https://github.com/chrislgarry/Apollo-11
Tip revision: 422050965990dfa8ad1ffe4ae92e793d7d1ddae5 authored by panoreak on 11 October 2020, 02:01:06 UTC
Proof INPUT_OUTPUT_CHANNEL_BIT_DESCRIPTIONS.acg #592 (#708)
Proof INPUT_OUTPUT_CHANNEL_BIT_DESCRIPTIONS.acg #592 (#708)
Tip revision: 4220509
INTEGRATION_INITIALIZATION.agc
# Copyright: Public domain.
# Filename: INTEGRATION_INITIALIZATION.agc
# Purpose: Part of the source code for Luminary 1A build 099.
# It is part of the source code for the Lunar Module's (LM)
# Apollo Guidance Computer (AGC), for Apollo 11.
# Assembler: yaYUL
# Contact: Ron Burkey <info@sandroid.org>.
# Website: www.ibiblio.org/apollo.
# Pages: 1205-1226
# Mod history: 2009-05-26 RSB Adapted from the corresponding
# Luminary131 file, using page
# images from Luminary 1A.
# 2011-01-06 JL Fixed pseudo-label indentation.
#
# This source code has been transcribed or otherwise adapted from
# digitized images of a hardcopy from the MIT Museum. The digitization
# was performed by Paul Fjeld, and arranged for by Deborah Douglas of
# the Museum. Many thanks to both. The images (with suitable reduction
# in storage size and consequent reduction in image quality as well) are
# available online at www.ibiblio.org/apollo. If for some reason you
# find that the images are illegible, contact me at info@sandroid.org
# about getting access to the (much) higher-quality images which Paul
# actually created.
#
# Notations on the hardcopy document read, in part:
#
# Assemble revision 001 of AGC program LMY99 by NASA 2021112-061
# 16:27 JULY 14, 1969
# Page 1205
# 1.0 INTRODUCTION
# ----------------
#
# FROM A USER'S POINT OF VIEW, ORBITAL INTEGRATION IS ESSENTIALLY THE SAME AS THE 278 INTEGRATION
# PROGRAM. THE SAME ENTRANCES TO THE PROGRAM WILL BE MAINTAINED, THE SAME STALLING ROUTINE WILL BE USED AND
# OUTPUT WILL STILL BE VIA THE PUSHLIST. THE PRIMARY DIFFERENCES TO A USER INVOLVE THE ADDED CAPABILITY OF
# TERMINATING INTEGRATION AT A SPECIFIC FINAL RADIUS AND THE DIFFERENCE IN STATE VECTOR SCALING INSIDE AND OUTSIDE
# THE LUNAR SPHERE OF INFLUENCE.
#
# IN ORDER TO MAKE THE CSM(LEM)PREC AND CSM(LEM)CONIC ENTRANCES SIMILAR TO FLIGHT 278, THE INTEGRATION PROGRAM
# WILL ITSELF SET THE FINAL RADIUS (RFINAL) TO 0 SO THAT REACHING THE DESIRED TIME ONLY WILL TERMINATE
# INTEGRATION. THE DP REGISTER RFINAL MUST BE SET BY USERS OF INTEGRVS AND INTEGRV, AND MUST BE DONE AFTER THE
# CALL TC INTSTALL.
#
# WHEN THE LM IS ON THE LUNAR SURFACE (INDICATED BY LUNAR SURFACE FLAG SET) CALLS TO LEMCONIC, LEMPREC, AND
# INTEGRV WITH VINFLAG = 0 WILL RESULT IN THE USE OF THE PLANETARY INERTIAL ORIENTATION SUBROUTINES TO PROVIDE
# BOTH THE LM'S POSITION AND VELOCITY IN THE REFERENCE COORDINATE SYSTEM.
