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Proof page # 1205-1206

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Isha 2020-10-25 21:45:23 -04:00
parent 0c6136893e
commit 7c5678f9bb
1 changed files with 19 additions and 19 deletions
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38
Luminary099/INTEGRATION_INITIALIZATION.agc
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@ -40,11 +40,11 @@
# 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.
# 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 LM'S POSITION AND VELOCITY IN THE REFERENCE COORDINATE SYSTEM.
# 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.
#
@ -80,15 +80,15 @@
# SETS STATEFLG (THE NAVIGATION PROGRAMS P20, P22.)
#
# Page 1206
# APPENDIX B OF THE USERS' GUIDE LISTS THE STATE VECTOR QUANTITIES.
# 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
# (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 WHOULD ENSURE THAT IF PHASE CHANGING IS DONE
# 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.
#
@ -106,28 +106,28 @@
#
# 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 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
# EARTH MOON
# 29 27
# RRECTCSM(LEM) RECTIFIED POSITION VECTOR METERS 2 2
#
# 7 5
# 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