Source Code
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These source-code files are part of a reconstructed copy of Comanche 45/2 (AKA Manche45 revision 2),
the final, flown mission release of the Apollo 10 Command Module (CM) Apollo Guidance
Computer (AGC) software. Comanche 45/2 was preceded by Comanche 44 and Comanche 45. The
reconstruction is believed to be exactly accurate, but in the absence of an actual Apollo-era
listing of Comanche 45/2, some explanation of the reconstruction process is needed
to insure confidence in that accuracy.
The starting point was the source code of Comanche 45 (itself previously accurately
reconstructed). Comanche 45 source code was then modified by incorporating changes
known from contemporary documentation to have been made between revisions 45 and 45/2.
The now-reconstructed Comanche 45/2 source code was
verified by assembling it and checking that the assembled code had
the expected known-correct memory-bank checksums.
Note that page numbers in the reconstructed code tend to match those in the Comanche 55, the
most-similar revision of Comanche for which we have access to an actual non-reconstructed hardcopy;
the source code would likely have different page numbers in a contemporary
Comanche 45 listing.
Annotations that were not present in the contemporary source code have been added to the reconstructed
code to justify each change relative to Comanche 44. Here's a guide to the Apollo documentation referenced
in those annotations:
Comments expected to have been present in 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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016687,000002: ## Copyright: Public domain.
016688,000003: ## Filename: R60,R62.agc
016689,000004: ## Purpose: A section of Manche45 revision 2.
016690,000005: ## It is part of the reconstructed source code for the
016691,000006: ## final, flown release of the flight software for the Command
016692,000007: ## Module's (CM) Apollo Guidance Computer (AGC) for Apollo 10.
016693,000008: ## The code has been recreated from a copy of Comanche 055. It
016694,000009: ## has been adapted such that the resulting bugger words
016695,000010: ## exactly match those specified for Manche 45/2 in NASA drawing
016696,000011: ## 2021153D, which gives relatively high confidence that the
016697,000012: ## reconstruction is correct.
016698,000013: ## Assembler: yaYUL
016699,000014: ## Contact: Ron Burkey <info@sandroid.org>.
016700,000015: ## Website: www.ibiblio.org/apollo/index.html
016701,000016: ## Mod history: 2020-12-24 MAS Created from Comanche 45.
016702,000017:
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Page 390
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016704,000019: 34,2002 BANK 34
016705,000020: 27,2000 SETLOC MANUVER
016706,000021: 27,2000 BANK
016707,000022:
016708,000023: 27,2000 1146 EBANK= TEMPR60
016709,000024:
016710,000025: 27,2000 COUNT 27/R60
016711,000026:
016712,000027: # R60CSM
016713,000028: # REV 13 CONFORMS TO GSOP CHAPTER FOUR REVISION LOGIC 09 JAN 18, 1968