# THE PROGRAM WILL PROVIDE OUTPUT AS IF INTEGRATION WAS USED. THAT IS, THE PUSHLIST WILL BE SET AS NOTED BELOW AND
# THE PERMANENT STATE VECTOR UPDATED WHEN SPECIFIED BY AN INTEGRV CALL.
#
# USERS OF INTEGRVS DESIRING INTEGRATION (INTYPFLG = 0) SHOULD NOTE THAT THE OBLATENESS PERTURBATION COMPUTATION
# IN LUNAR ORBIT IS TIME DEPENDENT. THEREFORE, THE USER SHOULD SUPPLY AN INITIAL STATE VECTOR VALID AT SOME REAL
# TIME AND THE DESIRED TIME (TDEC1) ALSO AT SOME REAL TIME. FOR CONIC "INTEGRATION" THE USER MAY STILL USE ZERO
# AS THE INITIAL TIME AND DELTA TIME AS THE DESIRED TIME.
#
# 2.0 GENERAL DESCRIPTION
# -----------------------
#
# THE INTEGRATION PROGRAM OPERATES AS A CLOSED INTERPRETIVE SUBROUTINE AND PERFORMS THESE FUNCTIONS --
# 1) INTEGRATES (PRECISION OR CONIC) EITHER CSM OR LM STATE VECTOR
# 2) INTEGRATES THE W-MATRIX
# 3) PERMANENT OR TEMPORARY UPDATE OF THE STATE VECTOR
#
# THERE ARE SIX ENTRANCES TO THE INTEGRATION PROGRAM. FOUR OF THESE (CSMPREC, LEMPREC, CSMCONIC, LEMCONIC) SET
# ALL THE FLAGS REQUIRED IN THE INTEGRATION PROGRAM ITSELF TO CAUSE THE PRECISION OR CONIC INTEGRATION (KEPLER) OF
# THE LM OR CSM STATE VECTOR, AS THE NAMES SUGGEST. ONE ENTRANCE (INTEGRVS) PERMITS THE CALLING PROGRAM TO
# PROVIDE A STATE VECTOR TO BE INTEGRATED. THE CALLING PROGRAM MUST SET THE FLAGS INDICATING (1) PRECISION OR
# CONIC INTEGRATION, (2) IN OR OUT OF LUNAR SPHERE, (3) MIDCOURSE OR NOT, AND THE INTEGRATION PROGRAM COMPLETES
# THE FLAG SETTING TO BYPASS W-MATRIX INTEGRATION. THE LAST ENTRANCE (INTEGRV, USED IN GENERAL BY THE
# NAVIGATION PROGRAMS) PERMITS THE CALLER TO SET FIVE FLAGS (NOT MOONFLAG OR MIDFLAG) BUT NOT TO INPUT A STATE
# VECTOR. ANY PROGRAM WHICH CALLS INTEGRVS OR INTEGRV MUST CALL INTSTALL BEFORE IT SETS THE INTEGRATION FLAGS
# AND/OR STATE VECTOR.
#
# THREE SETS OF 42 REGISTERS AND 2 FLAGS ARE USED FOR THE STATE VECTORS. TWO SETS, WHICH MAY NOT BE OVERLAYED, ARE
# USED FOR THE PERMANENT STATE VECTORS FOR THE CSM AND LM. THE THIRD SET, WHICH MAY BE OVERLAYED WHEN INTEGRATION
# IS NOT BEING DONE, IS USED IN THE COMPUTATIONS.
#
# THE PERMANENT STATE VECTORS WILL BE PERIODICALLY UPDATED SO THAT THE VECTORS WILL NOT BE OLDER THAN 4 TIMESTEPS.
# THE PERMANENT STATE VECTORS WILL ALSO BE UPDATED WHENEVER THE W-MATRIX IS INTEGRATED OR WHEN A CALLER OF INTEGRV
# SETS STATEFLG (THE NAVIGATION PROGRAMS P20, P22.)
#
# Page 1206
# APPENDIX B OF THE USERS' GUIDE LISTS THE STATE VECTOR QUANTITIES.
