Source Code
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These source-code files are part of a reconstructed copy of Comanche 44, the
initial release (though not the final mission release) of the Apollo 10
Command Module (CM) Apollo Guidance Computer (AGC) software. Subsequent releases
were Comanche 45 and Comanche 45/2 (the flown release on Apollo 10). The reconstruction
is believed to be exactly accurate, but in the absence of an actual Apollo-era
listing of Comanche 44, some explanation of the reconstruction process is needed
to insure confidence in that accuracy.
The starting point was the source code of Comanche 51
(separately previously reconstructed from an Apollo-era listing of Comanche 55,
flown on Apollo 11). Comanche 51 source code was then modified
by undoing changes known to have been made between revisions 44 and 51. The now-reconstructed
Comanche 44 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 match those on the Comanche 55 printout,
although the source code would likely have different page numbers in a contemporary
Comanche 44 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 51. Here's a guide to the Apollo documentation referenced
in those annotations:
In most cases, only the titles (rather than the full texts) of PCRs are known. In addition to the
explanatory annotations, there is also
a step-by-step commentary about the reconstruction process.
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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016836,000002: ## Copyright: Public domain.
016837,000003: ## Filename: R60,R62.agc
016838,000004: ## Purpose: A section of Comanche revision 044.
016839,000005: ## It is part of the reconstructed source code for the
016840,000006: ## original release of the flight software for the Command
016841,000007: ## Module's (CM) Apollo Guidance Computer (AGC) for Apollo 10.
016842,000008: ## The code has been recreated from a copy of Comanche 055. It
016843,000009: ## has been adapted such that the resulting bugger words
016844,000010: ## exactly match those specified for Comanche 44 in NASA drawing
016845,000011: ## 2021153D, which gives relatively high confidence that the
016846,000012: ## reconstruction is correct.
016847,000013: ## Assembler: yaYUL
016848,000014: ## Contact: Ron Burkey <info@sandroid.org>.
016849,000015: ## Website: www.ibiblio.org/apollo/index.html
016850,000016: ## Mod history: 2020-12-03 MAS Created from Comanche 51.
016851,000017:
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016853,000019: 34,2002 BANK 34
016854,000020: 27,2000 SETLOC MANUVER
016855,000021: 27,2000 BANK
016856,000022:
016857,000023: 27,2000 1146 EBANK= TEMPR60
016858,000024:
016859,000025: 27,2000 COUNT 27/R60
016860,000026:
016861,000027: # R60CSM
016862,000028: # REV 13 CONFORMS TO GSOP CHAPTER FOUR REVISION LOGIC 09 JAN 18, 1968
016863,000029:
016864,000030: 27,2000 04711 R60CSM TC MAKECADR
