053: # +1 1OCT 07381 E-4 B-12
001465,000054:
001466,000055:
001467,000056: # *************
001468,000057:
001469,000058:
001470,000059: # FLGWRD10 (1D) P(PGM) MANY PROGRAMS, DAP-R03 (00000 FOR DESCENT, 10000 FOR ASCENT )
001471,000060: # MUST BE SET TO ONE VALUE OR OTHER DEPEND
001472,000061: # ING ON MISSION PHASE BECAUSE APSFLAG IS
001473,000062: # NOT INITIALIZED IN FRESH START AS ARE
001474,000063: # OTHER FLAGBITS. MUST USE DSKY OR R03
001475,000064: # OCT 00000
001476,000065:
001477,000066:
001478,000067: # FLAGWRD3 (1D) P(PGM) MANY PROGRAMS (10000 FOR REFSMMAT GOOD; 00000 FOR NO
001479,000068: # GOOD) REFSMFLG IS NOT INITIALIZED BY
001480,000069: # FRESH START AS OTHER BITS ARE.
001481,000070: # OCT 00000
001482,000071: # OR OCT 10000
001483,000072:
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001485,000074: # FLAGWRD8 (1D) P(PGM) MANY PROGRAMS (THERE ARE 8 POSSIBLE CONFIGURATIONS)
001486,000075: # CMOON, LMOON, & SURFFLAG ARE NOT INITIAL
001487,000076: # IZED BY FRESH START AS OTHER BITS ARE.
001488,000077: # OCT; BITS 8,11,12 NEED TO BE SET AS YOU DESIRE
001489,000078:
001490,000079:
001491,000080: # HIASCENT (1D) P(F) (HIASCENT) DIGITAL AUTOPILOT (5000 KG.; 11,100 LBS.)
001492,000081: # INITIAL STAGED MASS
001493,000082: # 1DEC 5050 B-16 SUNLITER # 147
001494,000083:
001495,000084:
001496,000085: # DKTRAP (1D) P(F) (-THETA-MAX-C) DAP STATE ESTIMATOR PARAM. (.14 DEG SCALED AT 4.5 DEG OR -510 DEC)
001497,000086: # LEM-CSM DOCKED, THRESHOLD FOR MEASURE-
001498,000087: # MENT INCORPORATION
001499,000088: # 1OCT 77001 R557 GSOP SEC 3.3.2.3 JUNE68
001500,000089:
001501,000090:
001502,000091: # DKOMEGAN (1D) P(F) (N-OMEGA-C) DAP STATE ESTIMATOR PARAM. ( 10 DEC )
001503,000092: # LEM-CSM DOCKED, RATE GAIN CONSTANT
001504,000093: # 1OCT 00012 R557 GSOP SEC 3.3.2.3 JUNE68
001505,000094:
001506,000095:
001507,000096: # DKKAOSNN (1D) P(F) (N-ALPHA-C) DAP STATE ESTIMATOR PARAM. ( 60 DEC )
001508,000097: # LEM-CSM DOCKED, ACCELERATION GAIN
001509,000098: # CONSTANT
001510,000099: # 1OCT 00074 R557 GSOP SEC 3.3.2.3 JUNE68
001511,000100:
001512,000101:
001513,000102: # LMTRAP (1D) P(F) (-THETA-MAX-L) DAP STATE ESTIMATOR PARAM. (.14 DEG SCALED AT 4.5 DEG )
001514,000103: # LEM-ALONE, THRESHOLD FOR MEASUREMENT
001515,000104: # INCORPORATION
001516,000105: # 1OCT 77001 R557 GSOP SEC 3.3.2.3 JUNE68
001517,000106:
001518,000107:
001519,000108: # LMOMEGAN (1D) P(F) (N-OMEGA-L) DAP STATE ESTIMATOR PARAM. ( 0 DEC )
001520,000109: # LEM-ALONE, RATE GAIN CONSTANT
001521,000110: # 1OCT 00000 R557 GSOP SEC 3.3.2.3 JUNE68
001522,000111:
001523,000112:
001524,000113: # LMKAOSN (1D) P(F) (N-ALPHA-L) DAP STATE ESTIMATOR PARAM. ( 60 DEC )
001525,000114: # LEM-ALONE, ACCELERATION GAIN CONSTANT
001526,000115: # 1OCT 00074 R557 GSOP SEC 3.3.2.3 JUNE68
001527,000116:
001528,000117:
001529,000118: # DKDB (1D) P(F) DAP ( 1.4 DEGREES EXPRESSED IN RADIANS )
001530,000119: # WIDTH OF DEADBAND FOR DOCKED RCS AUTO-
001531,000120: # PILOT (PI/DKDB RADIANS = DEADBAND)
001532,000121: # 1OCT 00200 LUMINARY ERASABLES
001533,000122:
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001535,000124: # ROLLTIME (1D) P(D) (R-TRIM) D.A.P. AND R03 ( 3000 CENTISECONDS OR 30 SECS. )
001536,000125: # TIME TO TRIM DESCENT Z GIMBAL (ROLL)
001537,000126: # 1DEC 3000 SUNDANCE PADLOAD MEMO
001538,000127:
001539,000128:
001540,000129: # PITTIME (1D) P(D) (P-TRIM) D.A.P. AND R03 ( 3000 CENTISECONDS OR 30 SECS. )
001541,000130: # TIME TO TRIM DESCENT Z GIMBAL (ROLL)
001542,000131: # 1DEC 3000 SUNDANCE PADLOAD MEMO
001543,000132:
001544,000133:
001545,000134: # POSTORKP (1D) P(PGM) (POSTORKP) DAP ACCUMULATED JET TORQUE ABOUT +P AXIS
001546,000135: # SCALED AT 32 JET-SEC, OR ABOUT 2.0 JET-
001547,000136: # 1OCT 00000 PCR 616 MSEC PER BIT. PERMITTED TO OVERFLOW.
001548,000137:
001549,000138:
001550,000139: # NEGTORKP (1D) P(PGM) (NEGTORKP) DAP ACCUMULATED JET TORQUE ABOUT -P AXIS
001551,000140: # SCALED AS POSTORKP.
001552,000141: # 1OCT 00000 PCR 616
001553,000142:
001554,000143:
001555,000144: # POSTORKU (1D) P(PGM) (POSTORKU) DAP ACCUMULATED JET TORQUE ABOUT +U AXIS
001556,000145: # SCALED AS POSTORKP.