#
# 2.1 RESTARTS
#
# PHASE CHANGES WILL BE MADE IN THE INTEGRATION PROGRAM ONLY FOR THE INTEGRV ENTRANCE (I.E., WHEN THE W-MATRIX IS
# INTEGRATED OR PERMANENT STATE VECTOR IS UPDATED.) THE GROUP NUMBER USED WILL BE THAT FOR THE P20-25 PROGRAMS
# (I.E., GROUP2) WINCE THE INTEGRV ENTRANCE WILL ONLY BE USED BY THESE PROGRAMS. IF A RESTART OCCURS DURING AN
# INTEGRATION OF THE STATE VECTOR ONLY, THE RECOVERY WILL BE TO THE LAST PHASE IN THE CALLING PROGRAM. CALLING
# PROGRAMS WHICH USE THE INTEGRV OR INTEGRVS ENTRANCE OF INTEGRATION WHOULD ENSURE THAT IF PHASE CHANGING IS DONE
# THAT IT IS PRIOR TO SETTING THE INTEGRATION INPUTS IN THE PUSHLIST.
# THIS IS BECAUSE THE PUSHLIST IS LOST DURING A RESTART.
#
# 2.2 SCALING
#
# THE INTEGRATION ROUTINE WILL MAINTAIN THE PERMANENT MEMORY STATE VECTORS IN THE SCALING AND UNITS DEFINED IN
# APPENDIX B OF THE USERS GUIDE. THE SCALING OF THE OUTPUT POSITION VECTOR DEPENDS ON THE ORIGIN OF THE COORDINATE
# SYSTEM AT THE DESIRED INTEGRATION TIME. THE COORDINATE SYSTEM TRANSFORMATION WILL BE DONE AUTOMATICALLY ON
# MULTIPLE TIMESTEP ENCKE INTEGRATION ONLY. THUS IT IS POSSIBLE TO HAVE OUTPUT FROM SUCCESSIVE INTEGRATIONS IN
# DIFFERENT SCALING.
# HOWEVER, RATT, VATT WILL ALWAYS BE SCALED THE SAME.
#
# 3.0 INPUT/OUTPUT
# ----------------
#
# PROGRAM INPUTS ARE THE FLAGS DESCRIBED IN APPENDIX A AND THE PERMANENT STATE VECTOR QUANTITIES DESCRIBED IN
# APPENDIX B OF THE USERS GUIDE, PLUS THE DESIRED TIME TO INTEGRATE TO IN TDEC1 (A PUSH LIST LOCATION).
# FOR INTEGRVS, THE RCV,VCV,TET OR THE TEMPORARY STATE VECTOR MUST BE SET, PLUS MOONFLAG AND MIDFLAG
#
# FOR SIMULATION THE FOLLOWING QUANTITIES MUST BE PRESET ---
# EARTH MOON
# 29 27
# RRECTCSM(LEM) RECTIFIED POSITION VECTOR METERS 2 2
#
# 7 5
# VRECTCSM(LEM) RECTIFIED VELOCITY VECTOR M/CSEC 2 2
#
# 28 28
# TETCSM(LEM) TIME STATE VECTOR IS VALID CSEC 2 2
# CUSTOMARILY 0, BUT NOTE LUNAR
# ORBIT DEPENDENCE ON REAL TIME.
#
# 22 18
# DELTAVCSM(LEM) POSITION DEVIATION METERS 2 2
# 0 IF TCCSM(LEM) = 0
#
# 3 -1
# NUVCSM(LEM) VELOCITY DEVIATION M/CSEC 2 2
# 0 IF TCCSM(LEM) = 0
# Page 1207
# 29 27
# RCVSM(LEM) CONIC POSITION METERS 2 2
# EQUALS RRECTCSM(LEM) IF
# TCCSM(LEM) = 0
#
# 7 5
# VCVCSM(LEM) CONIC VELOCITY M/CSEC 2 2
# EQUALS VRECTCSM(LEM) IF
# TCCSM(LEM) = 0
#
# 28 28
# TCCSM(LEM) TIME SINCE RECTIFICATION CSECS 2 2
# CUSTOMARILY 0
#
# 1/2 17 16
# XKEPCSM(LEM) ROOT OF KEPLER'S EQUATION M 2 2
# 0 IF TCCSM(LEM) = 0
#
# CMOONFLG PERMANENT FLAGS CORRESPONDING 0 0
# CMIDFLAG TO MOONFLAG AND MIDFLAG 0,1 0,1
# LMOONFLG C = CSM, L = LM 0 0
# LMIDFLG 0,1 0,1
#
# SURFFLAG LUNAR SURFACE FLAG 0,1 0,1
#
# IN ADDITION, IF (L)CMIDFLAG IS SET, THE INITIAL INPUT VALUES FOR LUNAR
# SOLAR EPHEMERIDES SUBROUTINE AND PLANETARY INERTIAL ORIENTATION SUB-
# ROUTINE MUST BE PRESET.
#
# OUTPUT
# AFTER EVERY CALL TO INTEGRATION
# EARTH MOON
# 29 29
# 0D RATT POSITION METERS 2 2
#
# 7 7
# 6D VATT VELOCITY M/CSEC 2 2
#
# 28 28
# 12D TAT TIME 2 2
#
# 29 27
# 14D RATT1 POSITION METERS 2 2
#
# 7 5
# 20D VATT1 VELOCITY M/CSEC 2 2
#
# 3 2 36 30
# 26D MU(P) MU M /CS 2 2
#
# X1 MUTABLE ENTRY -2 -10D
#
# X2 COORDINT
# X2 COORDINATE SYSTEM ORIGIN 0 2
# (THIS, NOT MOONFLAG, SHOULD BE
# Page 1208
# USED TO DETERMINE ORIGIN.)