016865,000031: 27,2001 55146 TS TEMPR60
016866,000032:
016867,000033: # INSERT PRIODSP CHECK WITH R22 (V06N49) WITH JENNINGS BRODEUR
016868,000034:
016869,000035: 27,2002 35012 REDOMANN CAF BIT6
016870,000036: 27,2003 70101 MASK FLAGWRD5 # IS 3-AXIS FLAG SET
016871,000037: 27,2004 10000 CCS A
016872,000038: 27,2005 12013 TCF TOBALL # YES
016873,000039: 27,2006 06006 TC INTPRET
016874,000040: 27,2007 77624 CALL
016875,000041: 27,2010 56126 VECPOINT # TO COMPUTE FINAL ANGLES
016876,000042: 27,2011 01156 STORE CPHI # STORE FINAL ANGLES - CPHI, CTHETA, CPSI
016877,000043: 27,2012 77776 EXIT
016878,000044:
016879,000045: 27,2013 32125 TOBALL CAF V06N18
016880,000046: 27,2014 04662 TC BANKCALL
016881,000047: 27,2015 21132 CADR GOPERF2R # DISPLAY PLEASE PERFORM AUTO MANEUVER
016882,000048: 27,2016 02114 TC R61TEST
016883,000049: 27,2017 02023 TC REDOMANC # PROCEED
016884,000050: 27,2020 12052 TCF ENDMANU1 # ENTER I.E. FINISHED WITH R60
016885,000051:
016886,000052: 27,2021 02056 TC CHKLINUS # TO CHECK FOR PRIORITY DISPLAYS
016887,000053: 27,2022 05217 TC ENDOFJOB
016888,000054:
016889,000055: 27,2023 35012 REDOMANC CAF BIT6
016890,000056: 27,2024 70101 MASK FLAGWRD5 # IS 3-AXIS FLAG SET
016891,000057: 27,2025 10000 CCS A
016892,000058: 27,2026 12034 TCF TOBALLC # YES
016893,000059: 27,2027 06006 TC INTPRET
016894,000060: 27,2030 77624 CALL
016895,000061: 27,2031 56126 VECPOINT # TO COMPUTE FINAL ANGLES
016896,000062: 27,2032 01156 STORE CPHI # STORE ANGLES
016897,000063: 27,2033 77776 EXIT
016898,000064:
016899,000065: 27,2034 34371 TOBALLC CAF PRIO30 # IS MODE AUTO AND CTL GNC
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016901,000067: 27,2035 00006 EXTEND
016902,000068: 27,2036 06031 RXOR CHAN31
016903,000069: 27,2037 77707 MASK 13,14,15
016904,000070: 27,2040 00006 EXTEND
016905,000071: 27,2041 12043 BZF +2 # AUTO, NON-FLASH N18
016906,000072: 27,2042 12013 TCF TOBALL # NOT AUTO
016907,000073:
016908,000074: 27,2043 32125 CAF V06N18 # SET UP NON-FLASHING V06 N18
016909,000075: 27,2044 04662 TC BANKCALL
016910,000076: 27,2045 20676 CADR GODSPR
016911,000077: 27,2046 02056 TC CHKLINUS
016912,000078:
016913,000079: 27,2047 04662 STARTMNV TC BANKCALL
016914,000080: 27,2050 17627 CADR GOMANUR
016915,000081: 27,2051 12013 ENDMANUV TCF TOBALL # FINISHED MANEUVER
016916,000082:
016917,000083: 27,2052 05560 ENDMANU1 TC DOWNFLAG # RESET 3-AXIS FLAG
016918,000084: 27,2053 00124 ADRES 3AXISFLG # BIT 6 FLAG 5
016919,000085: 27,2054 31146 CAE TEMPR60 # -
016920,000086: 27,2055 04704 TC BANKJUMP # -
016921,000087:
016922,000088: 27,2056 40100 CHKLINUS CS FLAGWRD4
016923,000089: 27,2057 75004 MASK BIT12 # IS PRIORITY DISPLAY FLAG SET -
016924,000090: 27,2060 10000 CCS A # -
016925,000091: 27,2061 00002 TC Q # NO - EXIT
016926,000092: 27,2062 30002 CA Q
016927,000093: 27,2063 54156 TS MPAC +2 # SAVE RETURN
016928,000094: 27,2064 46214 CS THREE # OBTAIN LOCATION FOR RESTART.