001557,000146: # 1OCT 00000 PCR 616
001558,000147:
001559,000148:
001560,000149: # NEGTORKU (1D) P(PGM) (NEGTORKU) DAP ACCUMULATED JET TORQUE ABOUT -U AXIS
001561,000150: # SCALED AS POSTORKP.
001562,000151: # 1OCT 00000 PCR 616
001563,000152:
001564,000153:
001565,000154: # POSTORKV (1D) P(PCM) (POSTORKV) DAP ACCUMULATED JET TORQUE ABOUT +V AXIS
001566,000155: # SCALED AS POSTORKP
001567,000156: # 1OCT 00000 PCR 616
001568,000157:
001569,000158:
001570,000159: # ZOOMTIME (1D) P(2) (TAU-T) P40'S , LUNAR LANDING ( 26 SEC )
001571,000160: # TIME BETWEEN ENGINE ON AND THROTTLE UP
001572,000161: # COMMAND IN ANY DPS BURN
001573,000162: # 1DEC 2600 CSEC. SUNDANCE PADLOAD MEMO
001574,000163:
001575,000164:
001576,000165: # MASS (2D) P(U) (M) ALL P40'S, SERVICER (FULL LOADED VALUE APPROX. 15,043.8 KG.)
001577,000166: # VALUE FOR DESCENT STAGE WITH VARYING
001578,000167: # FUEL LOADS
001579,000168: # 2DEC B-16
001580,000169:
001581,000170:
001582,000171: # PIPASCFX (1D) P(I) (SFE1) IMU COMPENSATION PARAMETERS ( PARTS PER MILLION)
001583,000172: # SCALE FACTOR ERROR CORRECTION FACTOR
001584,000173: # 1OCT 75155 B-9 SUNDANCE PADLOAD MEMO
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001586,000175:
001587,000176:
001588,000177: # PIPASCFY (1D) P(I) (SFE2) IMU COMPENSATION PARAMETERS ( PARTS PER MILLION)
001589,000178: # SCALE FACTOR ERROR CORRECTION FACTOR
001590,000179: # 1OCT 77403 B-9 SUNDANCE PADLOAD MEMO
001591,000180:
001592,000181:
001593,000182: # PIPASCFZ (1D) P(I) (SFE3) IMU COMPENSATION PARAMETERS ( PARTS PER MILLION)
001594,000183: # SCALE FACTOR ERROR CORRECTION FACTOR
001595,000184: # 1OCT 65532 B-9 SUNDANCE PADLOAD MEMO
001596,000185:
001597,000186:
001598,000187: # PBIASX (1D) P(I) (BIAS1) IMU COMPENSATION PARAMETERS (PIPA PULSES PER CSEC OR CM PER SEC**2 )
001599,000188: # PIPA BIASES
001600,000189: # 1OCT 04554 B-5 SUNDANCE PADLOAD MEMO
001601,000190:
001602,000191:
001603,000192: # PBIASY (1D) P(I) (BIAS2) IMU COMPENSATION PARAMETERS (PIPA PULSES PER CSEC OR CM PER SEC**2 )
001604,000193: # PIPA BIASES
001605,000194: # 1OCT 06433 B-5 SUNDANCE PADLOAD MEMO
001606,000195:
001607,000196:
001608,000197: # PBIASZ (1D) P(I) (BIAS3) IMU COMPENSATION PARAMETERS (PIPA PULSES PER CSEC OR CM PER SEC**2 )
001609,000198: # PIPA BIASES
001610,000199: # 1OCT 77220 B-5 SUNDANCE PADLOAD MEMO
001611,000200:
001612,000201:
001613,000202: # ADIAX (1D) P(I) (ADIAX) IMU COMPENSATION PARAMETERS ( GYRO PULSES PER PIPA PULSE)
001614,000203: # (MILLI-EARTH-RATE UNIT (MERU) / GRAVITY)
001615,000204: # GYRO DRIFTS DUE TO ACCELERATION ALONG
001616,000205: # INPUT AXIS
001617,000206: # 1OCT 00436 B-6 SUNDANCE PADLOAD MEMO
001618,000207:
001619,000208:
001620,000209: # ADIAY (1D) P(I) (ADIAY) IMU COMPENSATION PARAMETERS ( GYRO PULSES PER PIPA PULSE)
001621,000210: # (MILLI-EARTH-RATE UNIT (MERU) / GRAVITY)
001622,000211: # GYRO DRIFTS DUE TO ACCELERATION ALONG
001623,000212: # INPUT AXIS
001624,000213: # 1OCT 76277 B-6 SUNDANCE PADLOAD MEMO
001625,000214:
001626,000215:
001627,000216: # ADIAZ (1D) P(I) (ADIAZ) IMU COMPENSATION PARAMETERS ( GYRO PULSES PER PIPA PULSE)
001628,000217: # (MILLI-EARTH-RATE UNIT (MERU) / GRAVITY)
001629,000218: # GYRO DRIFTS DUE TO ACCELERATION ALONG
001630,000219: # INPUT AXIS
001631,000220: # 1OCT 00064 B-6 SUNDANCE PADLOAD MEMO
001632,000221:
001633,000222:
001634,000223: # ADSRAX (1D) P(I) (ADSRAX) IMU COMPENSATION PARAMETERS ( GYRO PULSES PER PIPA PULSE)
001635,000224: # (MILLI-EARTH-RATE UNIT (MERU) / GRAVITY)
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001637,000226: # GYRO DRIFTS DUE TO ACCELERATION ALONG
001638,000227: # SPIN REFERENCE AXIS
001639,000228: # 1OCT 00064 B-6 SUNDANCE PADLOAD MEMO
001640,000229:
001641,000230:
001642,000231: # ADSRAY (1D) P(I) (ADSRAY) IMU COMPENSATION PARAMETERS ( GYRO PULSES PER PIPA PULSE)
001643,000232: # (MILLI-EARTH-RATE UNIT (MERU) / GRAVITY)
001644,000233: # GYRO DRIFTS DUE TO ACCELERATION ALONG
001645,000234: # SPIN REFERENCE AXIS
001646,000235: # 1OCT 00116 B-6 SUNDANCE PADLOAD MEMO
001647,000236:
001648,000237:
001649,000238: # ADSRAZ (1D) P(I) (ADSRAZ) IMU COMPENSATION PARAMETERS ( GYRO PULSES PER PIPA PULSE)
001650,000239: # (MILLI-EARTH-RATE UNIT (MERU) / GRAVITY)
001651,000240: # GYRO DRIFTS DUE TO ACCELERATION ALONG
001652,000241: # SPIN REFERENCE AXIS
001653,000242: # 1OCT 00064 B-6 SUNDANCE PADLOAD MEMO
001654,000243:
001655,000244:
001656,000245: # NBDX (1D) P(I) (NBDX) IMU COMPENSATION PARAMETERS ( GYRO PULSES PER CSEC.)
