Source Code
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These source-code files were obtained by digitally photographing
an Artemis 72 program listing from a private collection and then
modifying pre-existing Comanche 55 (Apollo 11) source files to
incorporate changes. Note that the page images
presented online are of reduced quality, and that additional images
may be available. Report any conversion errors or legibility
problems in page images to info@sandroid.org.
Notations on the program listing read, in part:GAP: ASSEMBLE REVISION 072 OF AGC PROGRAM ARTEMIS BY NASA 2021114-011 11:40 FEB. 26, 1971 THIS AGC PROGRAM SHALL ALSO BE REFERRED TO AS COLOSSUS 3 THIS PROGRAM IS INTENDED FOR USE IN THE CM AS SPECIFIED IN REPORT R-577. THIS PROGRAM WAS PREPARED UNDER OSR PROJECT 55-23890, SPONSORED BY THE MANNED SPACECRAFT CENTER OF THE NATIONAL AERONAUTICS AND SPACE ADMINISTRATION THROUGH CONTRACT NAS 9-4065 WITH THE CHARLES STARK DRAPER LABORATORY, MASSACHUSETTS INSTITUTE OF TECHNOLOGY, CAMBRIDGE, MASS. |
052970,000002: # Copyright: Public domain.
052971,000003: # Filename: PLANETARY_INERTIAL_ORIENTATION.agc
052972,000004: # Purpose: Part of the source code for Artemis (i.e., Colossus 3),
052973,000005: # build 072. This is for the Command Module's (CM)
052974,000006: # Apollo Guidance Computer (AGC), we believe for
052975,000007: # Apollo 15-17.
052976,000008: # Assembler: yaYUL
052977,000009: # Contact: Sergio Navarro <sergionavarrog@gmail.com>
052978,000010: # Website: www.ibiblio.org/apollo/index.html
052979,000011: # Page scans: www.ibiblio.org/apollo/ScansForConversion/Artemis072/
052980,000012: # Mod history: 2009-09-03 SN Adapted from corresponding Comanche 055 file.
052981,000013: # 2009-09-05 JL Fix typos. Remove code not in Artemis072.
052982,000014: # 2010-02-20 RSB Un-##'d this header.
052983,000015:
052984,000016: # # Page 1243
052985,000017: # PLANETARY INERTIAL ORIENTATION
052986,000018:
052987,000019: # ..... RP-TO-R SUBROUTINE .....
052988,000020: # SUBROUTINE TO CONVERT RP (VECTOR IN PLANETARY COORDINATE SYSTEM, EITHER
052989,000021: # EARTH-FIXED OR MOON-FIXED) TO R (SAME VECTOR IN BASIC REF. SYSTEM)
052990,000022:
052991,000023: # R = MT(T) * (RP + LP X RP) MT = M MATRIX TRANSPOSE
052992,000024:
052993,000025: # CALLING SEQUENCE
052994,000026: # L CALL
052995,000027: # L+1 RP-TO-R
052996,000028:
052997,000029: # SUBROUTINES USED
052998,000030: # EARTHMX, MOONMX, EARTHL
052999,000031:
053000,000032: # ITEMS AVAILABLE FROM LAUNCH DATA
053001,000033: # 504LM = THE LIBRATION VECTOR L OF THE MOON AT TIME TIMSUBL, EXPRESSED
053002,000034: # IN THE MOON-FIXED COORD. SYSTEM RADIANS B0
053003,000035:
053004,000036: # ITEMS NECESSARY FOR SUBR. USED (SEE DESCRIPTION OF SUBR.)