016929,000095: 27,2065 60133 AD BUF2 # HOLDS Q OF LAST DISPALY
016930,000096: 27,2066 55053 TS TBASE1
016931,000097:
016932,000098: 27,2067 05412 TC PHASCHNG
016933,000099: 27,2070 00071 OCT 71 # 1.7SPOT FOR RELINUS
016934,000100:
016935,000101: 27,2071 35011 CAF BIT7
016936,000102: 27,2072 05526 TC LINUS # GO SET BITS FOR PRIORITY DISPLAY -
016937,000103: 27,2073 00156 TC MPAC +2
016938,000104:
016939,000105: 27,2074 35013 RELINUS CAF BIT5 # IS TRACK FLAG ON
016940,000106: 27,2075 70075 MASK FLAGWRD1
016941,000107: 27,2076 00006 EXTEND
016942,000108: 27,2077 12111 BZF GOREDO20 # NO
016943,000109:
016944,000110: 27,2100 05546 TC UPFLAG
016945,000111: 27,2101 00077 ADRES PDSPFLAG # R60 PRIODSP FLAG
016946,000112:
016947,000113: 27,2102 05546 TC UPFLAG
016948,000114: 27,2103 00024 ADRES TARG1FLG # FOR R52
016949,000115:
016950,000116: 27,2104 35021 CAF ZERO # RESET TO ZERO, SINCE
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016952,000118: 27,2105 55303 TS OPTIND # OPTIND WAS SET TO -1 BY V379
016953,000119:
016954,000120: 27,2106 35066 CAF PRIO14 # RESTORE ORIGINAL PRIORITY
016955,000121: 27,2107 05210 TC PRIOCHNG
016956,000122:
016957,000123: 27,2110 01053 TC TBASE1
016958,000124:
016959,000125: 27,2111 05412 GOREDO20 TC PHASCHNG
016960,000126: 27,2112 00111 OCT 111 # 1.11 FOR PIKUP20
016961,000127:
016962,000128: 27,2113 05217 TC ENDOFJOB
016963,000129:
016964,000130: 27,2114 31011 R61TEST CA MODREG # ARE WE IN P00. IF YES THIS MUST BE
016965,000131: 27,2115 00006 EXTEND # VERB49 OR VERB89 SO DO ENDEXT.
016966,000132: 27,2116 12052 BZF ENDMANU1 # RESET 3-AXIS & RUTURN. USER DOES ENDEXT
016967,000133: 27,2117 30100 CA FLAGWRD4 # ARE WE IN R61 (P20)
016968,000134: 27,2120 75004 MASK BIT12
016969,000135: 27,2121 00006 EXTEND
016970,000136: 27,2122 14106 BZF GOTOPOOH # NO
016971,000137: 27,2123 04622 TC GOTOV56 # YES
016972,000138:
016973,000139: 27,2124 20100 BIT14+7 OCT 20100 # -
016974,000140: 27,2125 01422 V06N18 VN 0618
016975,000141:
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016977,000143: # PROGRAM DESCRIPTION - VECPOINT
016978,000144:
016979,000145: # THIS INTERPRETIVE SUBROUTINE MAY BE USED TO POINT A SPACECRAFT AXIS IN A DESIRED DIRECTION. THE AXIS
016980,000146: # TO BE POINTED MUST APPEAR AS A HALF UNIT DOUBLE PRECISION VECTOR IN SUCCESSIVE LOCATIONS OF ERASABLE MEMORY
016981,000147: # BEGINNING WITH THE LOCATION CALLED SCAXIS. THE COMPONENTS OF THIS VECTOR ARE GIVEN IN SPACECRAFT COORDINATES.
016982,000148: # THE DIRECTION IN WHICH THIS AXIS IS TO BE POINTED MUST APPEAR AS A HALF UNIT DOUBLE PRECISION VECTOR IN
016983,000149: # SUCCESSIVE LOCATIONS OF ERASABLE MEMORY BEGINNING WITH THE ADDRESS CALLED POINTVSM. THE COMPONENTS OF THIS
016984,000150: # VECTOR ARE GIVEN IN STABLE MEMBER COORDINATES. WITH THIS INFORMATION VECPOINT COMPUTES A SET OF THREE GIMBAL
016985,000151: # ANGLES (2S COMPLEMENT) CORRESPONDING TO THE CROSS-PRODUCT ROTATION BETWEEN SCAXIS AND POINTVSM AND STORES THEM
016986,000152: # IN T(MPAC) BEFORE RETURNING TO THE CALLER.