001657,000246: # OR (MILLI-EARTH-RATE UNIT CALLED 'MERU')
001658,000247: # GYRO BIAS DRIFTS
001659,000248: # 1OCT 77332 B-5 SUNDANCE PADLOAD MEMO
001660,000249:
001661,000250:
001662,000251: # NBDY (1D) P(I) (NBDY) IMU COMPENSATION PARAMETERS ( GYRO PULSES PER CSEC.)
001663,000252: # OR (MILLI-EARTH-RATE UNIT CALLED 'MERU')
001664,000253: # GYRO BIAS DRIFTS
001665,000254: # 1OCT 77415 B-5 SUNDANCE PADLOAD MEMO
001666,000255:
001667,000256:
001668,000257: # NBDZ (1D) P(I) (NBDZ) IMU COMPENSATION PARAMETERS ( GYRO PULSES PER CSEC.)
001669,000258: # OR (MILLI-EARTH-RATE UNIT CALLED 'MERU')
001670,000259: # GYRO BIAS DRIFTS
001671,000260: # 1OCT 00000 B-5 SUNDANCE PADLOAD MEMO
001672,000261:
001673,000262:
001674,000263: # WRENDPOS (1D) P(D-V67) (W-RR) P20 - RENDEZVOUS NAVIGATION (2440 METERS)
001675,000264: # W-MATRIX INERTIAL DIAGONAL ELEMENT
001676,000265: # PRESELECTED ERROR TRANSITION
001677,000266: # VALUE UNCERTAIN
001678,000267:
001679,000268:
001680,000269: # WRENDVEL (1D) P(D-V67) (W-RV) P20 - RENDEZVOUS NAVIGATION ( .0244 METERS PER CSEC.)
001681,000270: # W-MATRIX INERTIAL DIAGONAL ELEMENT
001682,000271: # PRESELECTED ERROR TRANSITION
001683,000272: # VALUE UNCERTAIN
001684,000273:
001685,000274:
001686,000275: # WSHAFT (1D) P(I) (W-THETA) P20-RENDESVOUS NAVIGATION ( 10 MILLIRADIANS)
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001688,000277: # W-MATRIX INERTIAL DIAGONAL ELEMENT
001689,000278: # SHAFT PRESELECTED ERROR TRANSITION
001690,000279: # VALUE UNCERTAIN
001691,000280:
001692,000281:
001693,000282: # WTRUN (1D) P(I) (W-BETA) P20-RENDESVOUS NAVIGATION ( 10 MILLIRADIANS -MR- )
001694,000283: # W-MATRIX INERTIAL DIAGONAL ELEMENT
001695,000284: # TRUNNIUN PRESELECTED ERROR TRANSITION
001696,000285: # VALUE UNCERTAIN
001697,000286:
001698,000287:
001699,000288: # RMAX (1D) P(I) (DELTA-RMAX) P20-RENDESVOUS NAVIGATION ( 9.26 TIMES 10 TO 4TH POWER)
001700,000289: # THRESHOLD LIMIT FOR POSITION CORRECTION
001701,000290: # VALUE UNCERTAIN
001702,000291:
001703,000292:
001704,000293: # VMAX (1D) P(I) (DELTA-VMAX) P20-RENDESVOUS NAVIGATION (9.144 TIMES 10 METERS PER SECOND)
001705,000294: # THRESHOLD LIMIT FOR VELOCITY CORRECTION
001706,000295: # VALUE UNCERTAIN
001707,000296:
001708,000297:
001709,000298: # SHAFTVAR (1D) P(U) (VAR-BETA) P22-RENDESVOUS RADAR ( 10 TO 6TH POWER SQUARE RADIANS)
001710,000299: # RR SHAFT ANGLE ERROR VARIANCE
001711,000300: # VALUE UNCERTAIN
001712,000301:
001713,000302:
001714,000303: # TRUNVAR (1D) P(U) (VAR-THETA) P22-RENDESVOUS RADAR ( 10 TO 6TH POWER SQUARE RADIANS)
001715,000304: # RR TRUNNION ANGLE ERROR VARIANCE
001716,000305: # VALUE UNCERTAIN
001717,000306:
001718,000307:
001719,000308: # WSURFPOS (1D) P(D-V67) (W-LR) P20'S-LUNAR SURFACE NAVIGAT
001720,000309:
001721,000310: # W-MATRIX INERTIAL DIAGONAL ELEMENT
001722,000311: # LUNAR ANALOG OF WRENPOS
001723,000312:
001724,000313:
001725,000314: # WSURFVEL (1D) P(D-V67) (W-LV) P20'S-LUNAR SURFACE NAVIGAT
001726,000315:
001727,000316: # W-MATRIX INERTIAL DIAGONAL ELEMENT
001728,000317: # LUNAR ANALOG OF WRENVEL
001729,000318:
001730,000319:
001731,000320: # RANGEVAR (2D) P(I) (VAR-R)) P20 NAVIGATION'S STATE VECTOR INCORPORATION ROUTINE
001732,000321: # (1/3 % QUANTITY SQUARED OR .11111111 E-4
001733,000322: # RANGE ERROR VARIANCE CORRESPONDING TO
001734,000323: # A PERCENTAGE ERROR
001735,000324: # 2DEC* .111111111 E-4 B12* GSOP
001736,000325:
001737,000326:
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001739,000328: # RATEVAR (2D) P(I) (VAR-V)) P20 NAVIGATION'S STATE VECTOR INCORPORATION ROUTINE
001740,000329: # (1.3/3 % QUANTITY SQUARED OR 1.8777 E-5
001741,000330: # VELOCITY ERROR VARIANCE CORRESPONDING TO
001742,000331: # A PERCENTAGE ERROR
001743,000332: # 2DEC 1.87777 E-5 B12 GSOP
001744,000333:
001745,000334:
001746,000335: # RVARMIN (1D) P(I) (VAR-RMIN) P20 NAVIGATION'S STATE VECTOR INCORPORATION ROUTINE
001747,000336: # (80/3 FT QUANTITY SQUARED)
001748,000337: # MIN. RENDESVOUS RADAR POSITION VARIANCE
001749,000338: # 1DEC 66.0 B-12 METERS**2 GSOP
001750,000339:
001751,000340:
001752,000341: # VVARMIN (1D) P(I) (VAR-VMIN) P20 NAVIGATION'S STATE VECTOR INCORPORATION ROUTINE (METERS/CSEC)**2
