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Proofed page # 1205-1215
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@ -34,8 +34,8 @@
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# FROM A USER'S POINT OF VIEW, ORBITAL INTEGRATION IS ESSENTIALLY THE SAME AS THE 278 INTEGRATION
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# PROGRAM. THE SAME ENTRANCES TO THE PROGRAM WILL BE MAINTAINED, THE SAME STALLING ROUTINE WILL BE USED AND
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# OUTPUT WILL STILL BE VIA THE PUSHLIST. THE PRIMARY DIFFERENCES TO A USER INVOLVE THE ADDED CAPABILITY OF
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# TERMINATING INTEGRATION AT A SPECIFIC FINAL RADIUS AND THE DIFFERENCE IN STATE VECTOR SCALING INSIDE AND OUTSIDE
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# THE LUNAR SPHERE OF INFLUENCE.
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# TERMINATING INTEGRATION AT A SPECIFIC FINAL RADIUS AND THE DIFFERENCE IN STATE VECTOR SCALING INSIDE AND OUT-
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# SIDE THE LUNAR SPHERE OF INFLUENCE.
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#
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# IN ORDER TO MAKE THE CSM(LEM)PREC AND CSM(LEM)CONIC ENTRANCES SIMILAR TO FLIGHT 278, THE INTEGRATION PROGRAM
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# WILL ITSELF SET THE FINAL RADIUS (RFINAL) TO 0 SO THAT REACHING THE DESIRED TIME ONLY WILL TERMINATE
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@ -109,57 +109,57 @@
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# FOR INTEGRVS, THE RCV,VCV,TET OF THE TEMPORARY STATE VECTOR MUST BE SET, PLUS MOONFLAG AND MIDFLAG
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#
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# FOR SIMULATION THE FOLLOWING QUANTITIES MUST BE PRESET ---
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# EARTH MOON
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# 29 27
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# RRECTCSM(LEM) RECTIFIED POSITION VECTOR METERS 2 2
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# EARTH MOON
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# 29 27
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# RRECTCSM(LEM) - RECTIFIED POSITION VECTOR METERS 2 2
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#
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# 7 5
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# VRECTCSM(LEM) RECTIFIED VELOCITY VECTOR M/CSEC 2 2
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# 7 5
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# VRECTCSM(LEM) - RECTIFIED VELOCITY VECTOR M/CSEC 2 2
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#
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# 28 28
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# TETCSM(LEM) TIME STATE VECTOR IS VALID CSEC 2 2
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# CUSTOMARILY 0, BUT NOTE LUNAR
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# ORBIT DEPENDENCE ON REAL TIME.
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# 28 28
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# TETCSM(LEM) - TIME STATE VECTOR IS VALID CSEC 2 2
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# CUSTOMARILY 0, BUT NOTE LUNAR
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# ORBIT DEPENDENCE ON REAL TIME.
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#
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# 22 18
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# DELTAVCSM(LEM) POSITION DEVIATION METERS 2 2
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# 0 IF TCCSM(LEM) = 0
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# 22 18
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# DELTAVCSM(LEM) - POSITION DEVIATION METERS 2 2
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# 0 IF TCCSM(LEM) = 0
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#
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# 3 -1
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# NUVCSM(LEM) VELOCITY DEVIATION M/CSEC 2 2
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# 0 IF TCCSM(LEM) = 0
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# 3 -1
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# NUVCSM(LEM) - VELOCITY DEVIATION M/CSEC 2 2
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# 0 IF TCCSM(LEM) = 0
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# Page 1207
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# 29 27
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# RCVSM(LEM) CONIC POSITION METERS 2 2
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# EQUALS RRECTCSM(LEM) IF
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# TCCSM(LEM) = 0
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# 29 27
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# RCVCSM(LEM) - CONIC POSITION METERS 2 2
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# EQUALS RRECTCSM(LEM) IF
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# TCCSM(LEM) = 0
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#
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# 7 5
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# VCVCSM(LEM) CONIC VELOCITY M/CSEC 2 2
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# EQUALS VRECTCSM(LEM) IF
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# TCCSM(LEM) = 0
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# 7 5
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# VCVCSM(LEM) - CONIC VELOCITY M/CSEC 2 2
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# EQUALS VRECTCSM(LEM) IF
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# TCCSM(LEM) = 0
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#
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# 28 28
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# TCCSM(LEM) TIME SINCE RECTIFICATION CSECS 2 2
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# CUSTOMARILY 0
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# 28 28
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# TCCSM(LEM) - TIME SINCE RECTIFICATION CSECS 2 2