016714,000029:
016715,000030: 27,2000 04711 R60CSM TC MAKECADR
016716,000031: 27,2001 55146 TS TEMPR60
016717,000032:
016718,000033: # INSERT PRIODSP CHECK WITH R22 (V06N49) WITH JENNINGS BRODEUR
016719,000034:
016720,000035: 27,2002 35012 REDOMANN CAF BIT6
016721,000036: 27,2003 70101 MASK FLAGWRD5 # IS 3-AXIS FLAG SET
016722,000037: 27,2004 10000 CCS A
016723,000038: 27,2005 12013 TCF TOBALL # YES
016724,000039: 27,2006 06006 TC INTPRET
016725,000040: 27,2007 77624 CALL
016726,000041: 27,2010 56126 VECPOINT # TO COMPUTE FINAL ANGLES
016727,000042: 27,2011 01156 STORE CPHI # STORE FINAL ANGLES - CPHI, CTHETA, CPSI
016728,000043: 27,2012 77776 EXIT
016729,000044:
016730,000045: 27,2013 32125 TOBALL CAF V06N18
016731,000046: 27,2014 04662 TC BANKCALL
016732,000047: 27,2015 21132 CADR GOPERF2R # DISPLAY PLEASE PERFORM AUTO MANEUVER
016733,000048: 27,2016 02114 TC R61TEST
016734,000049: 27,2017 02023 TC REDOMANC # PROCEED
016735,000050: 27,2020 12052 TCF ENDMANU1 # ENTER I.E. FINISHED WITH R60
016736,000051:
016737,000052: 27,2021 02056 TC CHKLINUS # TO CHECK FOR PRIORITY DISPLAYS
016738,000053: 27,2022 05217 TC ENDOFJOB
016739,000054:
016740,000055: 27,2023 35012 REDOMANC CAF BIT6
016741,000056: 27,2024 70101 MASK FLAGWRD5 # IS 3-AXIS FLAG SET
016742,000057: 27,2025 10000 CCS A
016743,000058: 27,2026 12034 TCF TOBALLC # YES
016744,000059: 27,2027 06006 TC INTPRET
016745,000060: 27,2030 77624 CALL
016746,000061: 27,2031 56126 VECPOINT # TO COMPUTE FINAL ANGLES
016747,000062: 27,2032 01156 STORE CPHI # STORE ANGLES
016748,000063: 27,2033 77776 EXIT
016749,000064:
016750,000065: 27,2034 34371 TOBALLC CAF PRIO30 # IS MODE AUTO AND CTL GNC
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Page 391
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016752,000067: 27,2035 00006 EXTEND
016753,000068: 27,2036 06031 RXOR CHAN31
016754,000069: 27,2037 77707 MASK 13,14,15
016755,000070: 27,2040 00006 EXTEND
016756,000071: 27,2041 12043 BZF +2 # AUTO, NON-FLASH N18
016757,000072: 27,2042 12013 TCF TOBALL # NOT AUTO
016758,000073:
016759,000074: 27,2043 32125 CAF V06N18 # SET UP NON-FLASHING V06 N18
016760,000075: 27,2044 04662 TC BANKCALL
016761,000076: 27,2045 20676 CADR GODSPR
016762,000077: 27,2046 02056 TC CHKLINUS
016763,000078:
016764,000079: 27,2047 04662 STARTMNV TC BANKCALL
016765,000080: 27,2050 17627 CADR GOMANUR
016766,000081: 27,2051 12013 ENDMANUV TCF TOBALL # FINISHED MANEUVER
016767,000082:
016768,000083: 27,2052 05560 ENDMANU1 TC DOWNFLAG # RESET 3-AXIS FLAG
016769,000084: 27,2053 00124 ADRES 3AXISFLG # BIT 6 FLAG 5
016770,000085: 27,2054 31146 CAE TEMPR60 # -
016771,000086: 27,2055 04704 TC BANKJUMP # -
016772,000087:
016773,000088: 27,2056 40100 CHKLINUS CS FLAGWRD4
016774,000089: 27,2057 75004 MASK BIT12 # IS PRIORITY DISPLAY FLAG SET -
016775,000090: 27,2060 10000 CCS A # -
016776,000091: 27,2061 00002 TC Q # NO - EXIT
016777,000092: 27,2062 30002 CA Q
016778,000093: 27,2063 54156 TS MPAC +2 # SAVE RETURN
016779,000094: 27,2064 46214 CS THREE # OBTAIN LOCATION FOR RESTART.