#
# IN ADDITION TO THE ABOVE, THE PERMANENT STATE VECTOR IS UPDATED WHENEVER
# STATEFLG WAS SET AND WHENEVER A W-MATRIX IS TO BE INTEGRATED. THE PUSH
# COUNTER IS SET TO 0 AND OVERFLOW IS CLEARED BEFORE RETURNING TO THE
# CALLING PROGRAM.
#
# 4.0 CALLING SEQUENCES AND SAMPLE CODE
# -------------------------------------
#
# A) PRECISION ORBITAL INTEGRATION. CSMPREC, LEMPREC ENTRANCES
# L-X STORE TIME TO 96T5791T5 T 95 PUS L9ST (T4531)
# L CALL
# L+1 CSMPREC (OR LEMPREC)
# L+2 RETURN
# INPUT 28
# TDEC1 (PD 32D) TIME TO INTEGRATE TO...CENTISECONDS SCALED 2
# OUTPUT
# THE DATA LISTED IN SECTION 3.0 PLUS
# RQVV POSITION VECTOR OF VEHICLE WITH RESPECT TO SECONDARY
# BODY... METERS B-29 ONLY IF MIDFLAG = DIM0FLAG = 1
# B) CONIC INTEGRATION. CSMCONIC, LEMCONIC ENTRANCES
# L-X STORE TIME IN PUSH LIST (TDEC1)
# L CALL
# L+1 CSMCONIC (OR LEMCONIC)
# INPUT/OUTPUT
# SAME AS PRECISION INTEGRATION, EXCEPT RQVV NOT SET
# C) INTEGRATE GIVEN STATE VECTOR. INTEGRVS ENTRANCE
# CALL
# INTSTALL
# VLOAD
# POSITION VECTOR
# STOVL RCV
# VELOCITY VECTOR
# STODL VCV
# TIME STATE VECTOR VALID
# STODL TET
# FINAL RADIUS
# STORE RFINAL
# SET(CLEAR) SET(CLEAR)
# INTYPFLAG
# MOONFLAG
# SET(CLEAR) DLOAD
# DESIRED TIME
# STCALL TDEC1
# INTEGRVS
# INPUT
# RCV POSITION VECTOR METERS
# VCV VELOCITY VECTOR M/CSEC
# TET TIME OF STATE VECTOR (MAY = 0) CSEC B-28
# Page 1209
# TDEC1 TIME TO INTEGRATE TO CSEC B-28 (PD 32D)
# (MAY BE INCREMENT IF TET=0)
# OUTPUT
# SAME AS FOR PRECISION OR CONIC INTEGRATION,
# DEPENDING ON INTYPFLG.
# D) INTEGRATE STATE VECTOR. INTGRV ENTRANCE
# L-X STORE TIME IN PUSH LIST (TDEC1) (MAY BE DONE AFTER CALL TO INTSTALL)
# L-8 CALL
# L-7
# L-6 SET(CLEAR) SET(CLEAR)
# L-5 VINTFLAG 1=CSM, 0=LM
# L-4 INTYPFLAG 1=CONIC, 0=PRECISION
# L-3 SET(CLEAR) SET(CLEAR)
# L-2 DIM0FLAG 1=W-MATRIX, 0=NO W-MATRIX
# L-1 D6OR9FLG 1=9X9, 0=6X6
# L SET DLOAD
# L+1 STATEFLG DESIRE PERMANENT UPDATE
# L+2 FINAL RAD. OF STATE VECTOR
# L+3 STCALL RFINAL
# L+4 INTEGRV
# L CALL NORMAL USE -- WILL UPDATE STATE
# L+1 INTEGRV VECTOR IF DIM0FLAG=1. (STATEFLG IS
# L+2 RETURN ALWAYS RESET IN INTEGRATION AFTER
# IT USED.)
# INPUT
# TDEC1 (PD 32D) TIME TO INTEGRATE TO CSEC B-28
# OUTPUT
# SAME AS FOR PRECISION OR CONIC INTEGRATION
# THE PROGRAM WILL SET MOONFLAG, MIDFLAG DEPENDING ON
# THE PERMANENT STATE VECTOR REPRESENTATION.
BANK 11
SETLOC INTINIT
BANK
EBANK= RRECTCSM
COUNT* $$/INTIN
STATEINT TC PHASCHNG
OCT 00052
CAF PRIO5
TC FINDVAC
EBANK= RRECTCSM
2CADR STATINT1
TC TASKOVER
STATINT1 TC INTPRET
BON RTB
QUITFLAG # KILL INTEGRATION UNTIL NEXT P00.