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# CUSTOMARILY 0
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#
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# 1/2 17 16
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# XKEPCSM(LEM) ROOT OF KEPLER'S EQUATION M 2 2
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# 0 IF TCCSM(LEM) = 0
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# 1/2 17 16
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# XKEPCSM(LEM) - ROOT OF KEPLERS EQUATION M 2 2
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# 0 IF TCCSM(LEM) = 0
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#
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# CMOONFLG PERMANENT FLAGS CORRESPONDING 0 0
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# CMIDFLAG TO MOONFLAG AND MIDFLAG 0,1 0,1
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# LMOONFLG C = CSM, L = LM 0 0
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# LMIDFLG 0,1 0,1
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# CMOONFLG - PERMANENT FLAGS CORRESPONDING 0 0
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# CMIDFLAG TO MOONFLAG AND MIDFLAG 0,1 0,1
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# LMOONFLG C = CSM, L = LM 0 0
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# LMIDFLG 0,1 0,1
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#
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# SURFFLAG LUNAR SURFACE FLAG 0,1 0,1
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# SURFFLAG - LUNAR SURFACE FLAG 0,1 0,1
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#
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# IN ADDITION, IF (L)CMIDFLAG IS SET, THE INITIAL INPUT VALUES FOR LUNAR
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# SOLAR EPHEMERIDES SUBROUTINE AND PLANETARY INERTIAL ORIENTATION SUB-
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# ROUTINE MUST BE PRESET.
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#
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# OUTPUT
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# AFTER EVERY CALL TO INTEGRATION
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#AFTER EVERY CALL TO INTEGRATION
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# EARTH MOON
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# 29 29
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# 0D RATT POSITION METERS 2 2
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@ -182,7 +182,7 @@
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# X1 MUTABLE ENTRY -2 -10D
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#
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# X2 COORDINT
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# X2 COORDINATE SYSTEM ORIGIN 0 2
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# X2 COORDINATE SYSTEM ORIGEN 0 2
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# (THIS, NOT MOONFLAG, SHOULD BE
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# Page 1208
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# USED TO DETERMINE ORIGIN.)
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@ -196,7 +196,7 @@
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# -------------------------------------
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#
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# A) PRECISION ORBITAL INTEGRATION. CSMPREC, LEMPREC ENTRANCES
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# L-X STORE TIME TO 96T5791T5 T 95 PUS L9ST (T4531)
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# L-X STORE TIME TO 95T5791T5 T 95 PUS L9ST (T4531)
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# L CALL
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# L+1 CSMPREC (OR LEMPREC)
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# L+2 RETURN
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@ -205,7 +205,7 @@
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# OUTPUT
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# THE DATA LISTED IN SECTION 3.0 PLUS
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# RQVV POSITION VECTOR OF VEHICLE WITH RESPECT TO SECONDARY
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# BODY... METERS B-29 ONLY IF MIDFLAG = DIM0FLAG = 1
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# BODY... METERS B-29 ONLY IF MIDFLAG = DIMOFLAG = 1
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# B) CONIC INTEGRATION. CSMCONIC, LEMCONIC ENTRANCES
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# L-X STORE TIME IN PUSH LIST (TDEC1)
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# L CALL
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@ -213,24 +213,24 @@
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# INPUT/OUTPUT
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# SAME AS PRECISION INTEGRATION, EXCEPT RQVV NOT SET
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# C) INTEGRATE GIVEN STATE VECTOR. INTEGRVS ENTRANCE
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# CALL
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# CALL
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# INTSTALL
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# VLOAD
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# VLOAD
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# POSITION VECTOR
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# STOVL RCV
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# STOVL RCV
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# VELOCITY VECTOR
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# STODL VCV
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# STODL VCV
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# TIME STATE VECTOR VALID
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# STODL TET
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# STODL TET
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# FINAL RADIUS
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# STORE RFINAL
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# SET(CLEAR) SET(CLEAR)