016987,000153:
016988,000154: # THIS ROTATION, HOWEVER, MAY BRING THE S/C INTO GIMBAL LOCK. WHEN POINTING A VECTOR IN THE Y-Z PLANE,
016989,000155: # THE TRANSPONDER AXIS, OR THE AOT FOR THE LEM, THE PROGRAM WILL CORRECT THIS PROBLEM BY ROTATING THE CROSS-
016990,000156: # PRODUCT ATTITUDE ABOUT POINTVSM BY A FIXED AMOUNT SUFFICIENT TO ROTATE THE DESIRED S/C ATTITUDE OUT OF GIMBAL
016991,000157: # 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,
016992,000158: # THE ADDITIONAL ROTATION TO AVOID GIMAL LOCK IS 35 DEGREES. IF THE AXIS IS MORE THAN 60.5 DEGEES FROM +X (OR -X)
016993,000159: # THE ADDITIONAL ROTATION IS 35 DEGREES. THE GIMBAL ANGLES CORRESPONDING TO THIS ATTITUDE ARE THEN COMPUTED AND
016994,000160: # STORED AS 2S COMPLIMENT ANGLES IN T(MPAC) BEFORE RETURNING TO THE CALLER.
016995,000161:
016996,000162: # WHEN POINTING THE X-AXIS, OR THE THRUST VECTOR, OR ANY VECTOR WITHIN 40.6 DEG OF THE X-AXIS, VECPOINT
016997,000163: # CANNOT CORRECT FOR A CROSS-PRODUCT ROTATION INTO GIMBAL LOCK. IN THIS CASE A PLATFORM REALIGNMENT WOULD BE
016998,000164: # REQUIRED TO POINT THE VECTOR IN THE DESIRED DIRECTION. AT PRESENT NO INDICATION IS GIVEN FOR THIS SITUATION
016999,000165: # EXCEPT THAT THE FINAL MIDDLE GIMBAL ANGLE IN MPAC +2 IS GREATER THAN 59 DEGREES.
017000,000166:
017001,000167: # CALLING SEQUENCE -
017002,000168:
017003,000169: # 1) LOAD SCAXIS, POINTVSM
017004,000170: # 2) CALL
017005,000171: # VECPOINT
017006,000172:
017007,000173: # RETURNS WITH
017008,000174:
017009,000175: # 1) DESIRED OUTER GIMBAL ANGLE IN MPAC
017010,000176: # 2) DESIRED INNER GIMBAL ANGLE IN MPAC +1
017011,000177: # 3) DESIRED MIDDLE GIMBAL ANGLE IN MPAC +2
017012,000178:
017013,000179: # ERASABLES USED -
017014,000180:
017015,000181: # 1) SCAXIS 6
017016,000182: # 2) POINTVSM 6
017017,000183: # 3) MIS 18
017018,000184: # 4) DEL 18
017019,000185: # 5) COF 6
017020,000186: # 6) VECQTEMP 1
017021,000187: # 7) ALL OF VAC AREA 43
017022,000188:
017023,000189: # TOTAL 99
017024,000190:
017025,000191: 27,2000 SETLOC VECPT
017026,000192: 27,2000 BANK
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017028,000194: 27,2126 E6,1661 EBANK= BCDU
017029,000195:
017030,000196: 27,2126 COUNT 27/VECPT
017031,000197:
017032,000198: 27,2126 40020 VECPOINT STQ BOV # SAVE RETURN ADDRESS
017033,000199: 27,2127 03310 VECQTEMP
017034,000200: 27,2130 56131 VECLEAR # AND CLEAR OVFIND
017035,000201: 27,2131 47164 VECLEAR AXC,2 RTB
017036,000202: 27,2132 03320 MIS # READ THE PRESENT CDU ANGLES AND
017037,000203: 27,2133 44376 READCDUK # STORE THEM IN PD25, 26, 27
017038,000204: 27,2134 34032 STCALL 25D
017039,000205: 27,2135 44405 CDUTODCM # S/C AXES TO STABLE MEMBER AXES (MIS)
017040,000206: 27,2136 61375 VLOAD VXM
017041,000207: 27,2137 03357 POINTVSM # RESOLVE THE POINTING DIRECTION VF INTO
017042,000208: 27,2140 03321 MIS # INITIAL S/C AXES (VF = POINTVSM)
017043,000209: 27,2141 77656 UNIT
017044,000210: 27,2142 00035 STORE 28D
017045,000211: # PD 28 29 30 31 32 33
017046,000212: 27,2143 53435 VXV UNIT # TAKE THE CROSS PRODUCT VF X VI
017047,000213: 27,2144 03351 SCAXIS # WHERE VI = SCAXIS
017048,000214: 27,2145 57400 BOV VCOMP
017049,000215: 27,2146 56256 PICKAXIS
017050,000216: 27,2147 17343 STODL COF # CHECK MAGNITUDE
017051,000217: 27,2150 00045 36D # OF CROSS PRODUCT
017052,000218: 27,2151 50025 DSU BMN # VECTOR, IF LESS
017053,000219: 27,2152 16327 DPB-14 # THAN B-14 ASSUME
017054,000220: 27,2153 56256 PICKAXIS # UNIT OPERATION
017055,000221: 27,2154 50375 VLOAD DOT # INVALID.