NOINT
LOADTIME
STORE TDEC1
# Page 1210
CALL
INTSTALL
SET CALL
NODOFLAG
SETIFLGS
GOTO
STATEUP
600SECS 2DEC 60000
ENDINT CLEAR EXIT
STATEFLG
TC PHASCHNG
OCT 20032
EXTEND
DCA 600SECS
TC LONGCALL
EBANK= RRECTHIS
2CADR STATEINT
TC ENDOFJOB
SETIFLGS SET CLEAR
STATEFLG
INTYPFLG
CLEAR CLEAR
DIM0FLAG
D6OR9FLG
RVQ
NOINT EXIT
TC PHASCHNG
OCT 00002
TC DOWNFLAG
ADRES QUITFLAG
TC ENDOFJOB
# ATOPCSM TRANSFERS RRECT TO RRECT +41 TO RRECTCSM TO RRECTCSM +41
#
# CALLING SEQUENCE
# L CALL
# L+1 ATOPCSM
#
# NORMAL EXIT AT L+2
ATOPCSM STQ RTB
S2
MOVEACSM
SET CALL
CMOONFLG
SVDWN1
BON CLRGO
# Page 1211
MOONFLAG
S2
CMOONFLG
S2
MOVEACSM TC SETBANK
TS DIFEQCNT # INITIALIZE INDEX
INDEX DIFEQCNT
CA RRECT
INDEX DIFEQCNT
TS RRECTCSM
CCS DIFEQCNT # IS TRANSFER COMPLETE
TCF MOVEACSM +1 # NO-LOOP
TC DANZIG # COMPLETE -- RETURN
# PTOACSM TRANSFERS RRECTCSM TO RRECTCSM +41 TO RRECT TO RRECT +41
#
# CALLING SEQUENCE
# L CALL
# PTOACSM
#
# NORMAL EXIT AT L+2
PTOACSM RTB BON
MOVEPCSM
CMOONFLG
SETMOON
CLRMOON CLEAR SSP
MOONFLAG
PBODY
0
RVQ
SETMOON SET SSP
MOONFLAG
PBODY
2
RVQ
MOVEPCSM TC SETBANK
TS DIFEQCNT
INDEX DIFEQCNT
CA RRECTCSM
INDEX DIFEQCNT
TS RRECT
CCS DIFEQCNT
TCF MOVEPCSM +1
TC DANZIG
# ATOPLEM TRANSFERS RRECT TO RRECT +41 TO RRECTLEM TO RRECTLEM +41
ATOPLEM STQ RTB
# Page 1212
S2
MOVEALEM
SET CALL
LMOONFLG
SVDWN2
BON CLRGO
MOONFLAG
S2
LMOONFLG
S2
MOVEALEM TC SETBANK
TS DIFEQCNT
INDEX DIFEQCNT
CA RRECT
INDEX DIFEQCNT
TS RRECTLEM
CCS DIFEQCNT
TCF MOVEALEM +1
TC DANZIG
# PTOALEM TRANSFERS RRECTLEM TO RRECTLEM +41 TO RRECT TO RRECT +41
PTOALEM BON RTB
SURFFLAG
USEPIOS
MOVEPLEM
BON GOTO
LMOONFLG
SETMOON
CLRMOON
MOVEPLEM TC SETBANK
TS DIFEQCNT
INDEX DIFEQCNT
CA RRECTLEM
INDEX DIFEQCNT
TS RRECT
CCS DIFEQCNT
TCF MOVEPLEM +1
TC DANZIG
USEPIOS SETPD VLOAD
0
RLS
PDDL PUSH
TDEC1
STODL TET
5/8
CALL
# Page 1213
RP-TO-R
STOVL RCV
ZUNIT
STODL 0D
TET
STODL 6D
5/8
SET CALL # NEEDED FOR SETTING X1 ON EXIT
MOONFLAG
RP-TO-R
VXV VXSC
RCV
OMEGMOON
STOVL VCV
ZEROVEC
STORE TDELTAV
AXT,2 SXA,2
2
PBODY
STCALL TNUV
A-PCHK
SETBANK CAF INTBANK
TS BBANK
CAF FORTYONE
TC Q
EBANK= RRECTCSM
INTBANK BBCON INTEGRV
# SPECIAL PURPOSE ENTRIES TO ORBITAL INTEGRATION. THESE ROUTINES PROVIDE ENTRANCES TO INTEGRATION WITH
# APPROPRIATE SWITCHES SET OR CLEARED FOR THE DESIRED INTEGRATION.
#
# CSMPREC AND LEMPREC PERFORM ORBIT INTEGRATION BY THE ENCKE METHOD TO THE TIME INDICATED IN TDEC1.
# ACCELERATIONS DUE TO OBLATENESS ARE INCLUDED. NO W-MATRIX INT. IS DONE.
# THE PERMANENT STATE VECTOR IS NOT UPDATED.
#
# CSMCONIC AND LEMCONIC PERFORM ORBIT INTEG. BY KEPLER'S METHOD TO THE TIME INDICATED IN TDEC1.
# NO DISTURBING ACCELERATIONS ARE INCLUDED. IN THE PROGRAM FLOW THE GIVEN
# STATE VECTOR IS RECTIFIED BEFORE SOLUTION OF KEPLER'S EQUATION.
#
# THE ROUTINES ASSUME THAT THE CSM (LEM) STATE VECTOR IN P-MEM IS VALID.
# SWITCHES SET PRIOR TO ENTRY TO THE MAIN INTEG. PROG ARE AS FOLLOWS:
# CSMPREC CSMCONIC LEMPREC LEMCONIC
# VINTFLAG SET SET CLEAR CLEAR
# INTYPFLG CLEAR SET CLEAR SET
# DIM0FLAG CLEAR CLEAR CLEAR CLEAR
#
# CALLING SEQUENCE
# L-X STORE TDEC1
# L CALL (STCALL TDEC1)
# Page 1214
# L+1 CSMPREC (CSMCONIC, LEMPREC, LEMCONIC)
#
# NORMAL EXIT TO L+2
#
# SUBROUTINES CALLED
# INTEGRV1
# PRECOUT FOR CSMPREC AND LEMPREC
# CONICOUT FOR CSMCONIC AND LEMCONIC
#
# OUTPUT -- SEE PAGE 2 OF THIS LOG SECTION
#
# INPUT
# TDEC1 TIME TO INTEGRATE TO. CSECS B-28
CSMPREC STQ CALL