053005,000037:
053006,000038: # INPUT
053007,000039: # MPAC = 0 FOR EARTH, NON-ZERO FOR MOON
053008,000040: # 0-5D = RP VECTOR
053009,000041: # 6-7D = TIME
053010,000042:
053011,000043: # OUTPUT
053012,000044: # MPAC = R VECTOR METERS B-29 FOR EARTH, B-27 FOR MOON
053013,000045:
053014,000046: 26,2000 SETLOC PLANTIN
053015,000047: 26,2000 BANK
053016,000048:
053017,000049: 26,3345 COUNT* $$/LUROT
053018,000050:
053019,000051: 26,3345 46020 RP-TO-R STQ BHIZ
053020,000052: 26,3346 00050 RPREXIT
053021,000053: 26,3347 55362 RPTORA
053022,000054: 26,3350 77624 CALL # COMPUTE M MATRIX FOR MOON
053023,000055: 26,3351 55416 MOONMX # LP=LM FOR MOON RADIANS B0
053024,000056: 26,3352 77775 VLOAD
053025,000057: 26,3353 02012 504LM
053026,000058: 26,3354 53235 RPTORB VXV VAD
053027,000059: 26,3355 00001 504RPR
053028,000060: 26,3356 00001 504RPR
053029,000061: 26,3357 52105 VXM GOTO
053030,000062: 26,3360 00025 MMATRIX # MPAC=R=MT(T)*(RP+LPXRP)
053031,000063: 26,3361 55406 RPRPXXXX # RESET PUSHLOC TO 0 BEFORE EXITING
053032,000064: 26,3362 77624 RPTORA CALL # EARTH COMPUTATIONS
053033,000065: 26,3363 55567 EARTHMX # M MATRIX B-1
053034,000066: # AND L VECTOR RADIANS B0
053035,000067: 26,3364 76521 MXV VSL1 # LP=M(T)*L RAD B-0
053036,000068: 26,3365 00025 MMATRIX
053037,000069: 26,3366 77650 GOTO
053038,000070: # # Page 1244
053039,000071: 26,3367 55354 RPTORB
053040,000072:
053041,000073: # # Page 1245
053042,000074: # ..... R-TO-RP SUBROUTINE .....
053043,000075: # SUBROUTINE TO CONVERT R (VECTOR IN REFERENCE COORD. SYSTEM) TO RP
053044,000076: # (VECTOR IN PLANETARY COORD SYSTEM) EITHER EARTH-FIXED OR MOON-FIXED
053045,000077:
053046,000078: # RP = M(T) * (R - L X R)
053047,000079:
053048,000080: # CALLING SEQUENCE
053049,000081: # L CALL
053050,000082: # L+1 R-TO-RP
053051,000083:
053052,000084: # SUBROUTINES USED
053053,000085: # EARTHMX, MOONMX, EARTHL
053054,000086:
053055,000087: # INPUT
053056,000088: # MPAC = 0 FOR EARTH, NON-ZERO FOR MOON
053057,000089: # 0-5D = R VECTOR
053058,000090: # 6-7D = TIME
053059,000091:
053060,000092: # ITEMS AVAILABLE FROM LAUNCH DATA
053061,000093: # 504LM = THE LIBRATION VECTOR L OF THE MOON AT TIME TIMSUBL, EXPRESSED
053062,000094: # IN THE MOON-FIXED COORD. SYSTEM RADIANS B0
053063,000095:
053064,000096: # ITEMS NECESSARY FOR SUBROUTINES USED (SEE DESCRIPTION OF SUBR.)
053065,000097:
053066,000098: # OUTPUT
053067,000099: # MPAC = RP VECTOR METERS B-29 FOR EARTH, B-27 FOR MOON
053068,000100:
053069,000101: 26,3370 46020 R-TO-RP STQ BHIZ
053070,000102: 26,3371 00050 RPREXIT
053071,000103: 26,3372 55412 RTORPA
053072,000104: 26,3373 77624 CALL
053073,000105: 26,3374 55416 MOONMX
053074,000106: 26,3375 61375 VLOAD VXM
053075,000107: 26,3376 02012 504LM # LP=LM
053076,000108: 26,3377 00025 MMATRIX
053077,000109: 26,3400 77772 VSL1 # L = MT(T)*LP RADIANS B0
053078,000110: 26,3401 51235 RTORPB VXV BVSU
053079,000111: 26,3402 00001 504RPR
053080,000112: 26,3403 00001 504RPR
053081,000113: 26,3404 77721 MXV # M(T)*(R-LXR) B-2
053082,000114: 26,3405 00025 MMATRIX
053083,000115: 26,3406 40372 RPRPXXXX VSL1 SETPD
053084,000116: 26,3407 00001 0D
053085,000117: 26,3410 77650 GOTO
053086,000118: 26,3411 00050 RPREXIT
053087,000119: 26,3412 77624 RTORPA CALL # EARTH COMPUTATIONS
053088,000120: 26,3413 55567 EARTHMX
053089,000121: 26,3414 77650 GOTO # MPAC=L=(-AX,-AY,0) RAD B-0
053090,000122: 26,3415 55401 RTORPB
053091,000123:
053092,000124: # # Page 1246
053093,000125: # ..... MOONMX SUBROUTINE .....
