| Quellcodebibliothek Statistik Leitseite products/Sources/formale Sprachen/Asm/Apollo-11/Luminary099/ Datei vom 11.9.2026 mit Größe 24 kB |
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SSL INTEGRATION_INITIALIZATION.agc Sprache: Apollo |
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# Copyright: Public domain. # Filename: INTEGRATION_INITIALIZATION.agc # Purpose: Part of the source code for Luminary 1A build 099. # It is part of the source code for the Lunar Module's (LM) # Apollo Guidance Computer (AGC), for Apollo 11. # Assembler: yaYUL # Contact: Ron Burkey <info@sandroid.org>. # Website: www.ibiblio.org/apollo. # Pages: 1205-1226 # Mod history: 2009-05-26 RSB Adapted from the corresponding # Luminary131 file, using page # images from Luminary 1A. # 2011-01-06 JL Fixed pseudo-label indentation. # # 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 001 of AGC program LMY99 by NASA 2021112-061 # 16:27 JULY 14, 1969 # Page 1205 # 1.0 INTRODUCTION # ---------------- # # FROM A USER'S POINT OF VIEW, ORBITAL INTEGRATION IS ESSENTIALLY THE SAME AS THE 278 INTEGRATIO # PROGRAM. THE SAME ENTRANCES TO THE PROGRAM WILL BE MAINTAINED, THE SAME STALLING ROUTINE WILL # OUTPUT WILL STILL BE VIA THE PUSHLIST. THE PRIMARY DIFFERENCES TO A USER INVOLVE THE ADDED CAPA # TERMINATING INTEGRATION AT A SPECIFIC FINAL RADIUS AND THE DIFFERENCE IN STATE VECTOR SCALIN # THE LUNAR SPHERE OF INFLUENCE. # # IN ORDER TO MAKE THE CSM(LEM)PREC AND CSM(LEM)CONIC ENTRANCES SIMILAR TO FLIGHT 278, THE INTE # WILL ITSELF SET THE FINAL RADIUS (RFINAL) TO 0 SO THAT REACHING THE DESIRED TIME ONLY WILL TERMI # INTEGRATION. THE DP REGISTER RFINAL MUST BE SET BY USERS OF INTEGRVS AND INTEGRV, AND MUST BE DO # CALL TC INTSTALL. # # WHEN THE LM IS ON THE LUNAR SURFACE (INDICATED BY LUNAR SURFACE FLAG SET) CALLS TO LEMCONIC, LEM # INTEGRV WITH VINFLAG = 0 WILL RESULT IN THE USE OF THE PLANETARY INERTIAL ORIENTATION SUBROUTI # BOTH THE LM'S 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 # THE PERMANENT STATE VECTOR UPDATED WHEN SPECIFIED BY AN INTEGRV CALL. # # USERS OF INTEGRVS DESIRING INTEGRATION (INTYPFLG = 0) SHOULD NOTE THAT THE OBLATENESS PERTUR # IN LUNAR ORBIT IS TIME DEPENDENT. THEREFORE, THE USER SHOULD SUPPLY AN INITIAL STATE VECTOR VA # TIME AND THE DESIRED TIME (TDEC1) ALSO AT SOME REAL TIME. FOR CONIC "INTEGRATION" THE USER MAY S # AS THE INITIAL TIME AND DELTA TIME AS THE DESIRED TIME. # # 2.0 GENERAL DESCRIPTION # ----------------------- # # THE INTEGRATION PROGRAM OPERATES AS A CLOSED INTERPRETIVE SUBROUTINE AND PERFORMS THESE FUN # 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, CSMCONI # ALL THE FLAGS REQUIRED IN THE INTEGRATION PROGRAM ITSELF TO CAUSE THE PRECISION OR CONIC INTEG # THE LM OR CSM STATE VECTOR, AS THE NAMES SUGGEST. ONE ENTRANCE (INTEGRVS) PERMITS THE CALLING P # PROVIDE A STATE VECTOR TO BE INTEGRATED. THE