017056,000222: 27,2155 03351 SCAXIS
017057,000223: 27,2156 00035 28D
017058,000224: 27,2157 65552 SL1 ARCCOS
017059,000225: 27,2160 77624 COMPMATX CALL # NOW COMPUTE THE TRANSFORMATION FROM
017060,000226: 27,2161 44530 DELCOMP # FINAL S/C AXES TO INITIAL S/C AXES MFI
017061,000227: 27,2162 75160 AXC,1 AXC,2
017062,000228: 27,2163 03320 MIS # COMPUTE THE TRANSFORMATION FROM FINAL
017063,000229: 27,2164 03425 DEL # S/C AXES TO STABLE MEMBER AXES
017064,000230: 27,2165 77624 CALL # MFS = MIS MFI
017065,000231: 27,2166 44304 MXM3 # (IN PD LIST)
017066,000232:
017067,000233: 27,2167 51545 DLOAD ABS
017068,000234: 27,2170 00007 6 # MFS6 = SIN(CPSI) $2
017069,000235: 27,2171 50025 DSU BMN
017070,000236: 27,2172 16314 SINGIMLC # = SIN(59 DEGS) $2
017071,000237: 27,2173 56246 FINDGIMB # /CPSI/ LESS THAN 59 DEGS
017072,000238: # I.E. DESIRED ATTITUDE NOT IN GIMBAL LOCK
017073,000239:
017074,000240: 27,2174 51545 DLOAD ABS # CHECK TO SEE IF WE ARE POINTING
017075,000241: 27,2175 03351 SCAXIS # THE THRUST AXIS
017076,000242: 27,2176 51025 DSU BPL
017077,000243: 27,2177 16316 SINVEC1 # SIN 49.4 DEGS $2
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017079,000245: 27,2200 56246 FINDGIMB # IF SO, WE ARE TRYING TO POINT IT INTO
017080,000246: 27,2201 77775 VLOAD # GIMBAL LOCK, ABORT COULD GO HERE
017081,000247: 27,2202 77626 STADR
017082,000248: 27,2203 50442 STOVL MIS +12D
017083,000249: 27,2204 77626 STADR # STORE MFS (IN PD LIST) IN MIS
017084,000250: 27,2205 50450 STOVL MIS +6
017085,000251: 27,2206 77626 STADR
017086,000252: 27,2207 50456 STOVL MIS
017087,000253: 27,2210 03327 MIS +6 # INNER GIMBAL AXIS IN FINAL S/C AXES
017088,000254: 27,2211 57444 BPL VCOMP # LOCATE THE IG AXIS DIRECTION CLOSEST TO
017089,000255: 27,2212 56213 IGSAMEX # FINAL X S/C AXIS
017090,000256:
017091,000257: 27,2213 50035 IGSAMEX VXV BMN # FIND THE SHORTEST WAY OF ROTATING THE
017092,000258: 27,2214 03351 SCAXIS # S/C OUT OF GIMBAL LOCK BY A ROTATION
017093,000259: 27,2215 56222 U=SCAXIS # ABOUT +- SCAXIS, I.E. IF (IG (SGN MFS3)
017094,000260: # X SCAXIS . XF) LESS THAN 0, U = SCAXIS
017095,000261: # OTHERWISE U = -SCAXIS
017096,000262:
017097,000263: 27,2216 57575 VLOAD VCOMP
017098,000264: 27,2217 03351 SCAXIS
017099,000265: 27,2220 37343 STCALL COF # ROTATE ABOUT -SCAXIS
017100,000266: 27,2221 56225 CHEKAXIS
017101,000267: 27,2222 77775 U=SCAXIS VLOAD