016780,000095: 27,2065 60133 AD BUF2 # HOLDS Q OF LAST DISPALY
016781,000096: 27,2066 55053 TS TBASE1
016782,000097:
016783,000098: 27,2067 05412 TC PHASCHNG
016784,000099: 27,2070 00071 OCT 71 # 1.7SPOT FOR RELINUS
016785,000100:
016786,000101: 27,2071 35011 CAF BIT7
016787,000102: 27,2072 05526 TC LINUS # GO SET BITS FOR PRIORITY DISPLAY -
016788,000103: 27,2073 00156 TC MPAC +2
016789,000104:
016790,000105: 27,2074 35013 RELINUS CAF BIT5 # IS TRACK FLAG ON
016791,000106: 27,2075 70075 MASK FLAGWRD1
016792,000107: 27,2076 00006 EXTEND
016793,000108: 27,2077 12111 BZF GOREDO20 # NO
016794,000109:
016795,000110: 27,2100 05546 TC UPFLAG
016796,000111: 27,2101 00077 ADRES PDSPFLAG # R60 PRIODSP FLAG
016797,000112:
016798,000113: 27,2102 05546 TC UPFLAG
016799,000114: 27,2103 00024 ADRES TARG1FLG # FOR R52
016800,000115:
016801,000116: 27,2104 35021 CAF ZERO # RESET TO ZERO, SINCE
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Page 392
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016803,000118: 27,2105 55303 TS OPTIND # OPTIND WAS SET TO -1 BY V379
016804,000119:
016805,000120: 27,2106 35066 CAF PRIO14 # RESTORE ORIGINAL PRIORITY
016806,000121: 27,2107 05210 TC PRIOCHNG
016807,000122:
016808,000123: 27,2110 01053 TC TBASE1
016809,000124:
016810,000125: 27,2111 05412 GOREDO20 TC PHASCHNG
016811,000126: 27,2112 00111 OCT 111 # 1.11 FOR PIKUP20
016812,000127:
016813,000128: 27,2113 05217 TC ENDOFJOB
016814,000129:
016815,000130: 27,2114 31011 R61TEST CA MODREG # ARE WE IN P00. IF YES THIS MUST BE
016816,000131: 27,2115 00006 EXTEND # VERB49 OR VERB89 SO DO ENDEXT.
016817,000132: 27,2116 12052 BZF ENDMANU1 # RESET 3-AXIS & RUTURN. USER DOES ENDEXT
016818,000133: 27,2117 30100 CA FLAGWRD4 # ARE WE IN R61 (P20)
016819,000134: 27,2120 75004 MASK BIT12
016820,000135: 27,2121 00006 EXTEND
016821,000136: 27,2122 14106 BZF GOTOPOOH # NO
016822,000137: 27,2123 04622 TC GOTOV56 # YES
016823,000138:
016824,000139: 27,2124 20100 BIT14+7 OCT 20100 # -
016825,000140: 27,2125 01422 V06N18 VN 0618
016826,000141:
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016828,000143: # PROGRAM DESCRIPTION - VECPOINT
016829,000144:
016830,000145: # THIS INTERPRETIVE SUBROUTINE MAY BE USED TO POINT A SPACECRAFT AXIS IN A DESIRED DIRECTION. THE AXIS
016831,000146: # TO BE POINTED MUST APPEAR AS A HALF UNIT DOUBLE PRECISION VECTOR IN SUCCESSIVE LOCATIONS OF ERASABLE MEMORY
016832,000147: # BEGINNING WITH THE LOCATION CALLED SCAXIS. THE COMPONENTS OF THIS VECTOR ARE GIVEN IN SPACECRAFT COORDINATES.
016833,000148: # THE DIRECTION IN WHICH THIS AXIS IS TO BE POINTED MUST APPEAR AS A HALF UNIT DOUBLE PRECISION VECTOR IN
016834,000149: # SUCCESSIVE LOCATIONS OF ERASABLE MEMORY BEGINNING WITH THE ADDRESS CALLED POINTVSM. THE COMPONENTS OF THIS
016835,000150: # VECTOR ARE GIVEN IN STABLE MEMBER COORDINATES. WITH THIS INFORMATION VECPOINT COMPUTES A SET OF THREE GIMBAL
016836,000151: # ANGLES (2S COMPLEMENT) CORRESPONDING TO THE CROSS-PRODUCT ROTATION BETWEEN SCAXIS AND POINTVSM AND STORES THEM
016837,000152: # IN T(MPAC) BEFORE RETURNING TO THE CALLER.