CALLING PROGRAM MUST SET THE FLAGS INDICATING (1) # CONIC INTEGRATION, (2) IN OR OUT OF LUNAR SPHERE, (3) MIDCOURSE OR NOT, AND THE INTEGRATION PRO # THE FLAG SETTING TO BYPASS W-MATRIX INTEGRATION. THE LAST ENTRANCE (INTEGRV, USED IN GENERAL # NAVIGATION PROGRAMS) PERMITS THE CALLER TO SET FIVE FLAGS (NOT MOONFLAG OR MIDFLAG) BUT NOT TO # VECTOR. ANY PROGRAM WHICH CALLS INTEGRVS OR INTEGRV MUST CALL INTSTALL BEFORE IT SETS THE INTE # AND/OR STATE VECTOR. # # THREE SETS OF 42 REGISTERS AND 2 FLAGS ARE USED FOR THE STATE VECTORS. TWO SETS, WHICH MAY NOT BE O # USED FOR THE PERMANENT STATE VECTORS FOR THE CSM AND LM. THE THIRD SET, WHICH MAY BE OVERLAYED WH # 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 # THE PERMANENT STATE VECTORS WILL ALSO BE UPDATED WHENEVER THE W-MATRIX IS INTEGRATED OR WHEN A # SETS STATEFLG (THE NAVIGATION PROGRAMS P20, P22.) # # Page 1206 # 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., WHE # INTEGRATED OR PERMANENT STATE VECTOR IS UPDATED.) THE GROUP NUMBER USED WILL BE THAT FOR THE P2 # (I.E., GROUP2) WINCE THE INTEGRV ENTRANCE WILL ONLY BE USED BY THESE PROGRAMS. IF A RESTART OCC # INTEGRATION OF THE STATE VECTOR ONLY, THE RECOVERY WILL BE TO THE LAST PHASE IN THE CALLING PROG # PROGRAMS WHICH USE THE INTEGRV OR INTEGRVS ENTRANCE OF INTEGRATION WHOULD ENSURE THAT IF PHAS # 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 U # APPENDIX B OF THE USERS GUIDE. THE SCALING OF THE OUTPUT POSITION VECTOR DEPENDS ON THE ORIGIN O # SYSTEM AT THE DESIRED INTEGRATION TIME. THE COORDINATE SYSTEM TRANSFORMATION WILL BE DONE AU # MULTIPLE TIMESTEP ENCKE INTEGRATION ONLY. THUS IT IS POSSIBLE TO HAVE OUTPUT FROM SUCCESSIVE # 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 QUANTITIE # APPENDIX B OF THE USERS GUIDE, PLUS THE DESIRED TIME TO INTEGRATE TO IN TDEC1 (A PUSH LIST LOCATI # FOR INTEGRVS, THE RCV,VCV,TET OR THE TEMPORARY STATE VECTOR MUST BE SET, PLUS MOONFLAG AND MID # # 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 1207 # 29 27 # RCVSM(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) ROOT 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 ORIGIN 0 2 # (THIS, NOT MOONFLAG, SHOULD BE # Page 1208 # 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 = DIM0FLAG = 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 1209 # 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 DIM0FLAG 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 DIM0FLAG=1. (STATEFLG IS # L+2 RETURN ALWAYS RESET IN INTEGRATION AFTER # IT 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* $$/INTIN STATEINT TC PHASCHNG OCT 00052 CAF PRIO5 TC FINDVAC EBANK= RRECTCSM 2CADR STATINT1 TC TASKOVER STATINT1 TC INTPRET BON RTB QUITFLAG # KILL INTEGRATION UNTIL NEXT P00. NOINT LOADTIME STORE TDEC1 # Page 1210 CALL 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 00002 