001753,000342: # (1.3 /3 FT PER SEC QUANTITY SQUARED)
001754,000343: # MINIMUM VELOCITY VARIANCE
001755,000344: # DEC .17445 E-5 B12 GSOP
001756,000345:
001757,000346:
001758,000347: # X789 (6D) P(PGM) (DELTA-BETA,DELTA-THETA,ZERO) P20S, MEAS.INCORP2 (MILLIRADIANS)
001759,000348: # 7,8,9TH COMPONENT NAVIGATION STATEVECTOR
001760,000349: # ALSO SHAFT + TRUNNION BIAS ESTIMATES
001761,000350: # +0 2DEC 0 INITIALLY
001762,000351: # +2 2DEC 0 INITIALLY LUMINARY LISTING
001763,000352: # +4 2DEC 0 ALWAYS
001764,000353:
001765,000354:
001766,000355: # ATIGINC (2D) P(I) (DELTA-TAU-3) P35 ( 7 MINUTES )
001767,000356: # ACTIVE VEHICLE TIME REQUIRED TO PREPARE
001768,000357: # FOR A TPM MANEUVER
001769,000358: # 2DEC 42000 B-28 (CSEC) SUNDANCE PADLOAD MEMO
001770,000359:
001771,000360:
001772,000361: # PTIGINC (2D) P(I) (DELTA-TAU-7) P75 (12 MINUTES )
001773,000362: # PASSIVE VEHICLE TIME REQUIRED TO PREPARE
001774,000363: # FOR A TPM MANEUVER
001775,000364: # 2DEC 72000 B-28 (CSEC) SUNDANCE PADLOAD MEMO
001776,000365:
001777,000366:
001778,000367: # AOTAZ (3D) P(I) (AZ1,AZ2,AZ3) AOTMARK (ALIGNMENT OPTICAL TELESCOPE) (-60 DEG, 0, +60 DEG)
001779,000368: # ANGLES BETWEEN THE LM NAVIGATION BASE Z
001780,000369: # AXIS AND AOT LINE OF SIGHT FOR DETENT1,
001781,000370: # 2,3. (AZIMUTH, 3 FORWARD VIEWING POSIT.)
001782,000371: # +0 OCT 65252
001783,000372: # +1 OCT 0 SUNDANCE PADLOAD MEMO
001784,000373: # +2 OCT 12525
001785,000374:
001786,000375:
001787,000376: # AOTEL (3D) P(I) (EL1,EL2,EL3) AOTMARK (ALIGNMENT OPTICAL TELESCOPE) (EACH IS 45 DEGREES)
001788,000377: # ANGLES BETWEEN THE LM NAVIGATION BASE
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001790,000379: # Y-Z PLANE & AOT LINE OF SIGHT FOR
001791,000380: # DETENT1,2,3. (ELEVATION, 3 FORWARD POS.)
001792,000381: # +0 OCT 10000
001793,000382: # +1 OCT 10000 SUNDANCE PADLOAD MEMO
001794,000383: # +2 OCT 10000
001795,000384:
001796,000385:
001797,000386: # DUMPCNT (1D) P(I) DOWNLINK TELEMETRY HOLDS THE NUMBER 'N' INDICATING THAT A
001798,000387: # DOWNLINK ERASABLE DUMP WILL SEND ALL OF
001799,000388: # ERASABLE STORAGE N TIMES (N=1 TO 4)
001800,000389: # OCT 20000 IF 4 ERASABLE DUMPS DESIRED
001801,000390: # OCT 10000 IF 2 COMPLETE DUMPS DESIRED LUMINARY
001802,000391: # OCT 04000 IF 1 COMPLETE ERASABLE DUMP LISTING
001803,000392:
001804,000393:
001805,000394: # AGSK (2D) P(U) V47(R47) AGS INITIALIZATION ( MINS ?)
001806,000395: # GROUND ELAPSED TIME OF LATEST AGS CLOCK
001807,000396: # ZERO
001808,000397:
001809,000398:
001810,000399: # RBRFG (6D) P(I) (R-OFG) LUNAR LANDING TARGET PARAMETERS ( METERS )
001811,000400: # RANGE VECTOR, BRAKING PHASE, HIGHGATE
001812,000401: # +0 2DEC* +2.92362643 E+ 3 B-24 *
001813,000402: # +2 2DEC* +0.00000000 E+ 0 B-24 * 23A LUMAR LANDING PGM
001814,000403: # +4 2DEC* -1.00839629 E+ 4 B-24 *
001815,000404:
001816,000405:
001817,000406: # VBRFG (6D) P(I) (V-OFG) LUNAR LANDING TARGET PARAMETERS ( METERS PER CSEC )
001818,000407: # VELOCITY VECTOR, BRAKING PHASE, HIGHGATE
001819,000408: # +0 2DEC* -4.83907728 E- 1 B-10 *
001820,000409: # +2 2DEC* +0.00000000 E+ 0 B-10 * 23A LUNAR LANDING PGM
001821,000410: # +4 2DEC* +1.71785605 E+ 0 B-10 *
001822,000411:
001823,000412:
001824,000413: # ABRFG (6D) P(I) (A-OFG) LUNAR LANDING TARGET PARAMETERS ( METERS PER CSEC SQUARED ) HIGHGATE
001825,000414: # ACCELERATION VECTOR, BRAKING PHASE
001826,000415: # +0 2DEC* -5.22722473 E- 5 B+04 *
001827,000416: # +2 2DEC* +0.00000000 E+ 0 B+04 * 23A LUNAR LANDING PGM
001828,000417: # +4 2DEC* -2.86621213 E- 4 B+04 *
001829,000418:
001830,000419:
001831,000420: # VBRFG* (2D) P(I) LUNAR LANDING TARGET PARAMETERS ( METERS PER CSEC )
001832,000421: # VELOCITY SCALAR, BRAKING PHASE, HIGHGATE
001833,000422: # 2DEC* +3.86517612 E+ 0 B-10 * 23A LUNAR LANDING PGM
001834,000423:
001835,000424:
001836,000425: # ABRFG* (2D) P(I) LUNAR LANDING TARGET PARAMETERS ( METERS PER CSEC SQUARED ) HIGH GATE
001837,000426: # ACCELERATION SCALAR, BRAKING PHASE
001838,000427: # 2DEC* -1.71972727 E- 3 B+04 * 23A LUNAR LANDING PGM
001839,000428:
001840,000429:
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Page 45 |
001842,000431: # JBRFG* (2D) P(I) (J-OFZG) LUNAR LANDING TARGET PARAMETERS ( METERS PER CSEC CUBED )
001843,000432: # JERK SCALAR, BRAKING PHASE, HIGHGATE
001844,000433: # 2DEC* -2.90216724 E- 8 B+18 * 23A LUNAR LANDING PGM
001845,000434:
001846,000435:
001847,000436: # RAPFG (6D) P(I) (R-1FG) LUNAR LANDING TARGET PARAMETERS ( METERS )
001848,000437: # RANGE VECTOR, APPROACH PHASE, LOWGATE
001849,000438: # +0 2DEC* +2.35092239 E+ 1 B-24 *
001850,000439: # +2 2DEC* +0.00000000 E+ 0 B-24 * 23A LUNAR LANDING PGM
001851,000440: # +4 2DEC* -5.28319999 E- 1 B-24 *
001852,000441:
001853,000442:
001854,000443: # VAPFG (6D) P(I) (V-1FG) LUNAR LANDING TARGET PARAMETERS ( METERS PER CSEC )
001855,000444: # VELOCITY VECTOR, APPROACH PHASE, LOWGATE
001856,000445: # +0 2DEC* -9.44879999 E- 3 B-10 *
001857,000446: # +2 2DEC* +0.00000000 E+ 0 B-10 * 23A LUNAR LANDNNG PGM
001858,000447: # +4 2DEC* +3.96239999 E- 3 B-10 *
001859,000448:
001860,000449:
001861,000450: # AAPFG (6D) P(I) (A-1FG) LUNAR LANDING TARGET PARAMETERS ( METERS PER CSEC SQUARED ) LOW GATE
001862,000451: # ACCELERATION VECTOR, APPROACH PHASE
001863,000452: # +0 2DEC* +1.52399999 E- 6 B+04 *
001864,000453: # +2 2DEC* +0.00000000 E+ 0 B+04 * 23A LUNAR LANDING PGM
001865,000454: # +4 2DEC* -1.98119999 E- 5 B+04 *
001866,000455:
001867,000456:
001868,000457: # VAPFG* (2D) P(I) LUNAR LANDING TARGET PARAMETERS ( METERS PER CSEC )
001869,000458: # VELOCITY SCALAR, APPROACH PHASE, LOWGATE
001870,000459: # 2DEC* +8.91539999 E- 3 B-10 * 23A LUNAR LANDING PGM
001871,000460:
001872,000461:
001873,000462: # AAPFG* (2D) P(I) LUNAR LANDING TARGET PARAMETERS ( METERS PER CSEC SQUARED ) LOW GATE
001874,000463: # ACCELERATION SCALAR, APPROACH PHASE
001875,000464: # 2DEC* -1.18871999 E- 4 B+04 * 23A LUNAR LANDING PGM
001876,000465:
001877,000466:
001878,000467: # JAPFG* (2D) P(I) (J-1FZG) LUNAR LANDING TARGET PARAMETERS ( METERS PER CSEC CUBED )
001879,000468: # JERK SCALAR, APPROACH PHASE, LOWGATE
001880,000469: # 2DEC* +8.37249023 E- 8 B+18 * 23A LUNAR LANDING PGM
001881,000470:
001882,000471:
001883,000472: # VIGN (2D) P(I) (V-IGG) LUNAR LANDING TARGET PARAMETERS (16.99 METERS PER SECOND )
001884,000473: # DESIRED SPEED FOR IGNITION
001885,000474: # 2DEC* +1.69952182 E+ 1 B-10 * 23A LUNAR LANDING PGM
001886,000475:
001887,000476:
001888,000477: # RIGNX (2D) P(I) (R-IGXG) LUNAR LANDING TARGET PARAMETERS ( 40127 METERS )
001889,000478: # DESIRED X-COMPONENT IN GUIDANCE COORDIN-
001890,000479: # ATES FOR IGNITION ("ALTITUDE")
001891,000480: # 2DEC* -4.09432231 E+ 4 B-24 * 23A LUNAR LANDING PGM
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Page 46 |
001893,000482:
001894,000483:
001895,000484: # RIGNZ (2D) P(I) (R-IGZG) LUNAR LANDING TARGET PARAMETERS ( 437347 METERS )
001896,000485: # DESIRED Z-COMPONENT IN GUIDANCE COORDIN-
001897,000486: # ATES FOR IGNITION ("GROUND RANGE")
001898,000487: # 2DEC* -4.40014934 E+ 5 B-24 * 23A LUNAR LANDING PGM
001899,000488:
001900,000489:
001901,000490: # KIGNX/B4 (2D) P(I) (K-X) LUNAR LANDING TARGET PARAMETERS
001902,000491: # IGNITION ALGORITHM SENSITIVITY COEF.
001903,000492: # 2DEC -.022499999 23A LUNAR LANDING PGM
001904,000493:
001905,000494:
001906,000495: # KIGNY/B8 (2D) P(I) (K-Y) LUNAR LANDING TARGET PARAMETERS
001907,000496: # IGNITION ALGORITHM SENSITIVITY COEF.
001908,000497: # 2DEC -.174716605 23A LUNAR LANDING PGM
001909,000498:
001910,000499:
001911,000500: # KIGNV/B4 (2D) P(I) (K-V) LUNAR LANDING TARGET PARAMETERS
001912,000501: # IGNITION ALGORITHM SENSITIVITY COEF.
001913,000502: # 2DEC -.165939331 23A LUNAR LANDING PGM
001914,000503:
001915,000504:
001916,000505: # LOWCRIT (1D) P(I) LUNAR LANDING TARGET PARAMETERS (2.7 LBS/BIT) (57% NOMINAL MAX THRUST )
001917,000506: # LOWER LIMIT BEYOND WHICH THROTTLE SET TO
001918,000507: # EITHER MAXIMUM OR TRUE VALUE
001919,000508: # 1OCT 04251
001920,000509:
001921,000510:
001922,000511: # HIGHCRIT (1D) P(I) LUNAR LANDING TARGET PARAMETERS ( LBS / BIT : 63% NOMINAL MAX THRUST)
001923,000512: # UPPER LIMIT BEYOND WHICH THROTTLE SET TO
001924,000513: # EITHER MAXIMUM OR TRUE VALUE ?