016838,000153:
016839,000154: # THIS ROTATION, HOWEVER, MAY BRING THE S/C INTO GIMBAL LOCK. WHEN POINTING A VECTOR IN THE Y-Z PLANE,
016840,000155: # THE TRANSPONDER AXIS, OR THE AOT FOR THE LEM, THE PROGRAM WILL CORRECT THIS PROBLEM BY ROTATING THE CROSS-
016841,000156: # PRODUCT ATTITUDE ABOUT POINTVSM BY A FIXED AMOUNT SUFFICIENT TO ROTATE THE DESIRED S/C ATTITUDE OUT OF GIMBAL
016842,000157: # LOCK. IF THE AXIS TO BE POINTED IS MORE THAN 40.6 DEGREES BUT LESS THAN 60.5 DEG FROM THE +X (OR -X) AXIS,
016843,000158: # THE ADDITIONAL ROTATION TO AVOID GIMAL LOCK IS 35 DEGREES. IF THE AXIS IS MORE THAN 60.5 DEGEES FROM +X (OR -X)
016844,000159: # THE ADDITIONAL ROTATION IS 35 DEGREES. THE GIMBAL ANGLES CORRESPONDING TO THIS ATTITUDE ARE THEN COMPUTED AND
016845,000160: # STORED AS 2S COMPLIMENT ANGLES IN T(MPAC) BEFORE RETURNING TO THE CALLER.
016846,000161:
016847,000162: # WHEN POINTING THE X-AXIS, OR THE THRUST VECTOR, OR ANY VECTOR WITHIN 40.6 DEG OF THE X-AXIS, VECPOINT
016848,000163: # CANNOT CORRECT FOR A CROSS-PRODUCT ROTATION INTO GIMBAL LOCK. IN THIS CASE A PLATFORM REALIGNMENT WOULD BE
016849,000164: # REQUIRED TO POINT THE VECTOR IN THE DESIRED DIRECTION. AT PRESENT NO INDICATION IS GIVEN FOR THIS SITUATION
016850,000165: # EXCEPT THAT THE FINAL MIDDLE GIMBAL ANGLE IN MPAC +2 IS GREATER THAN 59 DEGREES.
016851,000166:
016852,000167: # CALLING SEQUENCE -
016853,000168:
016854,000169: # 1) LOAD SCAXIS, POINTVSM
016855,000170: # 2) CALL
016856,000171: # VECPOINT
016857,000172:
016858,000173: # RETURNS WITH
016859,000174:
016860,000175: # 1) DESIRED OUTER GIMBAL ANGLE IN MPAC
016861,000176: # 2) DESIRED INNER GIMBAL ANGLE IN MPAC +1
016862,000177: # 3) DESIRED MIDDLE GIMBAL ANGLE IN MPAC +2
016863,000178:
016864,000179: # ERASABLES USED -
016865,000180:
016866,000181: # 1) SCAXIS 6
016867,000182: # 2) POINTVSM 6
016868,000183: # 3) MIS 18
016869,000184: # 4) DEL 18
016870,000185: # 5) COF 6
016871,000186: # 6) VECQTEMP 1
016872,000187: # 7) ALL OF VAC AREA 43
016873,000188:
016874,000189: # TOTAL 99
016875,000190:
016876,000191: 27,2000 SETLOC VECPT
016877,000192: 27,2000 BANK
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016879,000194: 27,2126 E6,1661 EBANK= BCDU
016880,000195:
016881,000196: 27,2126 COUNT 27/VECPT
016882,000197:
016883,000198: 27,2126 40020 VECPOINT STQ BOV # SAVE RETURN ADDRESS
016884,000199: 27,2127 03310 VECQTEMP
016885,000200: 27,2130 56131 VECLEAR # AND CLEAR OVFIND
016886,000201: 27,2131 47164 VECLEAR AXC,2 RTB
016887,000202: 27,2132 03320 MIS # READ THE PRESENT CDU ANGLES AND
016888,000203: 27,2133 44376 READCDUK # STORE THEM IN PD25, 26, 27
016889,000204: 27,2134 34032 STCALL 25D
016890,000205: 27,2135 44405 CDUTODCM # S/C AXES TO STABLE MEMBER AXES (MIS)
016891,000206: 27,2136 61375 VLOAD VXM
016892,000207: 27,2137 03357 POINTVSM # RESOLVE THE POINTING DIRECTION VF INTO
016893,000208: 27,2140 03321 MIS # INITIAL S/C AXES (VF = POINTVSM)
016894,000209: 27,2141 77656 UNIT
016895,000210: 27,2142 00035 STORE 28D
016896,000211: # PD 28 29 30 31 32 33
016897,000212: 27,2143 53435 VXV UNIT # TAKE THE CROSS PRODUCT VF X VI
016898,000213: 27,2144 03351 SCAXIS # WHERE VI = SCAXIS
016899,000214: 27,2145 57400 BOV VCOMP
016900,000215: 27,2146 56256 PICKAXIS
016901,000216: 27,2147 17343 STODL COF # CHECK MAGNITUDE
016902,000217: 27,2150 00045 36D # OF CROSS PRODUCT
016903,000218: 27,2151 50025 DSU BMN # VECTOR, IF LESS
016904,000219: 27,2152 16327 DPB-14 # THAN B-14 ASSUME
016905,000220: 27,2153 56256 PICKAXIS # UNIT OPERATION
016906,000221: 27,2154 50375 VLOAD DOT # INVALID.