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 CMOONFLG SVDWN1 BON CLRGO # Page 1211 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 # ATOPLEM TRANSFERS RRECT TO RRECT +41 TO RRECTLEM TO RRECTLEM +41 ATOPLEM STQ RTB # Page 1212 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 STODL TET 5/8 CALL # Page 1213 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 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 INTEGR # APPROPRIATE SWITCHES SET OR CLEARED FOR THE DESIRED INTEGRATION. # # CSMPREC AND LEMPREC PERFORM ORBIT INTEGRATION BY THE ENCKE METHOD TO THE TIME INDICATED IN TDE # 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. # NO DISTURBING ACCELERATIONS ARE INCLUDED. IN THE PROGRAM FLOW THE GIVEN # STATE VECTOR IS RECTIFIED BEFORE SOLUTION OF KEPLER'S 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 # # CALLING SEQUENCE # L-X STORE TDEC1 # L CALL (STCALL TDEC1) # Page 1214 # 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 INTSTALL SXA,1 CLRGO IRETURN # Page 1215 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 # # OUTPUT # RATT AS # VATT DEFINED # Page 1216 # TAT BEFORE INTEGRV STQ IRETURN INTEGRV1 SET SET RPQFLAG NEWIFLG INTEGRV2 SSP QPRET ALOADED BON GOTO VINTFLAG PTOACSM PTOALEM ALOADED DLOAD TDEC1 STORE TDEC BOFF GOTO INTYPFLG TESTLOOP RVCON A-PCHK BOF 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 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 # Page 1217 RRECT PDVL PDDL* VRECT MUEARTH,2 PUSH AXT,1 DEC -10 BON AXT,1 MOONFLAG +2 DEC -2 # SUBROUTINE TO COMPUTE L VECTOR FOR# # L CALL # AXO,AYO SET AT LAUNCH TIME WITH AYO# CLEAR# -AX AVEMIDSW # ALLOW UPDATE OF DOWNLINK STATE VECTOR java.lang.StringIndexOutOfBoundsException: Index 0 out of bounds for length 0 # STATEFLG =#java.lang.StringIndexOutOfBoundsException: Index 43 out of bounds for SLOAD EXIT IRETURN # TS =26 # TCMMATRIX D # RVCON SETS UP ORBIT INTEGRATION TO DO A CONIC SOLUTION FOR POSITION AND # VELOCITY FOR THE INTERVAL (TET-TDEC) RVCON DLOAD DSU TDEC TET STCALLTAU. RECTIFY CALL KEPPREP DLOAD DAD TC TET STCALL TET RECTOUT # Page 1218 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 POOHCHK USEMAXDT DLOAD SIGN 12D DT/2 # Page 1219 STCALL DT/2 POOHCHK MAXDT DLOAD PDDL # EXCHANGE DT/2MAX WITH COMPUTED MAX. DT/2MAX GOTO DT/2COMP GETMAXDT RTB SIGNMPAC STCALL DT/2 USEMAXDT POOHCHK 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 BMN GOTO INTEXIT TIMESTEP DT/2MIN 2DEC 3 B-20 DT/2MAX 2DEC 4000 E2 B-20 INTSTALL EXIT CA RASFLAG MASK INTBITAB # IS THIS STALL AREA FREE EXTEND BZF OKTOGRAB # YES # Page 1220 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, DON'T RESTART WITH SOMEONE ELSE'S Q TC PHASCHNG OCT 04022 CA TBASE2 INDEX FIXLOC TS QPRET CAF REINTBIT MASK RASFLAG EXTEND BZF GOBAC # DON'T INTWAKE IF WE CAME HERE VIA RESTART INTWAKE1 CAF WAKESTAL INHINT TC JOBWAKE CCS LOCCTR TCF INTWAKE1 FORTYONE DEC 41 CS INTBITAB MASK