053094,000126: # SUBROUTINE TO COMPUTE THE TRANSFORMATION MATRIX M FOR THE MOON
053095,000127:
053096,000128: # CALLING SEQUENCE
053097,000129: # L CALL
053098,000130: # L+1 MOONMX
053099,000131:
053100,000132: # SUBROUTINES USED
053101,000133: # NEWANGLE
053102,000134:
053103,000135: # INPUT
053104,000136: # 6-7D = TIME
053105,000137:
053106,000138: # ITEMS AVAILABLE FROM LAUNCH DATA
053107,000139: # BSUBO, BDOT
053108,000140: # TIMSUBO, NODIO, NODDOT, FSUBO, FDOT
053109,000141: # COSI = COS(I) B-1
053110,000142: # SINI = SIN(I) B-1
053111,000143: # I IS THE ANGLE BETWEEN THE MEAN LUNAR EQUATORIAL PLANE AND THE
053112,000144: # PLANE OF THE ECLIPTIC (1 DEGREE 32.1 MINUTES)
053113,000145:
053114,000146: # OUTPUT
053115,000147: # MMATRIX = 3X3 M MATRIX B-1 (STORED IN VAC AREA)
053116,000148:
053117,000149: 26,3416 40220 MOONMX STQ SETPD
053118,000150: 26,3417 00051 EARTHMXX
053119,000151: 26,3420 00011 8D
053120,000152: 26,3421 77770 AXT,1 # B REQUIRES SL 0, SL 5 IN NEWANGLE
053121,000153: 26,3422 00005 5
053122,000154: 26,3423 65345 DLOAD PDDL # PD 10D 8-9D=BSUBO
053123,000155: 26,3424 15647 BSUBO # 10-11D=BDOT
053124,000156: 26,3425 15641 BDOT
053125,000157: 26,3426 45006 PUSH CALL # PD 12D
053126,000158: 26,3427 55543 NEWANGLE # EXIT WITH PD 8D AND MPAC= B REVS B0
053127,000159: 26,3430 71406 PUSH COS # PD 10D
053128,000160: 26,3431 14041 STODL COB # PD 8D COS(B) B-1
053129,000161: 26,3432 77756 SIN # SIN(B) B-1
053130,000162: 26,3433 14043 STODL SOB # SETUP INPUT FOR NEWANGLE
053131,000163: 26,3434 15645 FSUBO # 8-9D=FSUBO
053132,000164: 26,3435 41525 PDDL PUSH # PD 10D THEN 12D 10-11D=FDOT
053133,000165: 26,3436 15637 FDOT
053134,000166: 26,3437 45170 AXT,1 CALL # F REQUIRES SL 1, SL 6 IN NEWANGLE
053135,000167: 26,3440 00004 4
053136,000168: 26,3441 55543 NEWANGLE # EXIT WITH PD 8D AND MPAC= F REVS B0
053137,000169: 26,3442 14027 STODL AVECTR +2 # SAVE F TEMP
053138,000170: 26,3443 15643 NODIO # 8-9D=NODIO
053139,000171: 26,3444 41525 PDDL PUSH # PD 10D THEN 12D 10-11D=NODDOT
053140,000172: 26,3445 15635 NODDOT # MPAC=T
053141,000173: 26,3446 45170 AXT,1 CALL # NODE REQUIRES SL 0, SL 5 IN NEWANGLE
053142,000174: 26,3447 00005 5
053143,000175: 26,3450 55543 NEWANGLE # EXIT WITH PD 8D AND MPAC= NODI REVS B0
053144,000176: # # Page 1247
053145,000177: 26,3451 71406 PUSH COS # PD 10D 8-9D= NODI REVS B0
053146,000178: 26,3452 77606 PUSH # PD 12D 10-11D= COS(NODI) B-1
053147,000179: 26,3453 00025 STORE AVECTR
053148,000180: 26,3454 76405 DMP SL1R
053149,000181: 26,3455 00041 COB # COS(NODI) B-1
053150,000182: 26,3456 14035 STODL BVECTR +2 # PD 10D 20-25D=AVECTR= COB*SIN(NODI)
053151,000183: 26,3457 76405 DMP SL1R # SOB*SIN(NODI)
053152,000184: 26,3460 00043 SOB
053153,000185: 26,3461 14037 STODL BVECTR +4 # PD 8D
053154,000186: 26,3462 41556 SIN PUSH # PD 10D -SIN(NODI) B-1