016907,000222: 27,2155 03351 SCAXIS
016908,000223: 27,2156 00035 28D
016909,000224: 27,2157 65552 SL1 ARCCOS
016910,000225: 27,2160 77624 COMPMATX CALL # NOW COMPUTE THE TRANSFORMATION FROM
016911,000226: 27,2161 44530 DELCOMP # FINAL S/C AXES TO INITIAL S/C AXES MFI
016912,000227: 27,2162 75160 AXC,1 AXC,2
016913,000228: 27,2163 03320 MIS # COMPUTE THE TRANSFORMATION FROM FINAL
016914,000229: 27,2164 03425 DEL # S/C AXES TO STABLE MEMBER AXES
016915,000230: 27,2165 77624 CALL # MFS = MIS MFI
016916,000231: 27,2166 44304 MXM3 # (IN PD LIST)
016917,000232:
016918,000233: 27,2167 51545 DLOAD ABS
016919,000234: 27,2170 00007 6 # MFS6 = SIN(CPSI) $2
016920,000235: 27,2171 50025 DSU BMN
016921,000236: 27,2172 16314 SINGIMLC # = SIN(59 DEGS) $2
016922,000237: 27,2173 56246 FINDGIMB # /CPSI/ LESS THAN 59 DEGS
016923,000238: # I.E. DESIRED ATTITUDE NOT IN GIMBAL LOCK
016924,000239:
016925,000240: 27,2174 51545 DLOAD ABS # CHECK TO SEE IF WE ARE POINTING
016926,000241: 27,2175 03351 SCAXIS # THE THRUST AXIS
016927,000242: 27,2176 51025 DSU BPL
016928,000243: 27,2177 16316 SINVEC1 # SIN 49.4 DEGS $2
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016930,000245: 27,2200 56246 FINDGIMB # IF SO, WE ARE TRYING TO POINT IT INTO
016931,000246: 27,2201 77775 VLOAD # GIMBAL LOCK, ABORT COULD GO HERE
016932,000247: 27,2202 77626 STADR
016933,000248: 27,2203 50442 STOVL MIS +12D
016934,000249: 27,2204 77626 STADR # STORE MFS (IN PD LIST) IN MIS
016935,000250: 27,2205 50450 STOVL MIS +6
016936,000251: 27,2206 77626 STADR
016937,000252: 27,2207 50456 STOVL MIS
016938,000253: 27,2210 03327 MIS +6 # INNER GIMBAL AXIS IN FINAL S/C AXES
016939,000254: 27,2211 57444 BPL VCOMP # LOCATE THE IG AXIS DIRECTION CLOSEST TO
016940,000255: 27,2212 56213 IGSAMEX # FINAL X S/C AXIS
016941,000256:
016942,000257: 27,2213 50035 IGSAMEX VXV BMN # FIND THE SHORTEST WAY OF ROTATING THE
016943,000258: 27,2214 03351 SCAXIS # S/C OUT OF GIMBAL LOCK BY A ROTATION
016944,000259: 27,2215 56222 U=SCAXIS # ABOUT +- SCAXIS, I.E. IF (IG (SGN MFS3)
016945,000260: # X SCAXIS . XF) LESS THAN 0, U = SCAXIS
016946,000261: # OTHERWISE U = -SCAXIS
016947,000262:
016948,000263: 27,2216 57575 VLOAD VCOMP
016949,000264: 27,2217 03351 SCAXIS
016950,000265: 27,2220 37343 STCALL COF # ROTATE ABOUT -SCAXIS
016951,000266: 27,2221 56225 CHEKAXIS
016952,000267: 27,2222 77775 U=SCAXIS VLOAD