RASFLAG TS RASFLAG # RELEASE STALL AREA RELINT TCF GOBAC OKTOGRAB CAF INTFLBIT INHINT ADS RASFLAG GOBAC TC INTPRET RVQ WAKESTAL CADR INTSTALL +1 INTBITAB OCT 20100 # Page 1221 # AVETOMID # # THIS ROUTINE PERFORMS THE TRANSITION FROM A THRUSTING PHASE TO THE COAST # PHASE BY INITIALIZING THIS VEHICLE'S 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 (OR WFLAG 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 INTINIT 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. OTHERS DLOAD CALL # GET SET FOR OTHER VEHICLE INTEGRATION PIPTIME # DESIRED TIME INTSTALL SET CALL VINTFLAG # CM SETIFLGS # SETS UP NONE W-MAT. PERMANENT INTEG. STCALL TDEC1 INTEGRV AXT,2 CALL # NOW MOVE PROPERLY SCALE RN,UN AS WELL AS 2 # PIPTIME TO INTEGRATION ERASABLES. INTSTALL BON AXT,2 MOONTHIS +2 0 VLOAD VSR* RN 0,2 STORE RRECT STODL RCV PIPTIME STOVL TET VN # Page 1222 VSR* CALL 0,2 MINIRECT # FINISH SETTING UP STATE VECTOR RTB SSP MOVATHIS # PUT TEMP STATE VECTOR INTO PERMANENT TRKMKCNT 0 GOTO FAZAB5 INT/W DLOAD CALL PIPTIME # INTEGRATE W THRU BURN INTSTALL SET SET DIM0FLAG # DO W-MATRIX AVEMIDSW # SO WON'T CLOBBER RN,VN,PIPTIME SET CLEAR D6OR9FLG # 9X9 FOR LM VINTFLAG # LM STCALL TDEC1 INTEGRV GOTO OTHERS # NOW GO DO THE OTHER VEHICLE # Page 1223 # 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 COMPUTATION TIME FOR ONE TIME STEP) # IS GREATER THAN THE DESIRED TIME, ALARM 1703 IS SET AND THE INTEGRATION # IS DONE TO THE CURRENT TIME. # 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 # MIDTOAV2 # # THIS ROUTINE INTEGRATES THIS VEHICLE'S STATE VECTOR TO THE CURRENT TIME. # 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 EBANK= IRETURN1 MIDTOAV2 STQ CLRGO # INTEGRATE TO PRESENT TIME PLUS TIMEDELT IRETURN1 MID1FLAG ENTMID2 MIDTOAV1 STQ SET # INTEGRATE TO TDEC1 IRETURN1 MID1FLAG RTB DAD # INITIAL CHECK, IS TDEC1 IN THE FUTURE LOADTIME TIMEDELT BDSU BPL TDEC1 ENTMID1 # Y5S CALL NOTIME # NO, SET ALARM, SWITCH TO MIDTOAV2 ENTMID2 RTB DAD LOADTIME TIMEDELT STORE TDEC1 ENTMID1 CALL INTSTALL CLEAR CALL # Page 1224 DIM0FLAG # NO W-MATRIX THISVINT CLEAR SET INTYPFLG MIDAVFLG # LET INTEG. KNOW THE CALL IS FOR MIDTOAV. CALL INTEGRV # GO INTEGRATE CLEAR VLOAD MIDAVFLG RATT STOVL RN1 VATT STODL VN1 TAT STORE PIPTIME1 SXA,2 SXA,1 RTX2 RTX1 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 NOTIME TIMEINC RTB DAD LOADTIME TIMEDELT STCALL TDEC TESTLOOP MID2 DLOAD DSU TDEC TET ABS DSU 3CSECS # Page 1225 BMN GOTO A-PCHK 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 RVQ 3CSECS 2DEC 3 TIMEDELT 2DEC 2000 BANK 27 SETLOC UPDATE2 BANK EBANK= INTWAKUQ 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 PRECT(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 # Page 1226 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' 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
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2026-10-13