162 lines
4.3 KiB
Plaintext
162 lines
4.3 KiB
Plaintext
# Copyright: Public domain.
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# Filename: P76.agc
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# Purpose: Part of the source code for Luminary 1A build 099.
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# It is part of the source code for the Lunar Module's (LM)
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# Apollo Guidance Computer (AGC), for Apollo 11.
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# Assembler: yaYUL
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# Contact: Ron Burkey <info@sandroid.org>.
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# Website: www.ibiblio.org/apollo.
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# Pages: 709-711
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# Mod history: 2009-05-19 RSB Adapted from the corresponding
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# Luminary131 file, using page
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# images from Luminary 1A.
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#
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# This source code has been transcribed or otherwise adapted from
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# digitized images of a hardcopy from the MIT Museum. The digitization
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# was performed by Paul Fjeld, and arranged for by Deborah Douglas of
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# the Museum. Many thanks to both. The images (with suitable reduction
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# in storage size and consequent reduction in image quality as well) are
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# available online at www.ibiblio.org/apollo. If for some reason you
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# find that the images are illegible, contact me at info@sandroid.org
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# about getting access to the (much) higher-quality images which Paul
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# actually created.
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#
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# Notations on the hardcopy document read, in part:
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#
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# Assemble revision 001 of AGC program LMY99 by NASA 2021112-61
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# 16:27 JULY 14, 1969
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# Page 709
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# 1) PROGRAM NAME - TARGET DELTA V PROGRAM (P76).
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# 2) FUNCTIONAL DESCRIPTION - UPON ENTRY BY ASTRONAUT ACTION, P76 FLASHES DSKY REQUESTS TO THE ASTRONAUT
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# TO PROVIDE VIA DSKY (1) THE DELTA V TO BE APPLIED TO THE OTHER VEHICLE STATE VECTOR AND (2) THE
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# TIME (TIG) AT WHICH THE OTHER VEHICLE VELOCITY WAS CHANGED BY EXECUTION OF A THRUSTING MANEUVER. THE
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# OTHER VEHICLE STATE VECTOR IS INTEGRATED TO TIG AND UPDATED BY THE ADDITION OF DELTA V (DELTA V HAVING
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# BEEN TRANSFORMED FROM LV TO REF COSYS). USING INTEGRVS, THE PROGRAM THEN INTEGRATES THE OTHER
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# VEHICLE STATE VECTOR TO THE STATE VECTOR OF THIS VEHICLE, THUS INSURING THAT THE W-MATRIX AND BOTH VEHICLE
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# STATES CORRESPOND TO THE SAME TIME.
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# 3) ERASABLE INIITIALIZATION REQUIRED - NONE.
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# 4) CALLING SEQUENCES AND EXIT MODES - CALLED BY ASTRONAUT REQUEST THRU DSKY V 37 E 76 E.
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# EXITS BY TCF ENDOFJOB.
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# 5) OUTPUT -- OTHER VEHICLE STATE VECTOR INTEGRATED TO TIG AND INCREMENTED BY DELTA V IN REF COSYS.
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# THE PUSHLIST CONTAINS THE MATRIX BY WHICH THE INPUT DELTA V MUST BE POST-MULTIPLIED TO CONVERT FROM LV
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# TO REF COSYS.
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# 6) DEBRIS - OTHER VEHICLE STATE VECTOR.
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# 7) SUBROUTINES CALLED - BANKCALL, GOXDSPF, CSMPREC (OR LEMPREC), ATOPCSM (OR ATOPLEM), INTSTALL, INTWAKE, PHASCHNG
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# INTPRET, INTEGRVS, AND MINIRECT.
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# 8) FLAG USE - MOONFLAG, CMOONFLG, INTYPFLG, RASFLAG, AND MARKCTR.
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BANK 30
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SETLOC P76LOC
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BANK
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COUNT* $$/P76
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EBANK= TIG
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P76 TC UPFLAG
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ADRES TRACKFLG
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TC INTPRET
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VLOAD
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DELVLVC
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STORE DELVOV
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EXIT
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CAF V06N84 # FLASH LAST DELTA V,
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TC BANKCALL # AND WAIT FOR KEYBOARD ACTION.
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CADR GOFLASH
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TCF ENDP76
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TC +2 # PROCEED
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TC -5 # STORE DATA AND REPEAT FLASHING
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CAF V06N84 +1 # FLASH VERB 06 NOUN 33, DISPLAY LAST TIG,
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TC BANKCALL # AND WAIT FOR KEYBOARD ACTION.
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CADR GOFLASH
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TCF ENDP76
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TC +2
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TC -5
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TC INTPRET # RETURN TO INTERPRETIVE CODE
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# Page 710
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DLOAD # SET D(MPAC)=TIG IN CSEC B28
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TIG
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STCALL TDEC1 # SET TDEC1=TIG FOR ORBITAL INTEGRATION
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OTHPREC
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COMPMAT VLOAD UNIT
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RATT
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VCOMP # U(-R)
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STORE 24D # U(-R) TO 24D
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VXV UNIT # U(-R) XV = U(VXR)
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VATT
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STORE 18D
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VXV UNIT # U(VXR)XU(-R) = U((RXV)XR)
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24D
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STOVL 12D
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DELVOV
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VXM VSL1 # V(MPAC)=DELTA V IN REFCOSYS
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12D
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VAD
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VATT
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STORE 6 # V(PD6)=VATT + DELTA V
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CALL # PRESENT WOULD-BE USER OF ORBITAL
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INTSTALL # INTEG FROM INTERFERING WITH UPDATING
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CALL
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P76SUB1
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VLOAD VSR*
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6
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0,2
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STOVL VCV
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RATT
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VSR*
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0,2
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STODL RCV
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TIG
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STORE TET
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CLEAR DLOAD
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INTYPFLG
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TETTHIS
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INTOTHIS STCALL TDEC1
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INTEGRVS
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CALL
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INTSTALL
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VLOAD
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RATT1
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STORE RRECT
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STODL RCV
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TAT
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STOVL TET
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VATT1
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CALL
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MINIRECT
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# Page 711
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EXIT
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TC PHASCHNG
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OCT 04024
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TC UPFLAG
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ADRES REINTFLG
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TC INTPRET
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CALL
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ATOPOTH
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SSP EXIT
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QPRET
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OUT
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TC BANKCALL # PERMIT USE OF ORBITAL INTEGRATION
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CADR INTWAKE1
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OUT EXIT
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ENDP76 CAF ZERO
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TS MARKCTR # CLEAR RR TRACKING MARK COUNTER
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TCF GOTOPOOH
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V06N84 NV 0684
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NV 0633
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P76SUB1 AXT,2 SET
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2
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MOONFLAG # SET MEANS MOON IS SPHERE OF INFLUENCE.
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BON AXT,2
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CMOONFLG # SET MEANS PERM CM STATE IN LUNAR SPHERE.
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QPRET
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0
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CLEAR RVQ
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MOONFLAG
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