1175 lines
26 KiB
Plaintext
1175 lines
26 KiB
Plaintext
# Copyright: Public domain.
|
|
# Filename: INTEGRATION_INITIALIZATION.agc
|
|
# Purpose: Part of the source code for Colossus 2A, AKA Comanche 055.
|
|
# It is part of the source code for the Command Module's (CM)
|
|
# Apollo Guidance Computer (AGC), for Apollo 11.
|
|
# Assembler: yaYUL
|
|
# Contact: Ron Burkey <info@sandroid.org>.
|
|
# Website: www.ibiblio.org/apollo.
|
|
# Pages: 1309-1333
|
|
# Mod history: 2009-05-15 RSB Adapted from the Colossus249/ file of the
|
|
# same name, using Comanche055 page images.
|
|
# 2009-05-20 RSB Corrections: fixed an interpreter instruction,
|
|
# fixed a SETLOC.
|
|
# 2009-05-23 RSB In SETCOAST, corrected MOONTHIS to AMOONFLG.
|
|
#
|
|
# 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 055 of AGC program Comanche by NASA
|
|
# 2021113-051. 10:28 APR. 1, 1969
|
|
#
|
|
# This AGC program shall also be referred to as
|
|
# Colossus 2A
|
|
|
|
# Page 1309
|
|
# 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 OUT-
|
|
# SIDE 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 TO 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 LMS 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 CENTRAL 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 1310
|
|
# 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) SINCE 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 SHOULD 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 VECTORDEPENDS 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 AP-
|
|
# PENDIX 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 1311
|
|
# 29 27
|
|
# RCVCSM(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) - RDOT 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 ORIGEN 0 2
|
|
# (THIS, NOT MOONFLAG, SHOULD BE
|
|
# Page 1312
|
|
# 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 = DIMOFLAG = 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 1313
|
|
# 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 DIMOFLAG 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 DIMOFLAG=1.(STATEFLG IS
|
|
# L+2 RETURN ALWAYS RESET IN INTEGRATION AFTER
|
|
# IT IS 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 13/INTIN
|
|
|
|
STATEINT TC PHASCHNG
|
|
OCT 00052
|
|
CAF PRIO5
|
|
TC FINDVAC
|
|
EBANK= RRECTCSM
|
|
2CADR STATINT1
|
|
|
|
TC TASKOVER
|
|
STATINT1 TC INTPRET
|
|
BON RTB
|
|
QUITFLAG
|
|
NOINT # NO STATEINT IF V96
|
|
LOADTIME
|
|
# Page 1314
|
|
STORE TDEC1
|
|
CLEAR CALL
|
|
V96ONFLG
|
|
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 2
|
|
|
|
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
|
|
# Page 1315
|
|
CMOONFLG
|
|
SVDWN1
|
|
BON CLRGO
|
|
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
|
|
|
|
# Page 1316
|
|
# ATOPLEM TRANSFERS RRECT TO RRECT +41 TO RRECTLEM TO RRECTLEM +41
|
|
ATOPLEM STQ RTB
|
|
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
|
|
# Page 1317
|
|
STODL TET
|
|
5/8
|
|
CALL
|
|
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
|
|
OMEGMOON 2DEC* 2.66169947 E-8 B+23*
|
|
|
|
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 KEPLERS 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 KEPLERS 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
|
|
# Page 1318
|
|
#
|
|
# CALLING SEQUENCE
|
|
# L-X STORE TDEC1
|
|
# L CALL (STCALL TDEC1)
|
|
# 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
|