053155,000187: 26,3463 77676 DCOMP # 26-31D=BVECTR= COB*COS(NODI)
053156,000188: 26,3464 14033 STODL BVECTR # PD 8D SOB*COS(NODI)
053157,000189: 26,3465 00027 AVECTR +2 # MOVE F FROM TEMP LOC. TO 504F
053158,000190: 26,3466 14007 STODL 504F
053159,000191: 26,3467 76405 DMP SL1R
053160,000192: 26,3470 00041 COB
053161,000193: 26,3471 14027 STODL AVECTR +2
053162,000194: 26,3472 00011 SINNODI # 8-9D=SIN(NODI) B-1
053163,000195: 26,3473 76405 DMP SL1R
053164,000196: 26,3474 00043 SOB
053165,000197: 26,3475 14031 STODL AVECTR +4 # 0
053166,000198: 26,3476 15336 HI6ZEROS # 8-13D= CVECTR= -SOB B-1
053167,000199: 26,3477 57525 PDDL DCOMP # PD 10D COB
053168,000200: 26,3500 00043 SOB
053169,000201: 26,3501 63325 PDDL PDVL # PD 12D THEN PD 14D
053170,000202: 26,3502 00041 COB
053171,000203: 26,3503 00033 BVECTR
053172,000204: 26,3504 63361 VXSC PDVL # PD 20D BVECTR*SINI B-2
053173,000205: 26,3505 15633 SINI
053174,000206: 26,3506 00011 CVECTR
053175,000207: 26,3507 53361 VXSC VAD # PD 14D CVECTR*COSI B-2
053176,000208: 26,3510 15631 COSI
053177,000209: 26,3511 77772 VSL1
053178,000210: 26,3512 24041 STOVL MMATRIX +12D # PD 8D M2=BVECTR*SINI+CVECTR*COSI B-1
053179,000211: 26,3513 63361 VXSC PDVL # PD 14D
053180,000212: 26,3514 15633 SINI # CVECTR*SINI B-2
053181,000213: 26,3515 00033 BVECTR
053182,000214: 26,3516 52361 VXSC VSU # PD 8D BVECTR*COSI B-2
053183,000215: 26,3517 15631 COSI
053184,000216: 26,3520 65372 VSL1 PDDL # PD 14D
053185,000217: 26,3521 00007 504F # 8-13D=DVECTR=BVECTR*COSI-CVECTR*SINI B-1
053186,000218: 26,3522 74346 COS VXSC
053187,000219: 26,3523 00011 DVECTR
053188,000220: 26,3524 73525 PDDL SIN # PD 20D 14-19D= DVECTR*COSF B-2
053189,000221: 26,3525 00007 504F
053190,000222: 26,3526 52361 VXSC VSU # PD 14D AVECTR*SINF B-2
053191,000223: 26,3527 00025 AVECTR
053192,000224: 26,3530 77772 VSL1
053193,000225: 26,3531 14033 STODL MMATRIX +6 # M1= AVECTR*SINF-DVECTR*COSF B-1
053194,000226: 26,3532 00007 504F
053195,000227: # # Page 1248
053196,000228: 26,3533 74356 SIN VXSC # PD 8D
053197,000229: 26,3534 71525 PDDL COS # PD 14D 8-13D=DVECTR*SINF B-2
053198,000230: 26,3535 00007 504F
053199,000231: 26,3536 53361 VXSC VAD # PD 8D AVECTR*COSF B-2
053200,000232: 26,3537 00025 AVECTR
053201,000233: 26,3540 57572 VSL1 VCOMP
053202,000234: 26,3541 34025 STCALL MMATRIX # M0= -(AVECTR*COSF+DVECTR*SINF) B-1
053203,000235: 26,3542 00051 EARTHMXX
053204,000236:
053205,000237: # COMPUTE X=X0+(XDOT)(T+T0)
053206,000238: # 8-9D= X0 (REVS B-0), PUSHLOC SET AT 12D
053207,000239: # 10-11D=XDOT (REVS/CSEC) SCALED B+23 FOR WEARTH,B+28 FOR NODDOT AND BDOT
053208,000240: # AND B+27 FOR FDOT
053209,000241: # X1=DIFFERENCE IN 23 AND SCALING OF XDOT, =0 FOR WEARTH, 5 FOR NDDOT AND
053210,000242: # BDOT AND 4 FOR FDOT
053211,000243: # 6-7D=T (CSEC B-28), TIMSUBO= (CSEC B-42 TRIPLE PREC.)