017102,000268: 27,2223 03351 SCAXIS
017103,000269: 27,2224 03343 STORE COF # ROTATE ABOUT + SCAXIS
017104,000270: 27,2225 51545 CHEKAXIS DLOAD ABS
017105,000271: 27,2226 03351 SCAXIS # SEE IF WE ARE POINTING THE AOT
017106,000272: 27,2227 51025 DSU BPL
017107,000273: 27,2230 16320 SINVEC2 # SIN 29.5 DEGS $2
017108,000274: 27,2231 56235 PICKANG1 # IF SO, ROTATE 50 DEGS ABOUT +- SCAXIS
017109,000275: 27,2232 52145 DLOAD GOTO # IF NOT, MUST BE POINTING THE TRANSPONDER
017110,000276: 27,2233 16324 VECANG2 # OR SOME VECTOR IN THE Y, OR Z PLANE
017111,000277: 27,2234 56237 COMPMFSN # IN THIS CASE ROTATE 35 DEGS TO GET OUT
017112,000278: # OF GIMBAL LOCK (VECANG2 $360)
017113,000279: 27,2235 77745 PICKANG1 DLOAD
017114,000280: 27,2236 16322 VECANG1 # = 50 DEGS $ 360
017115,000281: 27,2237 77624 COMPMFSN CALL
017116,000282: 27,2240 44530 DELCOMP # COMPUTE THE ROTATION ABOUT SCAXIS TO
017117,000283: 27,2241 75160 AXC,1 AXC,2 # BRING MFS OUT OF GIMBAL LOCK
017118,000284: 27,2242 03320 MIS
017119,000285: 27,2243 03425 DEL
017120,000286: 27,2244 77624 CALL # COMPUTE THE NEW TRANSFORMATION FROM
017121,000287: 27,2245 44304 MXM3 # DESIRED S/C AXES TO STABLE MEMBER AXES
017122,000288: # WHICH WILL ALIGN VI WITH VF AND AVOID
017123,000289: # GIMBAL LOCK
017124,000290: 27,2246 45160 FINDGIMB AXC,1 CALL
017125,000291: 27,2247 00000 0 # EXTRACT THE COMMANDED CDU ANGLES FROM
017126,000292: 27,2250 44655 DCMTOCDU # THIS MATRIX
017127,000293: 27,2251 40234 RTB SETPD
017128,000294: 27,2252 45552 V1STO2S # CONVERT TO 2:S COMPLEMENT
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017130,000296: 27,2253 00001 0
017131,000297: 27,2254 77650 GOTO
017132,000298: 27,2255 03310 VECQTEMP # RETURN TO CALLER
017133,000299:
017134,000300: 27,2256 50375 PICKAXIS VLOAD DOT # IF VF X VI = 0, FIND VF . VI
017135,000301: 27,2257 00035 28D
017136,000302: 27,2260 03351 SCAXIS
017137,000303: 27,2261 72240 BMN TLOAD
017138,000304: 27,2262 56266 ROT180
017139,000305: 27,2263 00032 25D
017140,000306: 27,2264 77650 GOTO # IF VF = VI, CDU DESIRED = PRESENT CDU
017141,000307: 27,2265 03310 VECQTEMP # PRESENT CDU ANGLES
017142,000308:
017143,000309: 27,2266 47375 ROT180 VLOAD VXV # IF VF, VI ANTIPARALLEL, 180 DEG ROTATION
017144,000310: 27,2267 03327 MIS +6 # IS REQUIRED. Y STABLE MEMBER AXIS IN
017145,000311: 27,2270 15333 HIUNITX # INITIAL S/C AXIS.