|
# Page 1319
|
|
INTSTALL
|
|
SXA,1 CLRGO
|
|
IRETURN
|
|
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
|
|
#
|
|
# Page 1320
|
|
# OUTPUT
|
|
# RATT AS
|
|
# VATT DEFINED
|
|
# TAT BEFORE
|
|
|
|
INTEGRV STQ
|
|
IRETURN
|
|
INTEGRV1 SET SET
|
|
RPQFLAG
|
|
NEWIFLG
|
|
INTEGRV2 SSP
|
|
QPRET
|
|
ALOADED
|
|
BON GOTO
|
|
VINTFLAG
|
|
PTOACSM
|
|
PTOALEM
|
|
SETLOC INTINIT1
|
|
BANK
|
|
ALOADED DLOAD
|
|
TDEC1
|
|
STORE TDEC
|
|
BOFF GOTO
|
|
INTYPFLG
|
|
TESTLOOP
|
|
RVCON
|
|
SETLOC INTINIT
|
|
BANK
|
|
A-PCHK BOF CALL
|
|
MIDFLAG
|
|
ANDOUT # DONT MAKE ORIGIN CHANGE CHECK
|
|
CHKSWTCH
|
|
BPL CALL
|
|
ANDOUT # NO ORIGIN CHANGE
|
|
ORIGCHNG # MAKE THE SWITCH
|
|
ANDOUT BOFCLR 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
|
|
# Page 1321
|
|
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
|
|
RRECT
|
|
PDVL PDDL*
|
|
VRECT
|
|
MUEARTH,2
|
|
PUSH AXT,1
|
|
DEC -10
|
|
BON AXT,1
|
|
MOONFLAG
|
|
+2
|
|
DEC -2
|
|
INTEXIT SETPD BOV
|
|
0
|
|
+1
|
|
CLEAR
|
|
MIDAVFLG
|
|
CLEAR CLEAR
|
|
AVEMIDSW # ALLOW UPDATE OF DOWNLINK STATE VECTOR
|
|
PRECIFLG
|
|
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
|
|
# Page 1322
|
|
TET
|
|
STCALL TET
|
|
RECTOUT
|
|
|
|
# Page 1323
|
|
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
|
|
P00HCHK
|
|
USEMAXDT DLOAD SIGN
|
|
12D
|
|
DT/2
|
|
# Page 1324
|
|
STCALL DT/2
|
|
P00HCHK
|
|
MAXDT DLOAD PDDL # EXCHANGE DT/2MAX WITH COMPUTED MAX.
|
|
DT/2MAX
|
|
GOTO
|
|
DT/2COMP
|
|
GETMAXDT RTB
|
|
SIGNMPAC
|
|
STCALL DT/2
|
|
USEMAXDT
|
|
P00HCHK 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 # NO
|
|
BMN GOTO
|
|
INTEXIT
|
|
TIMESTEP
|
|
DT/2MIN 2DEC 3 B-20
|
|
|
|
DT/2MAX 2DEC 4000 E2 B-20
|
|
|
|
INTSTALL EXIT
|
|
CAF ZERO
|
|
ALLSTALL TS L
|
|
CA RASFLAG
|
|
INDEX L
|
|
# Page 1325
|
|
MASK INTBITAB # IS THIS STALL AREA FREE
|
|
EXTEND
|
|
BZF OKTOGRAB # YES
|
|
INDEX L
|
|
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, DONT RESTART WITH SOMEONE ELSES Q
|
|
|
|
TC PHASCHNG
|
|
OCT 04022
|
|
|
|
CA TBASE2
|
|
INDEX FIXLOC
|
|
TS QPRET
|
|
|
|
CAF REINTBIT
|
|
MASK RASFLAG
|
|
EXTEND
|
|
BZF GOBAC # DONT INTWAKE IF WE CAME HERE VIA RESTART
|
|
|
|
INTWAKE1 CAF ZERO
|
|
WAKE TS STALTEM # INDEX OF ANY STALL USER
|
|
WAKE1 INDEX STALTEM
|
|
CAF WAKESTAL
|
|
INHINT
|
|
TC JOBWAKE
|
|
CCS LOCCTR
|
|
TCF WAKE1 # MAY BE MORE TO WAKE UP
|
|
FORTYONE DEC 41
|
|
INDEX STALTEM
|
|
CS INTBITAB
|
|
MASK RASFLAG
|
|
TS RASFLAG # RELEASE STALL AREA
|
|
RELINT
|
|
TCF GOBAC
|
|
OKTOGRAB INDEX L # NO, WAIT UNTIL AVAILABLE
|
|
CAF INTFLBIT
|
|
ADS RASFLAG
|
|
GOBAC TC INTPRET
|
|
RVQ
|
|
# Page 1326
|
|
ERASTAL1 EXIT
|
|
CAF ONE
|
|
TCF ALLSTALL
|
|
ERASTAL2 EXIT
|
|
CAF TWO
|
|
TCF ALLSTALL
|
|
ERASWAK1 CAF ONE
|
|
TCF WAKE
|
|
ERASWAK2 CAF TWO
|
|
TCF WAKE
|
|
WAKESTAL CADR INTSTALL +1
|
|
CADR ERASTAL1 +1
|
|
CADR ERASTAL2 +1
|
|
STALTEM EQUALS MPAC
|
|
INTBITAB OCT 20100
|
|
OCT 10040
|
|
OCT 04020
|
|
|
|
# Page 1327
|
|
# AVETOMID
|
|
#
|
|
# THIS ROUTINE PERFORMS THE TRANSITION FROM A THRUSTING PHASE TO THE COAST
|
|
# PHASE BY INITIALIZING THIS VEHICLES 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 (ORWFLAG 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 INTINIT2
|
|
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
|
|
|
|
SETCOAST AXT,2 CALL # NOW MOVE PROPERLY SCALED RN,VN AND
|
|
2 # PIPTIME TO INTEGRATION ERASABLES.