053212,000244:
053213,000245: 26,3543 54345 NEWANGLE DLOAD SR # ENTER PD 12D
053214,000246: 26,3544 00007 6D
053215,000247: 26,3545 20617 14D
053216,000248: 26,3546 72371 TAD TLOAD # CHANGE MODE TO TP
053217,000249: 26,3547 01707 TIMSUBO
053218,000250: 26,3550 00155 MPAC
053219,000251: 26,3551 14017 STODL TIMSUBM # T+T0 CSEC B-42
053220,000252: 26,3552 00020 TIMSUBM +1
053221,000253: 26,3553 77605 DMP # PD 10D MULT BY XDOT IN 10-11D
053222,000254: 26,3554 43257 SL* DAD # PD 8D ADD X0 IN 8-9D AFTER SHIFTING
053223,000255: 26,3555 20206 5,1 # SUCH THAT SCALING IS B-0
053224,000256: 26,3556 67206 PUSH SLOAD # PD 10D SAVE PARTIAL (X0+XDOT*T) IN 8-9D
053225,000257: 26,3557 00017 TIMSUBM
053226,000258: 26,3560 41261 SL DMP
053227,000259: 26,3561 20212 9D
053228,000260: 26,3562 00013 10D # XDOT
053229,000261: 26,3563 43257 SL* DAD # PD 8D SHIFT SUCH THAT THIS PART OF X
053230,000262: 26,3564 20213 10D,1 # IS SCALED REVS/CSEC B-0
053231,000263: 26,3565 43400 HERE BOV RVQ # TURN OFF OVERFLOW IF SET BY SHIFT
053232,000264: 26,3566 55565 HERE # INSTRUCTION BEFORE EXITING.
053233,000265: # MPAC=X=X0+(XDOT)(T+T0) REVS B0
053234,000266:
053235,000267: # # Page 1249
053236,000268: # ..... EARTHMX SUBROUTINE .....
053237,000269: # SUBROUTINE TO COMPUTE THE TRANSFORMATION MATRIX M FOR THE EARTH
053238,000270:
053239,000271: # CALLING SEQUENCE
053240,000272: # L CALL
053241,000273: # L+1 EARTHMX
053242,000274:
053243,000275: # SUBROUTINE USED
053244,000276: # NEWANGLE
053245,000277:
053246,000278: # INPUT
053247,000279: # INPUT AVAILABLE FROM LAUNCH DATA AZO REVS B-0
053248,000280: # TEPHEM CSEC B-42
053249,000281: # 6-7D= TIME CSEC B-28
053250,000282:
053251,000283: # OUTPUT
053252,000284: # MMATRIX= 3X3 M MATRIX B-1 (STORED IN VAC AREA)
053253,000285:
053254,000286: 26,3567 40220 EARTHMX STQ SETPD # SET 8-9D=AZO
053255,000287: 26,3570 00051 EARTHMXX
053256,000288: 26,3571 00011 8D # 10-11D=WEARTH
053257,000289: 26,3572 77770 AXT,1 # FOR SL 5, AND SL 10 IN NEWANGLE
053258,000290: 26,3573 00000 0
053259,000291: 26,3574 65345 DLOAD PDDL # LEAVING PD SET AT 12D FOR NEWANGLE
053260,000292: 26,3575 15653 AZO
053261,000293: 26,3576 15651 WEARTH
053262,000294: 26,3577 45006 PUSH CALL
053263,000295: 26,3600 55543 NEWANGLE
053264,000296: 26,3601 41401 SETPD PUSH # 18-19D=504AZ
053265,000297: 26,3602 00023 18D # COS(AZ) SIN(AZ) 0
053266,000298: 26,3603 65346 COS PDDL # 20-37D= MMATRIX= -SIN(AZ) COS(AZ) 0 B-1
053267,000299: 26,3604 00023 504AZ # 0 0 1
053268,000300: 26,3605 65356 SIN PDDL
053269,000301: 26,3606 15336 HI6ZEROS
053270,000302: 26,3607 73525 PDDL SIN
053271,000303: 26,3610 00023 504AZ
053272,000304: 26,3611 65276 DCOMP PDDL
053273,000305: 26,3612 00023 504AZ
053274,000306: 26,3613 63346 COS PDVL
053275,000307: 26,3614 15336 HI6ZEROS
053276,000308: 26,3615 41525 PDDL PUSH
053277,000309: 26,3616 15334 HIDPHALF
053278,000310: # # Page 1250
053279,000311: # ..... EARTHL SUBROUTINE .....
