### FILE="Main.annotation"
## Copyright: Public domain.
## Filename: P76.agc
## Purpose: The main source file for Luminary revision 069.
## It is part of the source code for the original release
## of the flight software for the Lunar Module's (LM) Apollo
## Guidance Computer (AGC) for Apollo 10. The actual flown
## version was Luminary 69 revision 2, which included a
## newer lunar gravity model and only affected module 2.
## This file is intended to be a faithful transcription, except
## that the code format has been changed to conform to the
## requirements of the yaYUL assembler rather than the
## original YUL assembler.
## Reference: pp. 717-719
## Assembler: yaYUL
## Contact: Ron Burkey <info@sandroid.org>.
## Website: www.ibiblio.org/apollo/index.html
## Mod history: 2016-12-13 MAS Created from Luminary 99.
## 2016-12-14 MAS Updated from comment-proofed Luminary 99 version.
## 2016-12-15 RRB Updated for Luminary 69.
## 2017-01-28 RSB Proofed comment text using octopus/prooferComments
## but no errors found.
## Page 717
# 1) PROGRAM NAME - TARGET DELTA V PROGRAM (P76).
# 2) FUNCTIONAL DESCRIPTION - UPON ENTRY BY ASTRONAUT ACTION, P76 FLASHES DSKY REQUESTS TO THE ASTRONAUT
# TO PROVIDE VIA DSKY (1) THE DELTA V TO BE APPLIED TO THE OTHER VEHICLE STATE VECTOR AND (2) THE
# TIME (TIG) AT WHICH THE OTHER VEHICLE VELOCITY WAS CHANGED BY EXECUTION OF A THRUSTING MANEUVER. THE
# OTHER VEHICLE STATE VECTOR IS INTEGRATED TO TIG AND UPDATED BY THE ADDITION OF DELTA V (DELTA V HAVING
# BEEN TRANSFORMED FROM LV TO REF COSYS). USING INTEGRVS, THE PROGRAM THEN INTEGRATES THE OTHER
# VEHICLE STATE VECTOR TO THE STATE VECTOR OF THIS VEHICLE, THUS INSURING THAT THE W-MATRIX AND BOTH VEHICLE
# STATES CORRESPOND TO THE SAME TIME.
# 3) ERASABLE INITIALIZATION REQUIRED - NONE.
# 4) CALLING SEQUENCES AND EXIT MODES - CALLED BY ASTRONAUT REQUEST THRU DSKY V 37 E 76E.
# EXITS BY TCF ENDOFJOB.
# 5) OUTPUT - OTHER VEHICLE STATE VECTOR INTEGRATED TO TIG AND INCREMENTED BY DELTA V IN REF COSYS.
# THE PUSHLIST CONTAINS THE MATRIX BY WHICH THE INPUT DELTA V MUST BE POST-MULTIPLIED TO CONVERT FROM LV
# TO REF COSYS.
# 6) DEBRIS - OTHER VEHICLE STATE VECTOR.
# 7) SUBROUTINES CALLED - BANKCALL, GOXDSPF, CSMPREC (OR LEMPREC), ATOPCSM (OR ATOPLEM), INTSTALL, INTWAKE, PHASCHNG
# INTPRET, INTEGRVS, AND MINIRECT.
# 8) FLAG USE - MOONFLAG, CMOONFLAG, INTYPFLG, RASFLAG, AND MARKCTR.
BANK 30
SETLOC P76LOC
BANK
COUNT* $$/P76
EBANK= TIG
P76 TC UPFLAG
ADRES TRACKFLG
TC INTPRET
VLOAD
DELVLVC
STORE DELVOV
EXIT
CAF V06N84 # FLASH LAST DELTA V,
TC BANKCALL # AND WAIT FOR KEYBOARD ACTION.
CADR GOFLASH
TCF ENDP76
TC +2 # PROCEED
TC -5 # STORE DATA AND REPEAT FLASHING
CAF V06N84 +1 # FLASH VERB 06 NOUN 33, DISPLAY LAST TIG,
TC BANKCALL # AND WAIT FOR KEYBOARD ACTION.
CADR GOFLASH
TCF ENDP76
TC +2
TC -5
TC INTPRET # RETURN TO INTERPRETIVE CODE
## Page 718
DLOAD # SET D(MPAC)=TIG IN CSEC B28
TIG
STCALL TDEC1 # SET TDEC1=TIG FOR ORBITAL INTEGRATION
OTHPREC
COMPMAT VLOAD UNIT
RATT
VCOMP # U(-R)
STORE 24D # U(-R) TO 24D
VXV UNIT # U(-R) X V = U(V X R)
VATT
STORE 18D
VXV UNIT # U(V X R) X U(-R) = U((R X V) X R)
24D
STOVL 12D
DELVOV
VXM VSL1 # V(MPAC)=DELTA V IN REFCOSYS
12D
VAD
VATT
STORE 6 # V(PD6)=VATT + DELTA V
CALL # PREVENT WOULD-BE USER OF ORBITAL
INTSTALL # INTEG FROM INTERFERING WITH UPDATING
CALL
P76SUB1
VLOAD VSR*
6
0,2
STOVL VCV
RATT
VSR*
0,2
STODL RCV
TIG
STORE TET
CLEAR DLOAD
INTYPFLG
TETTHIS
INTOTHIS STCALL TDEC1
INTEGRVS
CALL
INTSTALL
VLOAD
RATT1
STORE RRECT
STODL RCV
TAT
STOVL TET
VATT1
CALL
MINIRECT
## Page 719
EXIT
TC PHASCHNG
OCT 04024
TC UPFLAG
ADRES REINTFLG
TC INTPRET
CALL
ATOPOTH
SSP EXIT
QPRET
OUT
TC BANKCALL # PERMIT USE OF ORBITAL INTEGRATION
CADR INTWAKE1
OUT EXIT
ENDP76 CAF ZERO
TS MARKCTR # CLEAR RR TRACKING MARK COUNTER
TCF GOTOPOOH
V06N84 NV 0684
NV 0633
P76SUB1 AXT,2 SET
2
MOONFLAG # SET MEANS MOON IS SPHERE OF INFLUENCE.
BON AXT,2
CMOONFLG # SET MEANS PERM CM STATE IN LUNAR SPHERE.
QPRET
0
CLEAR RVQ
MOONFLAG