From 90585c1955ac68cb49b3afefe3a0bc894f197c7b Mon Sep 17 00:00:00 2001 From: Isha Date: Mon, 26 Oct 2020 13:43:34 -0400 Subject: [PATCH] Proofed page # 1205-1215 --- Luminary099/INTEGRATION_INITIALIZATION.agc | 152 ++++++++++----------- 1 file changed, 75 insertions(+), 77 deletions(-) diff --git a/Luminary099/INTEGRATION_INITIALIZATION.agc b/Luminary099/INTEGRATION_INITIALIZATION.agc index d466ced..956d867 100644 --- a/Luminary099/INTEGRATION_INITIALIZATION.agc +++ b/Luminary099/INTEGRATION_INITIALIZATION.agc @@ -34,8 +34,8 @@ # 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. +# 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 @@ -109,57 +109,57 @@ # FOR INTEGRVS, THE RCV,VCV,TET OF 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 +# EARTH MOON +# 29 27 +# RRECTCSM(LEM) - RECTIFIED POSITION VECTOR METERS 2 2 # -# 7 5 -# VRECTCSM(LEM) RECTIFIED VELOCITY VECTOR M/CSEC 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. +# 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 +# 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 +# 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 +# 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 +# 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 +# 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 +# 1/2 17 16 +# XKEPCSM(LEM) - ROOT OF KEPLERS 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 +# 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 +# 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 +#AFTER EVERY CALL TO INTEGRATION # EARTH MOON # 29 29 # 0D RATT POSITION METERS 2 2 @@ -182,7 +182,7 @@ # X1 MUTABLE ENTRY -2 -10D # # X2 COORDINT -# X2 COORDINATE SYSTEM ORIGIN 0 2 +# X2 COORDINATE SYSTEM ORIGEN 0 2 # (THIS, NOT MOONFLAG, SHOULD BE # Page 1208 # USED TO DETERMINE ORIGIN.) @@ -196,7 +196,7 @@ # ------------------------------------- # # A) PRECISION ORBITAL INTEGRATION. CSMPREC, LEMPREC ENTRANCES -# L-X STORE TIME TO 96T5791T5 T 95 PUS L9ST (T4531) +# L-X STORE TIME TO 95T5791T5 T 95 PUS L9ST (T4531) # L CALL # L+1 CSMPREC (OR LEMPREC) # L+2 RETURN @@ -205,7 +205,7 @@ # 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 +# 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 @@ -213,24 +213,24 @@ # INPUT/OUTPUT # SAME AS PRECISION INTEGRATION, EXCEPT RQVV NOT SET # C) INTEGRATE GIVEN STATE VECTOR. INTEGRVS ENTRANCE -# CALL +# CALL # INTSTALL -# VLOAD +# VLOAD # POSITION VECTOR -# STOVL RCV +# STOVL RCV # VELOCITY VECTOR -# STODL VCV +# STODL VCV # TIME STATE VECTOR VALID -# STODL TET +# STODL TET # FINAL RADIUS -# STORE RFINAL -# SET(CLEAR) SET(CLEAR) -# INTYPFLAG -# MOONFLAG -# SET(CLEAR) DLOAD -# DESIRED TIME -# STCALL TDEC1 -# INTEGRVS +# 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 @@ -249,7 +249,7 @@ # 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-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 @@ -257,9 +257,9 @@ # L+3 STCALL RFINAL # L+4 INTEGRV # L CALL NORMAL USE -- WILL UPDATE STATE -# L+1 INTEGRV VECTOR IF DIM0FLAG=1. (STATEFLG IS +# L+1 INTEGRV VECTOR IF DIMOFLAG=1. (STATEFLG IS # L+2 RETURN ALWAYS RESET IN INTEGRATION AFTER -# IT USED.) +# IT IS USED.) # INPUT # TDEC1 (PD 32D) TIME TO INTEGRATE TO CSEC B-28 # OUTPUT @@ -282,7 +282,7 @@ STATEINT TC PHASCHNG TC TASKOVER STATINT1 TC INTPRET BON RTB - QUITFLAG # KILL INTEGRATION UNTIL NEXT P00. + QUITFLAG # KILL INTEGRATION UNTIL NEXT POO. NOINT LOADTIME STORE TDEC1 @@ -311,7 +311,7 @@ SETIFLGS SET CLEAR STATEFLG INTYPFLG CLEAR CLEAR - DIM0FLAG + DIMOFLAG D6OR9FLG RVQ NOINT EXIT @@ -350,7 +350,7 @@ MOVEACSM TC SETBANK TS RRECTCSM CCS DIFEQCNT # IS TRANSFER COMPLETE TCF MOVEACSM +1 # NO-LOOP - TC DANZIG # COMPLETE -- RETURN + TC DANZIG # COMPLETE- RETURN # PTOACSM TRANSFERS RRECTCSM TO RRECTCSM +41 TO RRECT TO RRECT +41 # @@ -467,26 +467,25 @@ 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. +# 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. +# 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 KEPLER'S EQUATION. +# 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: +# 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 +# DIMOFLAG CLEAR CLEAR CLEAR CLEAR # # CALLING SEQUENCE # L-X STORE TDEC1 -# L CALL (STCALL TDEC1) +# L CALL (STCALL TDEC1) # Page 1214 -# L+1 CSMPREC (CSMCONIC, LEMPREC, LEMCONIC) +# L+1 CSMPREC (CSMCONIC, LEMPREC, LEMCONIC) # # NORMAL EXIT TO L+2 # @@ -495,10 +494,10 @@ INTBANK BBCON INTEGRV # PRECOUT FOR CSMPREC AND LEMPREC # CONICOUT FOR CSMCONIC AND LEMCONIC # -# OUTPUT -- SEE PAGE 2 OF THIS LOG SECTION +# OUTPUT - SEE PAGE 2 OF THIS LOG SECTION # # INPUT -# TDEC1 TIME TO INTEGRATE TO. CSECS B-28 +# TDEC1 TIME TO INTEGRATE TO. CSECS B-28 CSMPREC STQ CALL X1 @@ -509,7 +508,7 @@ CSMPREC STQ CALL IFLAGP SET CLEAR PRECIFLG - DIM0FLAG + DIMOFLAG CLRGO INTYPFLG INTEGRV1 @@ -528,7 +527,7 @@ CSMCONIC STQ CALL IRETURN VINTFLAG IFLAGC CLEAR SETGO - DIM0FLAG + DIMOFLAG INTYPFLG INTEGRV1 LEMCONIC STQ CALL @@ -556,7 +555,7 @@ INTEGRVS SET SSP STCALL TNUV RECTIFY CLEAR SET - DIM0FLAG + DIMOFLAG NEWIFLG SETGO RPQFLAG @@ -566,22 +565,21 @@ INTEGRVS SET SSP # 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. +# 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 +# DIMOFLAG # 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. +# AND DIMOFLAG IS CLEAR. # L CALL # L+1 INTEGRV # @@ -591,7 +589,7 @@ INTEGRVS SET SSP # # OUTPUT # RATT AS -# VATT DEFINED +# VATT DEFINED # Page 1216 # TAT BEFORE