016953,000268: 27,2223 03351 SCAXIS
016954,000269: 27,2224 03343 STORE COF # ROTATE ABOUT + SCAXIS
016955,000270: 27,2225 51545 CHEKAXIS DLOAD ABS
016956,000271: 27,2226 03351 SCAXIS # SEE IF WE ARE POINTING THE AOT
016957,000272: 27,2227 51025 DSU BPL
016958,000273: 27,2230 16320 SINVEC2 # SIN 29.5 DEGS $2
016959,000274: 27,2231 56235 PICKANG1 # IF SO, ROTATE 50 DEGS ABOUT +- SCAXIS
016960,000275: 27,2232 52145 DLOAD GOTO # IF NOT, MUST BE POINTING THE TRANSPONDER
016961,000276: 27,2233 16324 VECANG2 # OR SOME VECTOR IN THE Y, OR Z PLANE
016962,000277: 27,2234 56237 COMPMFSN # IN THIS CASE ROTATE 35 DEGS TO GET OUT
016963,000278: # OF GIMBAL LOCK (VECANG2 $360)
016964,000279: 27,2235 77745 PICKANG1 DLOAD
016965,000280: 27,2236 16322 VECANG1 # = 50 DEGS $ 360
016966,000281: 27,2237 77624 COMPMFSN CALL
016967,000282: 27,2240 44530 DELCOMP # COMPUTE THE ROTATION ABOUT SCAXIS TO
016968,000283: 27,2241 75160 AXC,1 AXC,2 # BRING MFS OUT OF GIMBAL LOCK
016969,000284: 27,2242 03320 MIS
016970,000285: 27,2243 03425 DEL
016971,000286: 27,2244 77624 CALL # COMPUTE THE NEW TRANSFORMATION FROM
016972,000287: 27,2245 44304 MXM3 # DESIRED S/C AXES TO STABLE MEMBER AXES
016973,000288: # WHICH WILL ALIGN VI WITH VF AND AVOID
016974,000289: # GIMBAL LOCK
016975,000290: 27,2246 45160 FINDGIMB AXC,1 CALL
016976,000291: 27,2247 00000 0 # EXTRACT THE COMMANDED CDU ANGLES FROM
016977,000292: 27,2250 44655 DCMTOCDU # THIS MATRIX
016978,000293: 27,2251 40234 RTB SETPD
016979,000294: 27,2252 45552 V1STO2S # CONVERT TO 2:S COMPLEMENT
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016981,000296: 27,2253 00001 0
016982,000297: 27,2254 77650 GOTO
016983,000298: 27,2255 03310 VECQTEMP # RETURN TO CALLER
016984,000299:
016985,000300: 27,2256 50375 PICKAXIS VLOAD DOT # IF VF X VI = 0, FIND VF . VI
016986,000301: 27,2257 00035 28D
016987,000302: 27,2260 03351 SCAXIS
016988,000303: 27,2261 72240 BMN TLOAD
016989,000304: 27,2262 56266 ROT180
016990,000305: 27,2263 00032 25D
016991,000306: 27,2264 77650 GOTO # IF VF = VI, CDU DESIRED = PRESENT CDU
016992,000307: 27,2265 03310 VECQTEMP # PRESENT CDU ANGLES
016993,000308:
016994,000309: 27,2266 47375 ROT180 VLOAD VXV # IF VF, VI ANTIPARALLEL, 180 DEG ROTATION
016995,000310: 27,2267 03327 MIS +6 # IS REQUIRED. Y STABLE MEMBER AXIS IN
016996,000311: 27,2270 15333 HIUNITX # INITIAL S/C AXIS.
