diff --git a/Comanche055/INTEGRATION_INITIALIZATION.agc b/Comanche055/INTEGRATION_INITIALIZATION.agc index 9c96681..3a6d0aa 100644 --- a/Comanche055/INTEGRATION_INITIALIZATION.agc +++ b/Comanche055/INTEGRATION_INITIALIZATION.agc @@ -37,29 +37,29 @@ # 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 # 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. # # 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 +# 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 -- +# 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 @@ -83,23 +83,23 @@ # SETS STATEFLG (THE NAVIGATION PROGRAMS P20, P22.) # # Page 1310 -# 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. # # 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 +# 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. @@ -107,85 +107,81 @@ # 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 +# 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 +# RRECTCSM(LEM) - RECTIFIED POSITION VECTOR METERS 2 2 # # 7 5 -# VRECTCSM(LEM) RECTIFIED VELOCITY VECTOR M/CSEC 2 2 +# VRECTCSM(LEM) - RECTIFIED VELOCITY VECTOR M/CSEC 2 2 # # 28 28 -# TETCSM(LEM) TIME STATE VECTOR IS VALID CSEC 2 2 +# 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 +# DELTAVCSM(LEM) - POSITION DEVIATION METERS 2 2 # 0 IF TCCSM(LEM) = 0 # # 3 -1 -# NUVCSM(LEM) VELOCITY DEVIATION M/CSEC 2 2 +# NUVCSM(LEM) - VELOCITY DEVIATION M/CSEC 2 2 # 0 IF TCCSM(LEM) = 0 # Page 1311 # 29 27 -# RCVSM(LEM) CONIC POSITION METERS 2 2 +# RCVCSM(LEM) - CONIC POSITION METERS 2 2 # EQUALS RRECTCSM(LEM) IF # TCCSM(LEM) = 0 # # 7 5 -# VCVCSM(LEM) CONIC VELOCITY M/CSEC 2 2 +# 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 +# TCCSM(LEM) - TIME SINCE RECTIFICATION CSECS 2 2 # CUSTOMARILY 0 # # 1/2 17 16 -# XKEPCSM(LEM) RDOT OF KEPLER'S EQUATION M 2 2 +# XKEPCSM(LEM) - RDOT OF KEPLER'S EQUATION M 2 2 # 0 IF TCCSM(LEM) = 0 # -# CMOONFLG PERMANENT FLAGS CORRESPONDING 0 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 +# 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 -# # 7 7 # 6D VATT VELOCITY M/CSEC 2 2 -# # 28 28 -# 12D TAT TIME 2 2 -# +# 12D TAT TIME 2 2 # 29 27 -# 14D RATT1 POSITION METERS 2 2 -# +# 14D RATT1 POSITION METERS 2 2 # 7 5 -# 20D VATT1 VELOCITY M/CSEC 2 2 -# +# 20D VATT1 VELOCITY M/CSEC 2 2 # 3 2 36 30 -# 26D MU(P) MU M /CS 2 2 +# 26D MU(P) MU M /CS 2 2 # -# X1 MUTABLE ENTRY -2 -10D +# X1 MUTABLE ENTRY -2 -10D # -# X2 COORDINT -# X2 COORDINATE SYSTEM ORIGIN 0 2 +# X2 COORDINT +# X2 COORDINATE SYSTEM ORIGEN 0 2 # (THIS, NOT MOONFLAG, SHOULD BE # Page 1312 # USED TO DETERMINE ORIGIN.) @@ -198,17 +194,17 @@ # 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) +# 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 3.2 PLUS +# 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 @@ -237,32 +233,32 @@ # INPUT # RCV POSITION VECTOR METERS # VCV VELOCITY VECTOR M/CSEC -# TET TIME OF STATE VECTOR (MAY = 0) CSEC B-28 +# 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) +# 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-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+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 CALL NORMAL USE-- WILL UPDATE STATE +# 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 @@ -356,7 +352,7 @@ 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 # @@ -475,15 +471,15 @@ 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 @@ -491,21 +487,22 @@ INTBANK BBCON INTEGRV # Page 1318 # # CALLING SEQUENCE -# L-X STORE TDEC1 +# 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 +# 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 @@ -569,21 +566,19 @@ INTEGRVS SET SSP 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. +# 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 @@ -591,7 +586,6 @@ INTEGRVS SET SSP # AND DIM0FLAG IS CLEAR. # L CALL # L+1 INTEGRV -# # INITIALIZATION # FLAGS AS ABOVE # STORE TIME TO INTEGRATE TO IN TDEC1 @@ -627,7 +621,7 @@ ALOADED DLOAD BANK A-PCHK BOF CALL MIDFLAG - ANDOUT # DON'T MAKE ORIGIN CHANGE CHECK + ANDOUT # DONT MAKE ORIGIN CHANGE CHECK CHKSWTCH BPL CALL ANDOUT # NO ORIGIN CHANGE @@ -728,7 +722,7 @@ NORFINAL DLOAD DMP MUEARTH,2 SQRT DMP .3D - SR3 SR4 # DT IS TRUNCATED TO A MULTIPLE + SR3 SR4 # DT IS TRUNCATED TO A MULTIPLE DLOAD SL MPAC 15D # OF 128 CSECS. @@ -789,8 +783,8 @@ P00HCHK DLOAD ABS BMN # NO BACKWARD INTEGRATION INTEXIT PDDL SR4 - DT/2 # IS 4(DT) LS (TDEC - TET) - SR2R BDSU + DT/2 # IS 4(DT) LS(TDEC - TET) + SR2R BDSU # NO BMN GOTO INTEXIT TIMESTEP @@ -820,7 +814,7 @@ INTWAKE CS RASFLAG # IS THIS INTSTALLED ROUTINE TO BE INDEX FIXLOC CA QPRET - TS TBASE2 # YES, DON'T RESTART WITH SOMEONE ELSE'S Q + TS TBASE2 # YES, DONT RESTART WITH SOMEONE ELSES Q TC PHASCHNG OCT 04022 @@ -832,7 +826,7 @@ INTWAKE CS RASFLAG # IS THIS INTSTALLED ROUTINE TO BE CAF REINTBIT MASK RASFLAG EXTEND - BZF GOBAC # DON'T INTWAKE IF WE CAME HERE VIA RESTART + BZF GOBAC # DONT INTWAKE IF WE CAME HERE VIA RESTART INTWAKE1 CAF ZERO WAKE TS STALTEM # INDEX OF ANY STALL USER @@ -877,10 +871,10 @@ INTBITAB OCT 20100 # AVETOMID # # THIS ROUTINE PERFORMS THE TRANSITION FROM A THRUSTING PHASE TO THE COAST -# PHASE BY INITIALIZING THIS VEHICLE'S PERMANENT STATE VECTOR WITH THE +# 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 IT'S VALID (OR WFLAG OR RENDWFLT IS +# 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. @@ -894,12 +888,12 @@ INTBITAB OCT 20100 AVETOMID STQ BON EGRESS RENDWFLG - INT/W # W-MATRIX VALID, GO INTEGRATE IT + INT/W # W-MATRIX VALID ,GO INTEGRATE IT BON ORBWFLAG - INT/W # W-MATRIX VALID, GO INTEGRATE IT. + INT/W # W-MATRIX VALID ,GO INTEGRATE