|
|
INTSTALL
|
|
BON AXT,2
|
|
AMOONFLG
|
|
+2
|
|
0
|
|
VLOAD VSR*
|
|
RN
|
|
0,2
|
|
STORE RRECT
|
|
STODL RCV
|
|
PIPTIME
|
|
STOVL TET
|
|
VN
|
|
VSR* CALL
|
|
0,2
|
|
MINIRECT # FINISH SETTING UP STATE VECTOR
|
|
RTB SSP
|
|
MOVATHIS # PUT TEMP STATE VECTOR INTO PERMANENT
|
|
TRKMKCNT
|
|
0
|
|
SET BON
|
|
CMOONFLG
|
|
# Page 1328
|
|
AMOONFLG
|
|
+3
|
|
CLEAR
|
|
CMOONFLG
|
|
|
|
BON DLOAD # NOW DO LM
|
|
SURFFLAG
|
|
FAZAB5 # NO COASTING LM
|
|
PIPTIME
|
|
STCALL TDEC1
|
|
SETIFLGS
|
|
CLEAR CALL
|
|
VINTFLAG
|
|
INTEGRV
|
|
GOTO
|
|
EGRESS
|
|
INT/W DLOAD CALL
|
|
PIPTIME # INTEGRATE W THRU BURN
|
|
INTSTALL
|
|
SET SET
|
|
DIM0FLAG # DO W-MATRIX
|
|
AVEMIDSW # SO WONT CLOBBER RN,VN,PIPTIME
|
|
CLEAR SET
|
|
D6OR9FLG
|
|
VINTFLAG
|
|
STCALL TDEC1
|
|
INTEGRV
|
|
GOTO
|
|
SETCOAST
|
|
|
|
# Page 1329
|
|
# 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 COMPUTATUON TIME FOR ONE TIME STEP)
|
|
# IS GREATER THAN THE DESIRED TIME, ALARM 1703 IS SET AND THE INTEGRATION
|
|
# IS DONE AS IT IS FOR MIDTOAV2.
|
|
# 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 TRAN
|
|
# FERRED FROM R,VATT TO R,VN1-PIPTIME1 IS SET TO THE FINISHING INTEGRA-
|
|
# TION TIME AND MPAC IS SET TO THE DELTA TIME---
|
|
# TAT MINUS CURRENT TIME.
|
|
|
|
# MIDTOAV2
|
|
#
|
|
# THIS ROUTINE INTEGRATES THE CSM STATE VECTOR TO CURRENT TIME PLUS
|
|
# INCREMENTS OF TIMEDELT SUCH THAT THE DIFFERENCE BETWEEN CURRENT TIME
|
|
# AND THE STATE VECTOR TIME AT THE END OF THE LAST STEP IS AT LEAST 5.6
|
|
# SECS.
|
|
# 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
|
|
|
|
SETLOC INTINIT
|
|
BANK
|
|
EBANK= IRETURN1
|
|
MIDTOAV2 STQ CALL
|
|
IRETURN1
|
|
INTSTALL
|
|
DLOAD CLEAR
|
|
TIMEDELT
|
|
MID1FLAG
|
|