001925,000514: # 1OCT 04622
001926,000515:
001927,000516:
001928,000517: # TENDAPPR (1D) P(I) LUNAR LANDING TARGET PARAMETERS ( 10 SECONDS )
001929,000518: # TIME CRITERION FOR SWITCHING OUT OF
001930,000519: # APPROACH PHASE QUADRATIC GUIDANCE
001931,000520: # DEC +10 E2 B-17 (BOTH ONEAND TWO-PHASE)
001932,000521: # LUM MEMO # 45
001933,000522:
001934,000523: # TENDBRAK (1D) P(I) LUNAR LANDING TARGET PARAMETER ( 200 SECONDS )
001935,000524: # TIME CRITERION FOR SWITCH TO APPROACH
001936,000525: # PHASE (P64 )
001937,000526: # DEC +20 E2 B-17 (TWO-PHASE LANDING MODE) LUM MEMO
001938,000527: # DEC +200 E2 B-17 (ONE-PHASE LANDING MODE) #45
001939,000528:
001940,000529:
001941,000530: # RPCRTIME (1D) P(I) LUNAR LANDING TARGET PARAMETERS (300 SECONDS )
001942,000531: # TIME CRITERION FOR REPOSITIONING LR
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Page 47 |
001944,000533: # ANTENNA
001945,000534: # DEC +5 E2 B-17 (TWO-PHASE LANDING MODE) LUM MEMO
001946,000535: # DEC +300 E2 B-17 (ONE-PHASE LANDING MODE) #45
001947,000536:
001948,000537:
001949,000538: # RPCRTQSW (1D) P(2) LUNAR LANDING TARGET PARAMETERS ( COS 45 DEGREES SCALED AT B+1 )
001950,000539: # X COMPONENT OF X-AXIS OF VEHICLE IN
001951,000540: # STABLE MEMBER COORDINATES: CRITERION FOR
001952,000541: # REPOSITIONING LR ANTENNA
001953,000542: # DEC 00000 (TWO-PHASE LANDING MODE) SUNLITER
001954,000543: # DEC .35356 (ONE-PHASE LANDING MODE) # 260
001955,000544:
001956,000545:
001957,000546: # LRALPHA (1D) P(I) (ALPHA-1) LANDING RADAR P63-67 ( 6 DEGREES)
001958,000547: # POSITION 1, X ROTATION
001959,000548: # 1OCT 01042 SUNLITER # 168
001960,000549:
001961,000550:
001962,000551: # LRBETA1 (1D) P(I) (BETA-1) LANDING RADAR P63-67 ( 24 DEGREES)
001963,000552: # POSITION 1, Y ROTATION
001964,000553: # 1OCT 04210
001965,000554:
001966,000555:
001967,000556: # LRALPHA2 (1D) P(I) (ALPHA-2) LANDING RADAR P63-67 ( 6 DEGREES)
001968,000557: # POSITION 2, X ROTATION
001969,000558: # 1OCT 01042 SUNLITER # 168
001970,000559:
001971,000560:
001972,000561: # LRBETA2 (1D) P(I) (BETA-2) LANDING RADAR P63-67 ( 0 DEGREES)
001973,000562: # POSITION 2, Y ROTATION
001974,000563: # 1OCT 00000 SUNLITER # 168
001975,000564:
001976,000565:
001977,000566: # LRHMAX (1D) P(I) (H-M) LANDING RADAR P63-67 (50,000 FEET)
001978,000567: # ALTITUDE WEIGHTING FUNCTION PARAMETER
001979,000568: # 1DEC 15240 PCR # 253
001980,000569:
001981,000570:
001982,000571: # LRVMAX (1D) P(I) (V-M) LANDING RADAR P63-67 (2000 FT PER SECOND)
001983,000572: # VELOCITY WEIGHTING FUNCTION PARAMETER
001984,000573: # 1DEC .047625 SUNLITER # 168
001985,000574:
001986,000575:
001987,000576: # LRWH (1D) P(I) (K-H) LANDING RADAR P63-67 (.35 DEC)
001988,000577: # ALTITUDE WEIGHTING FUNCTION PARAMETER
001989,000578: # 1DEC .35 PCR # 253
001990,000579:
001991,000580:
001992,000581: # LRWVZ (1D) P(I) (K-VZ) LANDING RADAR P63-67 ( .7 DEC )
001993,000582: # Z VELOCITY WEIGHTING FUNCTION PARAMETER
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Page 48 |
001995,000584: # 1DEC .7 SUNLITER # 168
001996,000585:
001997,000586:
001998,000587: # LRWVY (1D) P(I) (K-VY) LANDING RADAR P63-67 ( .7 DEC )
001999,000588: # Y VELOCITY WEIGHTING FUNCTION PARAMETER
002000,000589: # 1DEC .7 SUNLITER # 168
002001,000590:
002002,000591:
002003,000592: # LRWVX (1D) P(I) (K-VX) LANDING RADAR P63-67 ( .4 DEC )
002004,000593: # X VELOCITY WEIGHTING FUNCTION PARAMETER
002005,000594: # 1DEC .4 SUNLITER # 168
002006,000595:
002007,000596:
002008,000597: # DELQFIX (2D) P(I) DELQFIX R12 50 FEET
002009,000598: # LR ALT DATA REASONABLENESS TEST PARM.
002010,000599: # 2DEC 15.24 B-24 PCRS 639 &248
002011,000600:
002012,000601:
002013,000602: # TBRKPNT (1D) P(I) P70-71 ASCENT (540 SEC OR 54000 CSEC )
002014,000603: # TFI BRANCH TIME; ABORT TARGET
002015,000604: # 1DEC 54000 B-17 PCR # 133
002016,000605:
002017,000606:
002018,000607: # ABTVINJ1 (2D) P(I) P70-71 ASCENT (5551 FEET / SEC)
002019,000608: # DESIRED INJECTION VELOCITY FOR TFI
002020,000609: # BRANCH TIME LESS THAN TBRKPNT; VELOCITY
002021,000610: # REQUIRED TO GAIN 60 NM APOLUNE ORBIT
002022,000611: # 2DEC 16.91945 B-7 PCR # 133
002023,000612:
002024,000613:
002025,000614: # ABTVINJ2 (2D) P(I) P70-71 ASCENT (5510 FEET / SEC)
002026,000615: # DESIRED INJECTION VELOCITY FOR TFI
002027,000616: # BRANCH TIME GREATER THAN TBRKPNT; VEL
002028,000617: # REQUIRED TO GAIN 30 NM APOLUNE ORBIT
002029,000618: # 2DEC 16.79448 B-7 PCR # 133
002030,000619:
002031,000620:
002032,000621: # TLAND (2D) P(U) LUNAR LANDING TARGET PARAMETERS ( 2DEC 34573411 <CSEC>)
002033,000622: # BRAKING PHASE TIME OF LANDING ON MOON
002034,000623: # LAUNCH DATE DEPENDENT
002035,000624:
002036,000625:
002037,000626: # RLS (6D) P(U) (R-LS) P20-22 LUNAR SURFACE NAVIGATION (1.7 TIMES 10**6 METERS; 0 M; 0 METER)
002038,000627: # SAMPLE VALUE AT 0DEG LATITUDE & LONGITUD
002039,000628: # LANDING SITE VECTOR, MOON REFERENCE
002040,000629: # LAUNCH DATE DEPENDENT
002041,000630:
002042,000631:
002043,000632: # 504LM (6D) P(I) (L-M) PLANETARY INERTIAL ORIENTATION ( RADIANS) 8.5 X 10**-5
002044,000633: # 73.9 X 10**-5
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Page 49 |
002046,000635: # 6.6 X 10**-5
002047,000636: # MOON LIBRATION VECTOR EXPRESSED AT MID-
002048,000637: # POINT OF MISSION IN MOON FIXED COORDIN.