IT -SETCOAST AXT,2 CALL # NOW MOVE PROPERLY SCALED RN,UN AS WELL AS +SETCOAST AXT,2 CALL # NOW MOVE PROPERLY SCALED RN,VN AND 2 # PIPTIME TO INTEGRATION ERASABLES. INTSTALL BON AXT,2 @@ -945,7 +939,7 @@ INT/W DLOAD CALL INTSTALL SET SET DIM0FLAG # DO W-MATRIX - AVEMIDSW # SO WON'T CLOBBER RN,VN,PIPTIME + AVEMIDSW # SO WONT CLOBBER RN,VN,PIPTIME CLEAR SET D6OR9FLG VINTFLAG @@ -959,27 +953,27 @@ INT/W DLOAD CALL # # 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) +# 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 TO THE CURRENT TIME. +# 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 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 +# 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 THIS VEHICLE'S STATE VECTOR TO THE CURRENT TIME PLUS +# 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 +# ADDRESS WITH THE ABOVE TRANSFERS TO R,VN1-PIPTIME1-AND MPAC DONE SETLOC INTINIT BANK @@ -999,13 +993,13 @@ MIDTOAV1 STQ CALL SET RTB MID1FLAG LOADTIME - DAD BDSU # INITIAL CHECK, IS TDEC1 IN THE FUTURE + DAD BDSU # INITIAL CHECK.IS TDEC1 IN THE FUTURE. TIMEDELT TDEC1 BPL CALL ENTMID1 # Page 1330 - NOTIME # NO, SET ALARM, SWITCH TO MIDTOAV2 + NOTIME # NO SET ALARM.SWITCH TO MIDTOAV2 ENTMID2 RTB DAD LOADTIME @@ -1019,7 +1013,7 @@ ENTMID1 CLEAR CALL INTYPFLG MIDAVFLG # LET INTEG. KNOW THE CALL IS FOR MIDTOAV. CALL - INTEGRV # GO INTEGRATE + INTEGRV # GO INTEGRATE SXA,2 SXA,1 RTX2 RTX1 @@ -1077,9 +1071,9 @@ MID2 DLOAD DSU TET DSU BPL 5.6SECS - A-PCHK # YES. GET OUT. + A-PCHK # YES,GET OUT. - DLOAD DAD # NO. ADD TIMEDELT TO T-TO-ADD AND TRY + DLOAD DAD # NO,ADD TIMEDELT TO T-TO-ADD AND TRY T-TO-ADD # AGAIN. TIMEDELT STCALL T-TO-ADD @@ -1121,17 +1115,17 @@ INTWAKEU RELINT UPSVFLAG # REQUEST. IF NOT GO TO INTWAKUP. INTWAKUP - VLOAD # MOVE PRECT(6) AND VRECT(6) INTO - RRECT # RCV(6) AND VCV(6) RESPECTIVELY. + 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' + 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........ + INTWAKEM # SPHERE OF INFLUENCE......... AXT,2 CLRGO # EARTH SPHERE OF INFLUENCE. DEC 0 MOONFLAG @@ -1142,7 +1136,7 @@ INTWAKEM AXT,2 SET # LUNAR SPHERE OF INFLUENCE. 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...... + INTWAKLM # STATE VECTOR UPDATE...... CALL # UPDATE CSM STATE VECTOR ATOPCSM @@ -1150,17 +1144,17 @@ INTWAKEC SLOAD BMN # COMMON CODING AFTER X2 INITIALIZED AND ORBWFLAG INTWAKEX -INTWAKLM CALL # UPDATE LM STATE VECTOR +INTWAKLM CALL # UPDATE LM STATE VECTOR ATOPLEM INTWAKEX CLEAR RENDWFLG -INTWAKUP SSP CALL # REMOVE `UPDATE STATE VECTOR INDICATOR' +INTWAKUP SSP CALL # REMOVE :UPDATE STATE VECTOR INDICATOR: # Page 1333 UPSVFLAG 0 - INTWAKE0 # RELEASE `GRAB' OF ORBIT INTEG. + INTWAKE0 # RELEASE :GRAB: OF ORBIT INTEG EXIT TC PHASCHNG @@ -1178,5 +1172,3 @@ GRP2PC STQ EXIT GOTO GRP2SVQ - -