017146,000312: 27,2271 47256 UNIT VXV # FIND Y(SM) X X(I)
017147,000313: 27,2272 03351 SCAXIS # FIND UNIT(VI X UNIT(Y(SM) X X(I)))
017148,000314: 27,2273 40056 UNIT BOV # I.E. PICK A VECTOR IN THE PLANE OF X(I),
017149,000315: 27,2274 56310 PICKX # Y(SM) PERPENDICULAR TO VI
017150,000316: 27,2275 17343 STODL COF
017151,000317: 27,2276 00045 36D # CHECK MAGNITUDE
017152,000318: 27,2277 50025 DSU BMN # OF THIS VECTOR.
017153,000319: 27,2300 16327 DPB-14 # IF LESS THAN B-14,
017154,000320: 27,2301 56310 PICKX # PICK X-AXIS.
017155,000321: 27,2302 77775 VLOAD
017156,000322: 27,2303 03343 COF
017157,000323: 27,2304 17343 XROT STODL COF
017158,000324: 27,2305 15333 HIDPHALF
017159,000325: 27,2306 77650 GOTO
017160,000326: 27,2307 56160 COMPMATX
017161,000327: 27,2310 52175 PICKX VLOAD GOTO # PICK THE XAXIS IN THIS CASE
017162,000328: 27,2311 15333 HIUNITX
017163,000329: 27,2312 56304 XROT
017164,000330: 35,2000 BANK 35
017165,000331: 27,2000 SETLOC MANUVER1
017166,000332: 27,2000 BANK
017167,000333:
017168,000334: 27,2313 15555 35172 SINGIMLC 2DEC .4285836003 # = SIN(59) $2
017169,000335:
017170,000336: 27,2315 14113 36326 SINVEC1 2DEC .3796356537 # = SIN(49.4) $2
017171,000337:
017172,000338: 27,2317 07701 35703 SINVEC2 2DEC .2462117800 # = SIN(29.5) $2
017173,000339:
017174,000340: 27,2321 04343 21616 VECANG1 2DEC .1388888889 # = 50 DEGREES $360
017175,000341:
017176,000342: 27,2323 03070 34344 VECANG2 2DEC .09722222222 # = 35 DEGREES $360
017177,000343:
017178,000344:
017179,000345: 27,2325 00000 1BITDP OCT 0 # KEEP THIS BEFORE DPB(-14) *********
017180,000346: 27,2326 00001 DPB-14 OCT 00001
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017182,000348: 27,2327 00000 OCT 00000
017183,000349: 34,2002 BANK 34
017184,000350: 27,2000 SETLOC MANUVER
017185,000351: 27,2000 BANK
017186,000352:
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Page 398
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017188,000354: # ROUTINE FOR INITIATING AUTOMATIC MANEUVER VIA KEYBOARD (V49)
017189,000355:
017190,000356: 27,2330 1155 EBANK= CPHI
017191,000357:
017192,000358: 27,2330 COUNT 27/R62
017193,000359:
017194,000360: 27,2330 35052 R62DISP CAF V06N22 # DISPLAY COMMAND ICDUS CPHI, CTHETA, CPHI
017195,000361: 27,2331 04662 TC BANKCALL
017196,000362: 27,2332 20720 CADR GOFLASH
017197,000363: 27,2333 15534 TCF ENDEXT
017198,000364: 27,2334 12336 TCF GOMOVE # PROCEED
017199,000365: 27,2335 12330 TCF R62DISP # ENTER
017200,000366:
017201,000367: # ASTRONAUT MAY LOAD NEW ICDUS AT THIS
017202,000368: # POINT
017203,000369: 27,2336 05546 GOMOVE TC UPFLAG # SET 3-AXIS FLAG
017204,000370: 27,2337 00124 ADRES 3AXISFLG # BIT 6 FLAG 5
017205,000371:
017206,000372: 27,2340 04662 TC BANKCALL
017207,000373: 27,2341 56000 CADR R60CSM
017208,000374: 27,2342 15534 TCF ENDEXT
017209,000375:
End of include-file R60,R62.agc. Parent file is MAIN.agc