X1
INTSTALL
SXA,1 SET
IRETURN
VINTFLAG
IFLAGP SET CLEAR
PRECIFLG
DIM0FLAG
CLRGO
INTYPFLG
INTEGRV1
LEMPREC STQ CALL
X1
INTSTALL
SXA,1 CLRGO
IRETURN
VINTFLAG
IFLAGP
CSMCONIC STQ CALL
X1
INTSTALL
SXA,1 SET
IRETURN
VINTFLAG
IFLAGC CLEAR SETGO
DIM0FLAG
INTYPFLG
INTEGRV1
LEMCONIC STQ CALL
X1
INTSTALL
SXA,1 CLRGO
IRETURN
# Page 1215
VINTFLAG
IFLAGC
INTEGRVS SET SSP
PRECIFLG
PBODY
0
BOF SSP
MOONFLAG
+3
PBODY
2
STQ VLOAD
IRETURN
ZEROVEC
STORE TDELTAV
STCALL TNUV
RECTIFY
CLEAR SET
DIM0FLAG
NEWIFLG
SETGO
RPQFLAG
ALOADED
# INTEGRV IS AN ENTRY TO ORBIT INTEGRATION WHICH PERMITS THE CALLER,
# NORMALLY THE NAVIGATION PROGRAM, TO SET THE INTEG. FLAGS. THE ROUTINE
# IS ENTERED AT INTEGRV1 BY CSMPREC ET AL. AND AT ALOADED BY INTEGRVS.
# THE ROUTINE SETS UP A-MEMORY IF ENTERED AT INTEGRV,1 AND SETS THE INTEG.
# PROGRAM FOR PRECISION OR CONIC.
#
# THE CALLER MUST FIRST CALL INTSTALL TO CHECK IF INTEG. IS IN USE BEFORE
# SETTING ANY FLAGS.
#
# THE FLAGS WHICH SHOULD BE SET OR CLEARED ARE
# VINTFLAG (IGNORED WHEN ENTERED FROM INTEGRVS)
# INTYPFLG
# DIM0FLAG
# D6OR9FLG
#
# CALLING SEQUENCE
# L-X CALL
# L-Y INTSTALL
# L-1 SET OR CLEAR ALL FOUR FLAGS. ALSO CAN SET STATEFLG IF DESIRED
# AND DIM0FLAG IS CLEAR.
# L CALL
# L+1 INTEGRV
#
# INITIALIZATION
# FLAGS AS ABOVE
# STORE TIME TO INTEGRATE TO IN TDEC1
#
# OUTPUT
# RATT AS
# VATT DEFINED
# Page 1216
# TAT BEFORE
INTEGRV STQ
IRETURN
INTEGRV1 SET SET
RPQFLAG
NEWIFLG
INTEGRV2 SSP
QPRET
ALOADED
BON GOTO
VINTFLAG
PTOACSM
PTOALEM
ALOADED DLOAD
TDEC1
STORE TDEC
BOFF GOTO
INTYPFLG
TESTLOOP
RVCON
A-PCHK BOF EXIT
STATEFLG
RECTOUT
TC PHASCHNG
OCT 04022
TC UPFLAG # PHASE CHANGE HAS OCCURRED BETWEEN
ADRES REINTFLG # INTSTALL AND INTWAKE
TC INTPRET
SSP
QPRET
PHEXIT
BON GOTO
VINTFLAG
ATOPCSM
ATOPLEM
PHEXIT CALL
GRP2PC
RECTOUT SETPD CALL
0
RECTIFY
VLOAD VSL*
RRECT
0,2
PDVL VSL* # RATT TO PD0
VRECT
0,2
PDDL PDVL # VATT TO PD6 TAT TO PD12
TET
# Page 1217
RRECT
PDVL PDDL*
VRECT
MUEARTH,2
PUSH AXT,1
DEC -10
BON AXT,1
MOONFLAG
+2
DEC -2
INTEXIT SETPD BOV
0
+1
CLEAR CLEAR
AVEMIDSW # ALLOW UPDATE OF DOWNLINK STATE VECTOR
PRECIFLG
CLEAR
STATEFLG
SLOAD EXIT
IRETURN
CA MPAC
INDEX FIXLOC
TS QPRET
TC INTWAKE
# RVCON SETS UP ORBIT INTEGRATION TO DO A CONIC SOLUTION FOR POSITION AND
# VELOCITY FOR THE INTERVAL (TET-TDEC)
RVCON DLOAD DSU
TDEC
TET
STCALL TAU.
RECTIFY
CALL
KEPPREP
DLOAD DAD
TC
TET
STCALL TET
RECTOUT
# Page 1218
TESTLOOP BOF CLRGO
QUITFLAG
+3
STATEFLG
INTEXIT # STOP INTEGRATION
+3 SETPD LXA,2
10D
PBODY
VLOAD ABVAL
RCV
PUSH CLEAR # RC TO 10D
MIDFLAG
DSU* BMN # MIDFLAG=0 IF R G.T. RMP
RME,2
+3
SET
MIDFLAG
NORFINAL DLOAD DMP
10D
34D
SR1R DDV*
MUEARTH,2
SQRT DMP
.3D
SR3 SR4 # DT IS TRUNCATED TO A MULTIPLE
DLOAD SL
MPAC
15D # OF 128 CSECS.
PUSH BOV
MAXDT
BDSU BMN
DT/2MAX
MAXDT
DT/2COMP DLOAD DSU
TDEC
TET
RTB SL
SGNAGREE
8D
STORE DT/2 # B-19
BOV ABS
GETMAXDT
DSU BMN # IS TIME TO INTEG. TO GR THAN MAXTIME
12D
POOHCHK
USEMAXDT DLOAD SIGN
12D
DT/2
# Page 1219
STCALL DT/2
POOHCHK
MAXDT DLOAD PDDL # EXCHANGE DT/2MAX WITH COMPUTED MAX.