STCALL T-TO-ADD
|
|
ENTMID2
|
|
|
|
MIDTOAV1 STQ CALL
|
|
IRETURN1
|
|
INTSTALL
|
|
SET RTB
|
|
MID1FLAG
|
|
LOADTIME
|
|
DAD BDSU # INITIAL CHECK.IS TDEC1 IN THE FUTURE.
|
|
TIMEDELT
|
|
TDEC1
|
|
BPL CALL
|
|
ENTMID1
|
|
# Page 1330
|
|
NOTIME # NO SET ALARM.SWITCH TO MIDTOAV2
|
|
|
|
ENTMID2 RTB DAD
|
|
LOADTIME
|
|
T-TO-ADD
|
|
STORE TDEC1
|
|
|
|
ENTMID1 CLEAR CALL
|
|
DIM0FLAG # NO W-MATRIX
|
|
THISVINT
|
|
CLEAR SET
|
|
INTYPFLG
|
|
MIDAVFLG # LET INTEG. KNOW THE CALL IS FOR MIDTOAV.
|
|
CALL
|
|
INTEGRV # GO INTEGRATE
|
|
SXA,2 SXA,1
|
|
RTX2
|
|
RTX1
|
|
CLEAR SLOAD
|
|
AMOONFLG
|
|
RTX2
|
|
BZE SET
|
|
+2
|
|
AMOONFLG
|
|
VLOAD
|
|
RATT
|
|
STOVL RN1
|
|
VATT
|
|
STODL VN1
|
|
TAT
|
|
STORE PIPTIME1
|
|
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
|
|
# Page 1331
|
|
NOTIME
|
|
|
|
TIMEINC RTB DAD
|
|
LOADTIME
|
|
T-TO-ADD
|
|
STCALL TDEC
|
|
TESTLOOP
|
|
|
|
MID2 DLOAD DSU
|
|
TDEC
|
|
TET
|
|
ABS DSU
|
|
3CSECS
|
|
BPL
|
|
TIMEINC
|
|
|
|
RTB BDSU # SEE IF 5.6 SECS. AVAILABLE TO CALLER
|
|
LOADTIME
|
|
TET
|
|
DSU BPL
|
|
5.6SECS
|
|
A-PCHK # YES,GET OUT.
|
|
|
|
DLOAD DAD # NO,ADD TIMEDELT TO T-TO-ADD AND TRY
|
|
T-TO-ADD # AGAIN.
|
|
TIMEDELT
|
|
STCALL T-TO-ADD
|
|
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
|
|
DLOAD
|
|
TIMEDELT
|
|
STORE T-TO-ADD
|
|
RVQ
|
|
|
|
3CSECS 2DEC 3
|
|
|
|
TIMEDELT 2DEC 1250
|
|
|
|
5.6SECS 2DEC 560
|
|
|
|
BANK 27
|
|
SETLOC UPDATE2
|
|
BANK
|
|
EBANK= INTWAKUQ
|
|
|
|
# Page 1332
|
|
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 RRECT(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
|
|
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:
|
|
# Page 1333
|
|
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
|
|
|