053280,000312: # SUBROUTINE TO COMPUTE L VECTOR FOR EARTH
053281,000313:
053282,000314: # CALLING SEQUENCE
053283,000315: # L CALL
053284,000316: # L+1 EARTHL
053285,000317:
053286,000318: # INPUT
053287,000319: # AXO,AYO SET AT LAUNCH TIME WITH AYO IMMEDIATELY FOLLOWING AXO IN CORE
053288,000320:
053289,000321: # OUTPUT
053290,000322: # -AX
053291,000323: # MPAC= -AY RADIANS B-0
053292,000324: # 0
053293,000325:
053294,000326: 26,3617 71201 EARTHL SETPD DLOAD
053295,000327: 26,3620 00017 14D
053296,000328: 26,3621 15336 HI6ZEROS
053297,000329: 26,3622 65325 PDDL PDDL
053298,000330: 26,3623 01712 -AYO
053299,000331: 26,3624 01714 AXO
053300,000332: 26,3625 55476 DCOMP VDEF
053301,000333: 26,3626 77650 GOTO
053302,000334: 26,3627 00051 EARTHMXX
053303,000335:
053304,000336: # # Page 1251
053305,000337: # CONSTANTS AND ERASABLE ASSIGNMENTS
053306,000338:
053307,000339: 26,3630 04,3757 1B1 = DP1/2 # 1 SCALED B-1
053308,000340: 26,3630 17775 02052 COSI 2DEC* 9.996417320 E-1 B-1* # COS(5521.5 SEC.)
053309,000341: 26,3632 00333 10374 SINI 2DEC* 2.676579050 E-2 B-1* # SIN(5521.5 SEC.)
053310,000342: 26,3634 0000050 RPREXIT = S1 # R-TO-RP AND RP-TO-R SUBR EXIT
053311,000343: 26,3634 0000051 EARTHMXX = S2 # EARTHMX,MOONMX SUBR. EXITS
053312,000344: 26,3634 504RPR = 0D # 6 REGS R OR RP VECTOR
053313,000345: 26,3634 SINNODI = 8D # 2 SIN(NODI)
053314,000346: 26,3634 DVECTR = 8D # 6 D VECTOR MOON
053315,000347: 26,3634 CVECTR = 8D # 6 C VECTR MOON
053316,000348: 26,3634 504AZ = 18D # 2 AZ
053317,000349: 26,3634 TIMSUBM = 14D # 3 TIME SUB M (MOON) T+T0 IN GETAZ
053318,000350: 26,3634 504LPL = 14D # 6 L OR LP VECTOR
053319,000351: 26,3634 AVECTR = 20D # 6 A VECTOR (MOON)
053320,000352: 26,3634 BVECTR = 26D # 6 B VECTOR (MOON)
053321,000353: 26,3634 MMATRIX = 20D # 18 M MATRIX
053322,000354: 26,3634 COB = 32D # 2 COS(B) B-1
053323,000355: 26,3634 SOB = 34D # 2 SIN(B) B-1
053324,000356: 26,3634 504F = 6D # 2 F (MOON)
053325,000357: 26,3634 77665 42175 NODDOT 2DEC* -1.703706128 E-11 B28* # REVS/CS.
053326,000358: 26,3636 22211 00636 FDOT 2DEC* +4.253263471 E-9 B27* # REVS/CS.
053327,000359: 26,3640 77777 77767 BDOT 2DEC* -1.145531390 E-16 B28* # REVS/CS.
053328,000360: 26,3642 34076 30363 NODIO 2DEC* +8.788308600 E-1 B # REV.
053329,000361: 26,3644 24760 00133 FSUBO 2DEC* +6.552737750 E-1 B # REV.
053330,000362: 26,3646 02052 35250 BSUBO 2DEC* +6.511941688 E-2 B # REV.
053331,000363: 26,3650 37116 32631 WEARTH 2DEC* +1.160576171 E-7 B23* # REV/CS.
053332,000364: 26,3652 30576 10326 AZO 2DEC* +7.733314844 E-1 B # REVS.
End of include-file PLANETARY_INERTIAL_ORIENTATION.agc. Parent file is MAIN.agc