# Copyright: Public domain. # Filename: P37_P70.agc # Purpose: Part of the source code for Colossus 2A, AKA Comanche 055. # It is part of the source code for the Command Module's (CM) # Apollo Guidance Computer (AGC), for Apollo 11. # Assembler: yaYUL # Contact: Jim Lawton <jim.lawton@gmail.com>. # Website: www.ibiblio.org/apollo. # Pages: 890-933 # Mod history: 2009-05-11 JVL Adapted from the Colossus249/ file # of the same name, using Comanche055 page # images. # 2009-05-20 RSB Added missing label V2T179. Fixed POODOO -> POODOO. # 2009-05-23 RSB In RTD18, corrected a STOVL DELVLVC to # STODL DELVLVC and a STODL 02D to STORE 02D. # # 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 055 of AGC program Comanche by NASA # 2021113-051. 10:28 APR. 1, 1969 # # This AGC program shall also be referred to as # Colossus 2A
# Page 890 BANK31 SETLOC RTE1 BANK
EBANK= RTEDVD COUNT31/P37
# PROGRAM DESCRIPTION: P37, RETURN TO EARTH # # DESCRIPTION # A RETURN TO EARTH TRAJECTORY IS COMPUTED PROVIDED THE CSM IS OUTSIDE THE LUNAR SPHERE OF INFLUENCE AT THE # TIME OF IGNITION. INITIALLY A CONIC TRAJECTORY IS DETERMINED AND RESULTING IGNITION AND REENTRY PARAMETERS ARE # DISPLAYED TO THE ASTRONAUT. THEN IF THE ASTRONAUT SO DESIRES, A PRECISION TRAJECTORY IS DETERMINED WITH THE # RESULTING IGNITION AND REENTRY PARAMETERS DISPLAYED. UPON FINAL ACCEPTANCE BY THE ASTRONAUT, THE PROGRAM # COMPUTES AND STORES THE TARGET PARAMETERS FOR RETURN TO EARTH FOR USE BY SPS PROGRAM (P40) OR RCS PROGRAM (P41). # # CALLING SEQUENCE # L TC P37 # # SUBROUTINES CALLED # PREC100 # V2T100 # RTENCK2 # RTENCK3 # TIMERAD # PARAM # V2T100 # GAMDV10 # XT1LIM # DVCALC # RTENCK1 # INTSTALL # INTEGRVS # RTEVN # RTEDISP # TMRAD100 # AUGEKUGL # LAT-LONG # TMRAD100 # TIMERAD # INVC100 # CSMPREC # GETERAD # TIMETHET # P370ALRM # VN1645 # POLY # # ERASABLE INITIALIZATION REQUIRED # CSM STATE VECTOR # Page 891 # NJETSFLG NUMBER OF JETS IF THE RCS PROPULSION SYSTEM SELECTED STATE FLAG 0=4 JETS 1=2 JETS # # ASTRONAUT INPUT # SPRTETIG TIME OF IGNITION (OVERLAYS TIG) DP B28 CS # VPRED DESIRED CHANGE IN VELOCITY AT TIG(PROGRM COMPUTED IF 0) DP B7 METERS/CS # GAMMAEI DESIRED FLIGHT PATH ANGLE AT REENTRY (COMPUTED IF 0) DP B0 REVS + ABOVE HORIZ. # OPTION2 PROPULSION SYSTEM OPTION SP B14 1=SPS, 2=RCS # # OUTPUT # CONIC OR PRECISION TRAJECTORY DISPLAY # VPRED VELOCITY MAGNITUDE AT 400,000 FT. ENTRY ALTITUDE DP B7 METERS/CS # T3TOT4 TRANSIT TIME TO 400,000 FT. ENTRY ALTITUDE DP B28 CS # GAMMAEI FLIGHT PATH ANGLE AT 400,00 FT. ENTRY ALTITUDE DP B0 REVS + ABOVE HORIZON # DELVLVC INITIAL VELOCITY CHANGE