016997,000312: 27,2271 47256 UNIT VXV # FIND Y(SM) X X(I)
016998,000313: 27,2272 03351 SCAXIS # FIND UNIT(VI X UNIT(Y(SM) X X(I)))
016999,000314: 27,2273 40056 UNIT BOV # I.E. PICK A VECTOR IN THE PLANE OF X(I),
017000,000315: 27,2274 56310 PICKX # Y(SM) PERPENDICULAR TO VI
017001,000316: 27,2275 17343 STODL COF
017002,000317: 27,2276 00045 36D # CHECK MAGNITUDE
017003,000318: 27,2277 50025 DSU BMN # OF THIS VECTOR.
017004,000319: 27,2300 16327 DPB-14 # IF LESS THAN B-14,
017005,000320: 27,2301 56310 PICKX # PICK X-AXIS.
017006,000321: 27,2302 77775 VLOAD
017007,000322: 27,2303 03343 COF
017008,000323: 27,2304 17343 XROT STODL COF
017009,000324: 27,2305 15333 HIDPHALF
017010,000325: 27,2306 77650 GOTO
017011,000326: 27,2307 56160 COMPMATX
017012,000327: 27,2310 52175 PICKX VLOAD GOTO # PICK THE XAXIS IN THIS CASE
017013,000328: 27,2311 15333 HIUNITX
017014,000329: 27,2312 56304 XROT
017015,000330: 35,2000 BANK 35
017016,000331: 27,2000 SETLOC MANUVER1
017017,000332: 27,2000 BANK
017018,000333:
017019,000334: 27,2313 15555 35172 SINGIMLC 2DEC .4285836003 # = SIN(59) $2
017020,000335:
017021,000336: 27,2315 14113 36326 SINVEC1 2DEC .3796356537 # = SIN(49.4) $2
017022,000337:
017023,000338: 27,2317 07701 35703 SINVEC2 2DEC .2462117800 # = SIN(29.5) $2
017024,000339:
017025,000340: 27,2321 04343 21616 VECANG1 2DEC .1388888889 # = 50 DEGREES $360
017026,000341:
017027,000342: 27,2323 03070 34344 VECANG2 2DEC .09722222222 # = 35 DEGREES $360
017028,000343:
017029,000344:
017030,000345: 27,2325 00000 1BITDP OCT 0 # KEEP THIS BEFORE DPB(-14) *********
017031,000346: 27,2326 00001 DPB-14 OCT 00001
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Page 397
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017033,000348: 27,2327 00000 OCT 00000
017034,000349: 34,2002 BANK 34
017035,000350: 27,2000 SETLOC MANUVER
017036,000351: 27,2000 BANK
017037,000352:
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Page 398
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017039,000354: # ROUTINE FOR INITIATING AUTOMATIC MANEUVER VIA KEYBOARD (V49)
017040,000355:
017041,000356: 27,2330 1155 EBANK= CPHI
017042,000357:
017043,000358: 27,2330 COUNT 27/R62
017044,000359:
017045,000360: 27,2330 35052 R62DISP CAF V06N22 # DISPLAY COMMAND ICDUS CPHI, CTHETA, CPHI
017046,000361: 27,2331 04662 TC BANKCALL
017047,000362: 27,2332 20720 CADR GOFLASH
017048,000363: 27,2333 15534 TCF ENDEXT
017049,000364: 27,2334 12336 TCF GOMOVE # PROCEED
017050,000365: 27,2335 12330 TCF R62DISP # ENTER
017051,000366:
017052,000367: # ASTRONAUT MAY LOAD NEW ICDUS AT THIS
017053,000368: # POINT
017054,000369: 27,2336 05546 GOMOVE TC UPFLAG # SET 3-AXIS FLAG
017055,000370: 27,2337 00124 ADRES 3AXISFLG # BIT 6 FLAG 5
017056,000371:
017057,000372: 27,2340 04662 TC BANKCALL
017058,000373: 27,2341 56000 CADR R60CSM
017059,000374: 27,2342 15534 TCF ENDEXT
017060,000375:
End of include-file R60,R62.agc. Parent file is MAIN.agc