Source Code
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These source-code files are part of a reconstructed copy of Luminary 97, the
second release of the Apollo 11 Lunar Module (LM) Apollo Guidance Computer
(AGC) software. It was created to fix two incorrect ephemeris constants in
Luminary 96, as described by anomaly report LNY-59.
The reconstruction began with source code of Luminary 99 revision 1 previously
transcribed from a digitized copy of that program. The code was then updated
by undoing changes described in original Luminary memos 83 and 85, using asterisks
indicating changed lines in the listing as a guide. The reconstruction was
verified by matching memory-bank checksums to those listed in drawing 2021152D.
Note that page numbers in the reconstructed code match those on the Luminary 099
revision 001 printout, although the added code would likely have changed page
numbers for a real Luminary 97 listing.
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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013788,000002: ## Copyright: Public domain.
013789,000003: ## Filename: R63.agc
013790,000004: ## Purpose: A section of Luminary revision 97.
013791,000005: ## It is part of the reconstructed source code for the
013792,000006: ## second release of the flight software for the Lunar
013793,000007: ## Module's (LM) Apollo Guidance Computer (AGC) for Apollo 11.
013794,000008: ## It was created to fix two incorrect ephemeris constants in
013795,000009: ## Luminary 96, as described by anomaly report LNY-59.
013796,000010: ## The code has been recreated from a copy of Luminary 99
013797,000011: ## revision 001, using asterisks indicating changed lines in
013798,000012: ## the listing and Luminary Memos #83 and #85, which list
013799,000013: ## changes between Luminary 97 and 98, and 98 and 99. The
013800,000014: ## code has been adapted such that the resulting bugger words
013801,000015: ## exactly match those specified for Luminary 97 in NASA drawing
013802,000016: ## 2021152D, which gives relatively high confidence that the
013803,000017: ## reconstruction is correct.
013804,000018: ## Reference: pp. 338-341
013805,000019: ## Assembler: yaYUL
013806,000020: ## Contact: Ron Burkey <info@sandroid.org>.
013807,000021: ## Website: www.ibiblio.org/apollo/index.html
013808,000022: ## Mod history: 2019-07-28 MAS Created from Luminary 99.
013809,000023:
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Page 338
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013811,000025: # SUBROUTINE NAME: V89CALL
013812,000026: # MOD NO: 0 DATE: 9 JAN 1968
013813,000027: # MOD BY: DIGITAL DEVEL GROUP LOG SECTION: R63
013814,000028:
013815,000029: # FUNCTIONAL DESCRIPTION:
013816,000030:
013817,000031: # CALLED BY VERB 89 ENTER DURING P00. PRIO 10 USED. CALCULATES AND
013818,000032: # DISPLAYS FINAL FDAI BALL ANGLES TO POINT LM +X OR +Z AXIS AT CSM.
013819,000033:
013820,000034: # 1. KEY IN V 89 E ONLY IF IN PROG 00. IF NOT IN P00, OPERATOR ERROR AND
013821,000035: # EXIT R63, OTHERWISE CONTINUE.
013822,000036:
013823,000037: # 2. IF IN P00, DO IMU STATUS CHECK ROUTINE (R02BOTH). IF IMU ON AND ITS
013824,000038: # ORIENTATION KNOWN TO LGC, CONTINUE.
013825,000039:
013826,000040: # 3. FLASH DISPLAY V 04 N 06. R2 INDICATES WHICH SPACECRAFT AXIS IS TO
013827,000041: # BE POINTED AT CSM. INITIAL CHOICE IS PREFERRED (+Z) AXIS (R2=1).
013828,000042: # ASTRONAUT CAN CHANGE TO (+X) AXIS (R2 NOT =1) BY V 22 E 2 E. CONTINUE
013829,000043: # AFTER KEYING IN PROCEED.
013830,000044:
013831,000045: # 4. BOTH VEHICLE STATE VECTORS UPDATED BY CONIC EQS.