DT/2MAX
GOTO
DT/2COMP
GETMAXDT RTB
SIGNMPAC
STCALL DT/2
USEMAXDT
POOHCHK DLOAD ABS
DT/2
DSU BMN
DT/2MIN
A-PCHK
SLOAD BHIZ
MODREG
+3
GOTO
TIMESTEP
BON # WAS THIS CALL VIA CSM(LEM)PREC
PRECIFLG
TIMESTEP # YES
DLOAD DSU
DT/2
12D
BMN BOFCLR
A-PCHK
NEWIFLG
TIMESTEP
DLOAD DSU
TDEC
TET
BMN # NO BACKWARD INTEGRATION
INTEXIT
PDDL SR4
DT/2 # IS 4(DT) LS (TDEC - TET)
SR2R BDSU
BMN GOTO
INTEXIT
TIMESTEP
DT/2MIN 2DEC 3 B-20
DT/2MAX 2DEC 4000 E2 B-20
INTSTALL EXIT
CA RASFLAG
MASK INTBITAB # IS THIS STALL AREA FREE
EXTEND
BZF OKTOGRAB # YES
# Page 1220
CAF WAKESTAL
TC JOBSLEEP
INTWAKE0 EXIT
TCF INTWAKE1
INTWAKE CS RASFLAG # IS THIS INTSTALLED ROUTINE TO BE
MASK REINTBIT # RESTARTED
CCS A
TC INTWAKE1 # NO
INDEX FIXLOC
CA QPRET
TS TBASE2 # YES, DON'T RESTART WITH SOMEONE ELSE'S Q
TC PHASCHNG
OCT 04022
CA TBASE2
INDEX FIXLOC
TS QPRET
CAF REINTBIT
MASK RASFLAG
EXTEND
BZF GOBAC # DON'T INTWAKE IF WE CAME HERE VIA RESTART
INTWAKE1 CAF WAKESTAL
INHINT
TC JOBWAKE
CCS LOCCTR
TCF INTWAKE1
FORTYONE DEC 41
CS INTBITAB
MASK RASFLAG
TS RASFLAG # RELEASE STALL AREA
RELINT
TCF GOBAC
OKTOGRAB CAF INTFLBIT
INHINT
ADS RASFLAG
GOBAC TC INTPRET
RVQ
WAKESTAL CADR INTSTALL +1
INTBITAB OCT 20100
# Page 1221
# AVETOMID
#
# THIS ROUTINE PERFORMS THE TRANSITION FROM A THRUSTING PHASE TO THE COAST
# PHASE BY INITIALIZING THIS VEHICLE'S PERMANENT STATE VECTOR WITH THE
# VALUES LEFT BY THE AVERAGEG ROUTINE IN RN,VN,PIPTIME.
#
# BEFORE THIS IS DONE THE W-MATRIX, IF ITS VALID (OR WFLAG OR RENDWFLT IS
# SET) IS INTEGRATED FORWARD TO PIPTIME WITH THE PRE-THRUST STATE VECTOR.
#
# IN ADDITION, THE OTHER VEHICLE IS INTEGRATED (PERMANENT) TO PIPTIME.
#
# FINALLY TRKMKCNT IS ZEROED.
SETLOC INTINIT
BANK
COUNT* $$/INTIN
AVETOMID STQ BON
EGRESS
RENDWFLG
INT/W # W-MATRIX VALID, GO INTEGRATE IT
BON
ORBWFLAG
INT/W # W-MATRIX VALID, GO INTEGRATE IT.
OTHERS DLOAD CALL # GET SET FOR OTHER VEHICLE INTEGRATION
PIPTIME # DESIRED TIME
INTSTALL
SET CALL
VINTFLAG # CM
SETIFLGS # SETS UP NONE W-MAT. PERMANENT INTEG.
STCALL TDEC1
INTEGRV
AXT,2 CALL # NOW MOVE PROPERLY SCALE RN,UN AS WELL AS
2 # PIPTIME TO INTEGRATION ERASABLES.