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# INTYPFLAG
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# MOONFLAG
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# SET(CLEAR) DLOAD
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# DESIRED TIME
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# STCALL TDEC1
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# INTEGRVS
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# STORE RFINAL
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# SET(CLEAR) SET(CLEAR)
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# INTYPFLAG
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# MOONFLAG
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# SET(CLEAR) DLOAD
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# DESIRED TIME
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# STCALL TDEC1
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# INTEGRVS
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# INPUT
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# RCV POSITION VECTOR METERS
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# VCV VELOCITY VECTOR M/CSEC
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@ -249,7 +249,7 @@
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# L-5 VINTFLAG 1=CSM, 0=LM
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# L-4 INTYPFLAG 1=CONIC, 0=PRECISION
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# L-3 SET(CLEAR) SET(CLEAR)
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# L-2 DIM0FLAG 1=W-MATRIX, 0=NO W-MATRIX
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# L-2 DIMOFLAG 1=W-MATRIX, 0=NO W-MATRIX
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# L-1 D6OR9FLG 1=9X9, 0=6X6
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# L SET DLOAD
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# L+1 STATEFLG DESIRE PERMANENT UPDATE
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# L+3 STCALL RFINAL
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# L+4 INTEGRV
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# L CALL NORMAL USE -- WILL UPDATE STATE
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# L+1 INTEGRV VECTOR IF DIM0FLAG=1. (STATEFLG IS
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# L+1 INTEGRV VECTOR IF DIMOFLAG=1. (STATEFLG IS
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# L+2 RETURN ALWAYS RESET IN INTEGRATION AFTER
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# IT USED.)
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# IT IS USED.)
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# INPUT
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# TDEC1 (PD 32D) TIME TO INTEGRATE TO CSEC B-28
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# OUTPUT
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@ -282,7 +282,7 @@ STATEINT TC PHASCHNG
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TC TASKOVER
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STATINT1 TC INTPRET
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BON RTB
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QUITFLAG # KILL INTEGRATION UNTIL NEXT P00.
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QUITFLAG # KILL INTEGRATION UNTIL NEXT POO.
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NOINT
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LOADTIME
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STORE TDEC1
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@ -311,7 +311,7 @@ SETIFLGS SET CLEAR
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STATEFLG
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INTYPFLG
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CLEAR CLEAR
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DIM0FLAG
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DIMOFLAG
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D6OR9FLG
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RVQ
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NOINT EXIT
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@ -350,7 +350,7 @@ MOVEACSM TC SETBANK
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TS RRECTCSM
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CCS DIFEQCNT # IS TRANSFER COMPLETE
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TCF MOVEACSM +1 # NO-LOOP
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TC DANZIG # COMPLETE -- RETURN
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TC DANZIG # COMPLETE- RETURN
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# PTOACSM TRANSFERS RRECTCSM TO RRECTCSM +41 TO RRECT TO RRECT +41
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#
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@ -467,26 +467,25 @@ INTBANK BBCON INTEGRV
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# SPECIAL PURPOSE ENTRIES TO ORBITAL INTEGRATION. THESE ROUTINES PROVIDE ENTRANCES TO INTEGRATION WITH
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# APPROPRIATE SWITCHES SET OR CLEARED FOR THE DESIRED INTEGRATION.
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#
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# CSMPREC AND LEMPREC PERFORM ORBIT INTEGRATION BY THE ENCKE METHOD TO THE TIME INDICATED IN TDEC1.
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# CSMPREC AND LEMPREC PERFORM ORBIT INTEGRATION BY THE ENCKE METHOD TO THE TIME INDICATED IN TDEC1
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# ACCELERATIONS DUE TO OBLATENESS ARE INCLUDED. NO W-MATRIX INT. IS DONE.
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# THE PERMANENT STATE VECTOR IS NOT UPDATED.
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#
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# CSMCONIC AND LEMCONIC PERFORM ORBIT INTEG. BY KEPLER'S METHOD TO THE TIME INDICATED IN TDEC1.
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# CSMCONIC AND LEMCONIC PERFORM ORBIT INTEG. BY KEPLERS METHOD TO THE TIME INDICATED IN TDEC1
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# NO DISTURBING ACCELERATIONS ARE INCLUDED. IN THE PROGRAM FLOW THE GIVEN
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# STATE VECTOR IS RECTIFIED BEFORE SOLUTION OF KEPLER'S EQUATION.