013832,000046:
013833,000047: # 5. HALF MAGNITUDE UNIT LOS VECTOR (IN STABLE MEMBER COORDINATES) AND
013834,000048: # HALF MAGNITUDE UNIT SPACECRAFT AXIS VECTOR (IN BODY COORDINATES)
013835,000049: # PREPARED FOR VECPOINT.
013836,000050:
013837,000051: # 6. GIMBAL ANGLES FROM VECPOINT TRANSFORMED INTO FDAI BALL ANGLES BY
013838,000052: # BALLANGS. FLASH DISPLAY V 06 N 18 AND AWAIT RESPONSE.
013839,000053:
013840,000054: # 7. RECYCLE - RETURN TO STEP 4.
013841,000055: # TERMINATE - EXIT R63.
013842,000056: # PROCEED - RESET 3AXISFLG AND CALL R60LEM FOR ATTITUDE MANEUVER.
013843,000057:
013844,000058: # CALLING SEQUENCE: V 89 E.
013845,000059:
013846,000060: # SUBROUTINES CALLED: CHKPOOH, R02BOTH, GOXDSPF, CSMCONIC, LEMCONIC,
013847,000061: # VECPOINT, BALLANGS, R60LEM.
013848,000062:
013849,000063: # NORMAL EXIT MODES: TC ENDEXT
013850,000064:
013851,000065: # ALARMS: 1. OPERATOR ERROR IF NOT IN P00.
013852,000066: # 2. PROGRAM ALARM IF IMU IS OFF.
013853,000067: # 3. PROGRAM ALARM IF IMU ORIENTATION IS UNKNOWN.
013854,000068:
013855,000069: # OUTPUT: NONE
013856,000070:
013857,000071: # ERASABLE INITIALIZATION REQUIRED: NONE
013858,000072:
013859,000073: # DEBRIS: OPTION1, +1, TDEC1, POINTVSM, SCAXIS, CPHI, CTHETA, CPSI,
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Page 339
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013861,000075: # 3AXISFLG.
013862,000076:
013863,000077: 06,3715 E4,1606 EBANK= RONE
013864,000078: 32,2217 BANK 32
013865,000079: 26,2000 SETLOC BAWLANGS
013866,000080: 26,2000 BANK
013867,000081:
013868,000082: 26,2022 COUNT* $$/R63
013869,000083: 26,2022 04616 V89CALL TC BANKCALL # IMU STATUS CHECK. RETURNS IF ORIENTATION
013870,000084: 26,2023 11254 CADR R02BOTH # KNOWN. ALARMS IF NOT.
013871,000085: 26,2024 36245 CAF THREE # ALLOW ASTRONAUT TO SELECT DESIRED
013872,000086: 26,2025 55051 TS OPTIONX # TRACKING ATTITUDE AXIS.
013873,000087: 26,2026 34753 CAF ONE
013874,000088: 26,2027 55052 TS OPTIONX +1
013875,000089: 26,2030 32117 CAF VB04N12 # V 04 N 12
013876,000090: 26,2031 04616 TC BANKCALL
013877,000091: 26,2032 20476 CADR GOFLASH
013878,000092: 26,2033 05472 TC ENDEXT # TERMINATE
013879,000093: 26,2034 02036 TC +2 # PROCEED
013880,000094: 26,2035 02030 TC -5 # DATA IN. OPTION1+1 = 1 FOR Z AXIS
013881,000095: 26,2036 06037 V89RECL TC INTPRET # = 2 FOR X AXIS
013882,000096: 26,2037 43234 RTB DAD
013883,000097: 26,2040 21573 LOADTIME # READ PRESENT TIME
013884,000098: 26,2041 14122 DP1MIN
013885,000099: 26,2042 02205 STORE TSTART82 # SAVE TIME FOR LEMCONIC CALL
013886,000100: 26,2043 34041 STCALL TDEC1 # STORE TIME FOR CSMCONIC CALL
013887,000101: 26,2044 27066 CSMCONIC # CSM STATE VECTOR UPDATE
013888,000102: 26,2045 77775 VLOAD # CSMCONIC LEFT R VECTOR IN RATT
013889,000103: 26,2046 00001 RATT
013890,000104: 26,2047 16207 STODL RONE # SAVE FOR LINE OF SIGHT (LOS) COMPUTATION
013891,000105: 26,2050 02205 TSTART82
013892,000106: 26,2051 34041 STCALL TDEC1 # STORE TIME FOR LEMCONIC CALL
013893,000107: 26,2052 27100 LEMCONIC # LEM STATE VECTOR UPDATE
013894,000108: 26,2053 52375 VLOAD VSU # CSM POSITION - LEM POSITION = LOS
013895,000109: 26,2054 02207 RONE # LOS VECTOR LEFT IN MPAC
013896,000110: 26,2055 00001 RATT
013897,000111: 26,2056 47121 MXV RTB # (REFSMMAT X LOS). TRANSFORMS LOS FROM
013898,000112: 26,2057 01734 REFSMMAT # REFERENCE COORD TO STAB MEMB COORD.