INTSTALL
BON AXT,2
MOONTHIS
+2
0
VLOAD VSR*
RN
0,2
STORE RRECT
STODL RCV
PIPTIME
STOVL TET
VN
# Page 1222
VSR* CALL
0,2
MINIRECT # FINISH SETTING UP STATE VECTOR
RTB SSP
MOVATHIS # PUT TEMP STATE VECTOR INTO PERMANENT
TRKMKCNT
0
GOTO
FAZAB5
INT/W DLOAD CALL
PIPTIME # INTEGRATE W THRU BURN
INTSTALL
SET SET
DIM0FLAG # DO W-MATRIX
AVEMIDSW # SO WON'T CLOBBER RN,VN,PIPTIME
SET CLEAR
D6OR9FLG # 9X9 FOR LM
VINTFLAG # LM
STCALL TDEC1
INTEGRV
GOTO
OTHERS # NOW GO DO THE OTHER VEHICLE
# Page 1223
# MIDTOAV1
#
# THIS ROUTINE INTEGRATES (PRECISION) TO THE TIME SPECIFIED IN TDEC1.
# IF, AT THE END OF AN INTEGRATION TIME STEP, CURRENT TIME PLUS A DELTA
# TIME (SEE TIMEDELT.....BASED ON THE COMPUTATION TIME FOR ONE TIME STEP)
# IS GREATER THAN THE DESIRED TIME, ALARM 1703 IS SET AND THE INTEGRATION
# IS DONE TO THE CURRENT TIME.
# RETURN IS IN BASIC TO THE RETURN ADDRESS PLUS ONE.
#
# IF THE INTEGRATION IS FINISHED TO THE DESIRED TIME, RETURN IS IN BASIC
# TO THE RETURN ADDRESS.
#
# IN EITHER CASE, BEFORE RETURNING, THE EXTRAPOLATED STATE VECTOR IS TRANSFERRED
# FROM R,VATT TO R,VN1-PIPTIME1 IS SET TO THE FINISHING INTEGRATION
# TIME AND MPAC IS SET TO THE DELTA TIME --
# TAT MINUS CURRENT TIME
# MIDTOAV2
#
# THIS ROUTINE INTEGRATES THIS VEHICLE'S STATE VECTOR TO THE CURRENT TIME.
# NO INPUTS ARE REQUIRED OF THE CALLER. RETURN IS IN BASIC TO THE RETURN
# ADDRESS WITH THE ABOVE TRANSFERS TO R,VN1-PIPTIME1-AND MPAC DONE
EBANK= IRETURN1
MIDTOAV2 STQ CLRGO # INTEGRATE TO PRESENT TIME PLUS TIMEDELT
IRETURN1
MID1FLAG
ENTMID2
MIDTOAV1 STQ SET # INTEGRATE TO TDEC1
IRETURN1
MID1FLAG
RTB DAD # INITIAL CHECK, IS TDEC1 IN THE FUTURE
LOADTIME
TIMEDELT
BDSU BPL
TDEC1
ENTMID1 # Y5S
CALL
NOTIME # NO, SET ALARM, SWITCH TO MIDTOAV2
ENTMID2 RTB DAD
LOADTIME
TIMEDELT
STORE TDEC1
ENTMID1 CALL
INTSTALL
CLEAR CALL
# Page 1224
DIM0FLAG # NO W-MATRIX
THISVINT
CLEAR SET
INTYPFLG
MIDAVFLG # LET INTEG. KNOW THE CALL IS FOR MIDTOAV.
CALL
INTEGRV # GO INTEGRATE
CLEAR VLOAD
MIDAVFLG
RATT
STOVL RN1
VATT
STODL VN1
TAT
STORE PIPTIME1
SXA,2 SXA,1
RTX2
RTX1
EXIT
INHINT
EXTEND
DCS TIME2
DAS MPAC
TC TPAGREE
CA IRETURN1
TC BANKJUMP
CKMID2 BOF RTB
MID1FLAG
MID2
LOADTIME
DAD BDSU
TIMEDELT
TDEC
BPL CALL
TESTLOOP # YES
NOTIME
TIMEINC RTB DAD
LOADTIME
TIMEDELT
STCALL TDEC
TESTLOOP
MID2 DLOAD DSU
TDEC
TET
ABS DSU
3CSECS
# Page 1225
BMN GOTO
A-PCHK
TIMEINC
NOTIME CLEAR EXIT # TOO LATE
MID1FLAG
INCR IRETURN1 # SET ERROR EXIT (CALLOC +2)
TC ALARM # INSUFFICIENT TIME FOR INTEGRATION --
OCT 1703 # TIG WILL BE SLIPPED...
TC INTPRET
RVQ
3CSECS 2DEC 3
TIMEDELT 2DEC 2000
BANK 27
SETLOC UPDATE2
BANK
EBANK= INTWAKUQ
COUNT* $$/INTIN
INTWAKUQ = INTWAK1Q # TEMPORARY UNTIL NAME OF INTWAK1Q IS CHNG
INTWAKEU RELINT
EXTEND
QXCH INTWAKUQ # SAVE Q FOR RETURN
TC INTPRET
SLOAD BZE # IS THIS A CSM/LEM STATE VECTOR UPDATE
UPSVFLAG # REQUEST. IF NOT GO TO INTWAKUP.
INTWAKUP
VLOAD # MOVE PRECT(6) AND VRECT(6) INTO
RRECT # RCV(6) AND VCV(6) RESPECTIVELY.
STOVL RCV
VRECT # NOW GO TO `RECTIFY +13D' TO
CALL # STORE VRECT INTO VCV AND ZERO OUT
RECTIFY +13D # TDELTAV(6),TNUV(6),TC(2), AND XKEP(2)
SLOAD ABS # COMPARE ABSOLUTE VALUE OF `UPSVFLAG'
UPSVFLAG # TO `UPDATE MOON STATE VECTOR CODE'
DSU BZE # TO DETERMINE WHETHER THE STATE VECTOR TO
UPMNSVCD # BE UPDATED IS IN THE EARTH OR LUNAR
INTWAKEM # SPHERE OF INFLUENCE........
AXT,2 CLRGO # EARTH SPHERE OF INFLUENCE.
DEC 0
MOONFLAG
# Page 1226
INTWAKEC
INTWAKEM AXT,2 SET # LUNAR SPHERE OF INFLUENCE.
DEC 2
MOONFLAG
INTWAKEC SLOAD BMN # COMMON CODING AFTER X2 INITIALIZED AND
# MOONFLAG SET (OR CLEARED).
UPSVFLAG # IS THIS A REQUEST FOR A LEM OR CSM
INTWAKLM # STATE VECTOR UPDATE......
CALL # UPDATE CSM STATE VECTOR
ATOPCSM
CLEAR GOTO
ORBWFLAG
INTWAKEX
INTWAKLM CALL # UPDATE LM STATE VECTOR
ATOPLEM
INTWAKEX CLEAR
RENDWFLG
INTWAKUP SSP CALL # REMOVE `UPDATE STATE VECTOR INDICATOR'
UPSVFLAG
0
INTWAKE0 # RELEASE `GRAB' OF ORBIT INTEG.
EXIT
TC PHASCHNG
OCT 04026
TC INTWAKUQ
UPMNSVCD OCT 2
OCT 0
GRP2PC STQ EXIT
GRP2SVQ
TC PHASCHNG
OCT 04022
TC INTPRET
GOTO
GRP2SVQ