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# STATE VECTOR IS RECTIFIED BEFORE SOLUTION OF KEPLERS EQUATION.
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#
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# THE ROUTINES ASSUME THAT THE CSM (LEM) STATE VECTOR IN P-MEM IS VALID.
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# SWITCHES SET PRIOR TO ENTRY TO THE MAIN INTEG. PROG ARE AS FOLLOWS:
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# SWITCHES SET PRIOR TO ENTRY TO THE MAIN INTEG. PROG ARE AS FOLLOWS:
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# CSMPREC CSMCONIC LEMPREC LEMCONIC
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# VINTFLAG SET SET CLEAR CLEAR
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# INTYPFLG CLEAR SET CLEAR SET
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# DIM0FLAG CLEAR CLEAR CLEAR CLEAR
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# DIMOFLAG CLEAR CLEAR CLEAR CLEAR
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#
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# CALLING SEQUENCE
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# L-X STORE TDEC1
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# L CALL (STCALL TDEC1)
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# L CALL (STCALL TDEC1)
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# Page 1214
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# L+1 CSMPREC (CSMCONIC, LEMPREC, LEMCONIC)
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# L+1 CSMPREC (CSMCONIC, LEMPREC, LEMCONIC)
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#
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# NORMAL EXIT TO L+2
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#
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# PRECOUT FOR CSMPREC AND LEMPREC
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# CONICOUT FOR CSMCONIC AND LEMCONIC
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#
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# OUTPUT -- SEE PAGE 2 OF THIS LOG SECTION
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# OUTPUT - SEE PAGE 2 OF THIS LOG SECTION
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#
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# INPUT
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# TDEC1 TIME TO INTEGRATE TO. CSECS B-28
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# TDEC1 TIME TO INTEGRATE TO. CSECS B-28
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CSMPREC STQ CALL
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X1
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@ -509,7 +508,7 @@ CSMPREC STQ CALL
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IFLAGP SET CLEAR
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PRECIFLG
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DIM0FLAG
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DIMOFLAG
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CLRGO
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INTYPFLG
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INTEGRV1
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IRETURN
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VINTFLAG
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IFLAGC CLEAR SETGO
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DIM0FLAG
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DIMOFLAG
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INTYPFLG
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INTEGRV1
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LEMCONIC STQ CALL
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@ -556,7 +555,7 @@ INTEGRVS SET SSP
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STCALL TNUV
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RECTIFY
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CLEAR SET
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DIM0FLAG
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DIMOFLAG
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NEWIFLG
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SETGO
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RPQFLAG
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# NORMALLY THE NAVIGATION PROGRAM, TO SET THE INTEG. FLAGS. THE ROUTINE
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# IS ENTERED AT INTEGRV1 BY CSMPREC ET AL. AND AT ALOADED BY INTEGRVS.
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# THE ROUTINE SETS UP A-MEMORY IF ENTERED AT INTEGRV,1 AND SETS THE INTEG.
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# PROGRAM FOR PRECISION OR CONIC.
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# PROGRAM FOR PRECISION OR CONIC
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#
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# THE CALLER MUST FIRST CALL INTSTALL TO CHECK IF INTEG. IS IN USE BEFORE
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# SETTING ANY FLAGS.
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#
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# THE FLAGS WHICH SHOULD BE SET OR CLEARED ARE
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# VINTFLAG (IGNORED WHEN ENTERED FROM INTEGRVS)
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# INTYPFLG
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# DIM0FLAG
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# DIMOFLAG
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# D6OR9FLG
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#
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# CALLING SEQUENCE
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# L-X CALL
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# L-Y INTSTALL
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# L-1 SET OR CLEAR ALL FOUR FLAGS. ALSO CAN SET STATEFLG IF DESIRED
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# AND DIM0FLAG IS CLEAR.
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# AND DIMOFLAG IS CLEAR.
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# L CALL
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# L+1 INTEGRV
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#
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#
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# OUTPUT
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# RATT AS
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# VATT DEFINED
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# VATT DEFINED
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# Page 1216
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# TAT BEFORE
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