002049,000638: # LAUNCH DATE DEPENDENT
002050,000639:
002051,000640:
002052,000641: # TEPHEM (3D) P(U) (T-0) LUNAR + SOLAR EPHEMERIDES,P50S (2.23452 X 10**9 CSEC )
002053,000642: # LAUNCH TIME - ELAPSED TIME BETWEEN MID-
002054,000643: # NITE JULY 1 UNIVERSAL TIME PRECEEDING
002055,000644: # LAUNCH AND THE TIME THAT THE COMPUTER
002056,000645: # CLOCK WAS ZEROED AT TIME OF LAUNCH
002057,000646: # +0 DEC LAUNCH DATE DEPENDENT
002058,000647: # +1 2DEC
002059,000648:
002060,000649:
002061,000650: # AXO (2D) P(I) (A-X-TLO) PLANETARY INERTIAL ORIENTATION ( 4.65 X 10**-5 RADIANS)
002062,000651: # EARTH ANALOGS OF 504LM
002063,000652: # FUNCTION OF LAUNCH TIME USED BY NAVIGA-
002064,000653: # TION PROGRAMS
002065,000654: # SMALL ANGLE ABOUT THE X-AXIS OF BASIC
002066,000655: # REFERENCE COORDINATE SYSTEM.....
002067,000656: # LAUNCH DATE DEPENDENT
002068,000657:
002069,000658:
002070,000659: # -AYO (2D) P(I) (A-Y-TLO) PLANETARY INERTIAL ORIENTATION ( 2.147 X 10**-5 RADIANS)
002071,000660: # SEE AXO COMMENTS
002072,000661: # SMALL ANGLE ABOUT THE Y AXIS OF BASIC
002073,000662: # REFERENCE COORDINATE SYSTEM THAT DES-
002074,000663: # CRIBES THE PRECESSION AND NUTATION OF
002075,000664: # THE EARTH'S POLAR AXIS
002076,000665: # LAUNCH DATE DEPENDENT
002077,000666:
002078,000667:
002079,000668: # AZO (2D) P(I) (A-Z-O) PLANETARY INERITAL ORIENTATION ( .7753 REVOLUTIONS)
002080,000669: # ANGLE BETWEEN THE X AXIS OF BASIC REF
002081,000670: # COORDINATE SYSTEM AND THE X AXIS OF THE
002082,000671: # EARTH-FIXED COORDINATE SYSTEM AT
002083,000672: # --,196- UNIVERSAL TIME
002084,000673: # LAUNCH DATE DEPENDENT
002085,000674:
002086,000675:
002087,000676: # REFSMMAT (18D) PGM P50'S COMPUTE; MOST MAJOR PGMS. ( ORTHOGONAL UNIT VECTORS ) SEE BELOW
002088,000677: # TRANSFORMATION MATRIX BETWEEN
002089,000678: # STABLE MEMBER COORDINATE SYSTEM AND
002090,000679: # INERTIAL COORDINATE SYSTEM
002091,000680: # A S V +0 2DEC +.155540134
002092,000681: # A A +2 2DEC -.441118568
002093,000682: # M L +4 2DEC -.176696562
002094,000683: # P U +6 2DEC -.001190874
002095,000684: # L E +10 2DEC -.186282563 23A LUNAR LANDING PGM
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Page 50 |
002097,000686: # E . +12 2DEC +.464001495
002098,000687: # . . +14 2DEC -.475190328
002099,000688: # . . +16 2DEC -.143920862
002100,000689: # . . +20 2DEC -.058999463
002101,000690:
002102,000691:
002103,000692: # RRECTCSM (6D) U(PGM) (R-C0) INTEGRATION INITIALIZATION (METERS,B-29 OR B-27 IF EARTH OR MOON
002104,000693: # PERMANENT STATE VECTORS AND TIMES
002105,000694: # RECTIFICATION POSITION VECTOR FOR CSM
002106,000695:
002107,000696:
002108,000697: # RRECTLEM (6D) U(PGM) (R-L-0) INTEGRATION INITIALIZATION (METERS,B-29 OR B-27 IF EARTH OR MOON
002109,000698: # PERMANENT STATE VECTORS AND TIMES
002110,000699: # RECTIFICATION POSITION VECTOR FOR LEM
002111,000700:
002112,000701:
002113,000702: # VRECTCSM (6D) U(PGM) (V-C-0) INTEGRATION INITIALIZATION (M/CSEC, B-7 OR B-5 IF EARTH OR MOON)
002114,000703: # PERMANENT STATE VECTORS AND TIMES
002115,000704: # RECTIFICATION VELOCITY VECTOR FOR CSM
002116,000705:
002117,000706:
002118,000707: # VRECTLEM (6D) U(PGM) (V-L-0) INTEGRATION INITIALIZATION (M/CSEC, B-7 OR B-5 IF EARTH OR MOON)
002119,000708: # PERMANENT STATE VECTORS AND TIMES
002120,000709: # RECTIFICATION VELOCITY VECTOR FOR LEM
002121,000710:
002122,000711:
002123,000712: # RCVCSM (6D) U(PGM) (R-C-CON) INTEGRATION INITIALIZATION (METERS,B-29 OR B-27 IF EARTH OR MOON
002124,000713: # PERMANENT STATE VECTORS AND TIMES
002125,000714: # CONIC POSITION VECTOR FOR CSM
002126,000715: # EQUALS RRECTCSM IF TCCSM =0
002127,000716:
002128,000717:
002129,000718: # RCVLEM (6D) U(PGM) (R-L-CON) INTEGRATION INITIALIZATION (METERS,B-29 OR B-27 IF EARTH OR MOON
002130,000719: # PERMANENT STATE VECTORS AND TIMES
002131,000720: # CONIC POSITION VECTOR FOR LEM
002132,000721: # EQUALS RRECTLEM IF TCLEM =0
002133,000722:
002134,000723:
002135,000724: # VCVCSM (6D) U(PGM) (V-C-CON) INTEGRATION INITIALIZATION (M/CSEC, B-7 OR B-5 IF EARTH OR MOON)
002136,000725: # PERMANENT STATE VECTORS AND TIMES
002137,000726: # CONIC VELOCITY VECTOR FOR CSM
002138,000727: # EQUALS VRECTCSM IF TCCSM =0
002139,000728:
002140,000729:
002141,000730: # VCVLEM (6D) U(PGM) (V-L-CON) INTEGRATION INITIALIZATION (M/CSEC, B-7 OR B-5 IF EARTH OR MOON)
002142,000731: # PERMANENT STATE VECTORS AND TIMES
002143,000732: # CONIC VELOCITY VECTOR FOR LEM
002144,000733: # EQUALS VRECTLEM IF TCLEM =0
002145,000734:
002146,000735:
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Page 51 |
002148,000737: # DELTACSM (6D) P(U) (DELTA-C) INTEGRATION INITIALIZATION (METERS, B-22 OR B-18 IF EARTH OR MOON)
002149,000738: # PERMANENT STATE VECTORS AND TIMES
002150,000739: # POSITION DEVIATION VECTOR FOR CSM
002151,000740: # = 0 IF TCCSM =0
002152,000741: # 6DEC 0 LUMINARY LIST, INT. INIT.
002153,000742:
002154,000743:
002155,000744: # DELTALEM (6D) P(U) (DELTA-L) INTEGRATION INITIALIZATION (METERS, B-22 OR B-18 IF EARTH OR MOON)
002156,000745: # PERMANENT STATE VECTORS AND TIMES
002157,000746: # POSITION DEVIATION VECTOR FOR LEM
002158,000747: # = 0 IF TCLEM =0
002159,000748: # 6DEC 0 LUMINARY LIST, INT. INIT.
002160,000749:
002161,000750:
002162,000751: # NUVCSM (6D) P(U) (UPSILON-C) INTEGRATION INITIALIZATION (M/CSEC, B-3 OR B-(-1) IF EARTH OR MOON
002163,000752: # PERMANENT STATE VECTORS AND TIMES
002164,000753: # VELOCITY DEVIATION VECTOR FOR CSM
002165,000754: # = 0 IF TCCSM =0
002166,000755: # 6DEC 0 LUMINARY LIST, INT. INIT.
002167,000756:
002168,000757:
002169,000758: # NUVLEM (6D) P(U) (UPSILON-L) INTEGRATION INITIALIZATION (M/CSEC, B-3 OR B-(-1) IF EARTH OR MOON
002170,000759: # PERMANENT STATE VECTORS AND TIMES
002171,000760: # VELOCITY DEVIATION VECTOR FOR LEM
002172,000761: # = 0 IF TCLEM =0
002173,000762: # 6DEC 0 LUMINARY LIST, INT. INIT.
002174,000763:
002175,000764:
002176,000765: # TCCSM (2D) P(U) (TAU-C) INTEGRATION INITIALIZATION ( 0 CSEC, B-28 )
002177,000766: # PERMANENT STATE VECTORS AND TIMES
002178,000767: # TIME SINCE RECTIFICATION FOR CSM
002179,000768: # TIME ASSOCIATED WITH CSM CONIC POSITION,
002180,000769: # CONIC VELOCITY, POSITION DEVIATION AND
002181,000770: # VELOCITY DEVIATION VECTORS
002182,000771: # 2DEC 0 LUMINARY LIST, INT. INIT.
002183,000772:
002184,000773:
002185,000774: # TCLEM (2D) P(U) (TAU-L) INTEGRATION INITIALIZATION ( 0 CSEC, B-28 )
002186,000775: # PERMANENT STATE VECTORS AND TIMES
002187,000776: # TIME SINCE RECTIFICATION FOR LEM
002188,000777: # TIME ASSOCIATED WITH LEM CONICS AS ABOVE
002189,000778: # 2DEC 0 LUMINARY LIST, INT. INIT.
002190,000779:
002191,000780:
002192,000781: # TETCSM (2D) U(PGM) (T-C) INTEGRATION INITIALIZATION ( CSEC, B-28 )
002193,000782: # PERMANENT STATE VECTORS AND TIMES
002194,000783: # THE TIME THAT STATE VECTOR IS VALID;
002195,000784: # LUNAR ORBIT DEPENDENCE ON REAL TIME
002196,000785:
002197,000786:
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002199,000788: # TETLEM (2D) U(PGM) (T-L) INTEGRATION INITIALIZATION ( CSEC, B-28 )
002200,000789: # PERMANENT STATE VECTORS AND TIMES
002201,000790: # THE TIME THAT STATE VECTOR IS VALID;
002202,000791: # LUNAR ORBIT DEPENDENCE ON REAL TIME
002203,000792:
002204,000793:
002205,000794: # XKEPCSM (2D) P(U) (X-C) INTEGRATION INITIALIZATION (M**1/2, B-17 OR B-16 IF EARTH OR MOON)
002206,000795: # PERMANENT STATE VECTORS AND TIMES
002207,000796: # ROOT OF KEPLER'S EQUATION FOR CSM
002208,000797: # = 0 IF TCCSM =0
002209,000798: # 2DEC 0 LUMINARY LIST, INT. INIT.
002210,000799:
002211,000800:
002212,000801: # XKEPLEM (2D) P(U) (X-L) INTEGRATION INITIALIZATION (M**1/2, B-17 OR B-16 IF EARTH OR MOON)
002213,000802: # PERMANENT STATE VECTORS AND TIMES
002214,000803: # ROOT OF KEPLER'S EQUATION FOR LEM
002215,000804: # = 0 IF TCLEM =0
002216,000805: # 2DEC 0 LUMINARY LIST, INT. INIT.
002217,000806:
End of include-file PADLOADS.agc. Parent file is MAIN.agc