013899,000113: 26,2060 21726 NORMUNIT
013900,000114: 26,2061 03773 STORE POINTVSM # STORE LOS FOR VECPOINT CALL
013901,000115: 26,2062 77776 EXIT
013902,000116: 26,2063 41052 CS OPTIONX +1 # 1 FOR Z AXIS. 2 FOR X AXIS.
013903,000117: 26,2064 64753 AD ONE
013904,000118: 26,2065 00006 EXTEND
013905,000119: 26,2066 12113 BZF ALINEZ
013906,000120: 26,2067 06037 ALINEX TC INTPRET # X AXIS ALIGNMENT
013907,000121: 26,2070 77775 VLOAD
013908,000122: 26,2071 06520 UNITX # READ (.5, 0, 0)
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Page 340
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013910,000124: 26,2072 37765 V89CALL1 STCALL SCAXIS # STORE SELECTED ALIGNMENT AXIS
013911,000125: 26,2073 56040 VECPOINT # PUTS DESIRED GIM ANG (OG,IG,MG) IN TMPAC
013912,000126: 26,2074 00322 STORE CPHI # STORE GIMBAL ANGLES FOR BALLANGS CALL.
013913,000127: 26,2075 77776 EXIT
013914,000128: 26,2076 04616 TC BANKCALL
013915,000129: 26,2077 54266 CADR BALLANGS # PUTS DESIRED BALL ANGLES IN FDAIX,Y,Z
013916,000130: 26,2100 32120 CAF VB06N18 # V 06 N 18
013917,000131: 26,2101 04616 TC BANKCALL # NOUN 18 REFERS TO FDAIX,Y,Z
013918,000132: 26,2102 20476 CADR GOFLASH
013919,000133: 26,2103 05472 TC ENDEXT # TERMINATE
013920,000134: 26,2104 02106 TC +2 # PROCEED
013921,000135: 26,2105 02036 TC V89RECL # RECYCLE
013922,000136: 26,2106 05516 TC DOWNFLAG # RESET 3 AXIS FLAG
013923,000137: 26,2107 00124 ADRES 3AXISFLG # RESET BIT6 FLAG WORD 5
013924,000138: 26,2110 04616 TC BANKCALL # PERFORMS LEM MANEUVER TO ALIGN SELECTED
013925,000139: 26,2111 54123 CADR R60LEM # SPACECRAFT AXIS TO CSM.
013926,000140: 26,2112 15472 TCF ENDEXT # TERMINATE R63
013927,000141:
013928,000142: 26,2113 06037 ALINEZ TC INTPRET # Z AXIS ALIGNMENT
013929,000143: 26,2114 52175 VLOAD GOTO
013930,000144: 26,2115 06514 UNITZ # READ (0, 0, .5)
013931,000145: 26,2116 54072 V89CALL1
013932,000146:
013933,000147: 26,2117 01014 VB04N12 VN 412
013934,000148: 26,2120 01422 VB06N18 VN 0618
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Page 341
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013936,000150: 26,2121 00000 13560 DP1MIN 2DEC 6000 B-28
013937,000151:
End of include-file R63.agc. Parent file is MAIN.agc