VECTOR IN LOCAL VERTICAL COORD. VECTOR B7 METERS/CS # LAT(SPL) LATITUDE OF THE LANDING SITE DP B0 REVS # LNG(SPL) LONGITUDE OF THE LANDING SITE DP B0 REVS # TARGETING COMPUTATION DISPLAY # TIG RECOMPUTED TIG BASED ON THRUST OPTION DP B28 CS # TTOGO TIME FROM TIG DP B28 CS # +MGA POSITIVE MIDDLE GIMBAL ANGLE DP B0 REVS -.02 IF REFSMFLG=0 # THRUST PROGRAM COMMUNICATION # XDELVFLG EXTERNAL DELTA V FLAG STATE FLAG SET 0 FOR LAMBERT AIMPT # NORMSW LAMBERT AIMPT ROTATION SWITCH STATE FLAG SET 0 FOR NO ROTATION # ECSTEER CROSS PRODUCT STEERING CONSTANT SP B2 SET 1 # RTARG CONICALLY INTEGRATED REENTRY POSITION VECTOR VECTOR B29 METERS # TPASS4 REENTRY TIME DP B28 CS
# Page 901 # TIME RADIUS CALLING SUBROUTINE # # INPUT # RVEC INITIAL POSITION VECTOR VECTOR B29 METERS # VVEC INITIAL VELOCITY VECTOR VECTOR B7 METERS/CS # RDESIRED FINAL RADIUS FOR WHICH TRANSFER TIME IS TO BE COMPUTED DP B29 METERS # CONICX1 X1 SETTING FOR CONIC SUBROUTINES -2=EARTH SP B14 # # OUTPUT # R(T2)/ FINAL POSITION VECTOR VECTOR B29 METERS # V(T2)/ FINAL VELOCITY VECTOR VECTOR B7 METERS/CS # T12 TRANSFER TIME TO FINAL RADIUS DP B28 CS
# Page 902 # DISPLAY CALCULATION SUBROUTINE # # DESCRIPTION # OUTPUT FOR DISPLAY IS CONVERTED TO PROPER UNITS AND PLACED IN OUTPUT STORAGE REGISTERS. LANDING SITE # COMPUTATION FOR DETERMINING LANDING SITE LATITUDE AND LONGITUDE IS INCLUDED IN THE ROUTINE. # # CALLING SEQUENCE # L CALL # L+1 RTEDISP # # SUBROUTINES CALLED # TMRAD100 # AUGEKUGL # LAT-LONG # # ERASABLE INITIALIZATION REQUIRED # PUSHLIST # NONE # MPAC # NONE # OTHER # R(T2)/ FINAL POSITION VECTOR VECTOR B29 METERS # V(T2)/ FINAL VELOCITY VECTOR VECTOR B7 METERS/CS # T2 FINAL TIME DP B28 CS # V2(T1)/ POST IMPULSE INITIAL VELOCITY VECTOR VECTOR B7 METERS/CS # V(T1)/ INITIAL VELOCITY VECTOR VECTOR B7 # UR1/ UNIT INITIAL VECTOR VECTOR B1 # UH/ UNIT HORIZONTAL VECTOR VECTOR B1 # # OUTPUT # VPRED VELOCITY MAGNITUDE AT 400,000 FT. ENTRY ALTITUDE DP B7 METERS/CS # T3TOT4 TRANSIT TIME TO 400,000 FT. ENTRY ALTITUDE DP B28 CS # GAMMAEI FLIGHT PATH ANGLE AT 400,000 FT. ENTRY ALTITUDE DP B0 REVS + ABOVE HORIZ # DELVLVC INITIAL VELOCITY CHANGE VECTOR IN LOCAL VERTICAL COORD. VECTOR B7 METERS/CS # LAT(SPL) LATITUDE OF THE LANDING SITE DP B0 REVS # LNG(SPL) LONGITUDE OF THE LANDING SITE DP B0 REVS
# Page 904 04D STODL LNG(SPL) # LNG(SPL)=SIN(PHIE) PL04D
COS STORE LAT(SPL) # LAT(SPL)=COS(PHIE)
VLOAD UNIT
R(T2)/ PUSHPUSH
PDVL UNIT # PL22D
V(T2)/
PDVL VXV
VXV UNIT # UH3=UNIT(UR3 X UV3 X UR3) PL10D VXSC PDVL
LNG(SPL) VXSC VAD # PL04D
LAT(SPL)
CLEAR CLEAR # T(LS) IN MPAC
ERADFLAG
LUNAFLAG STODL ALPHAV # ALPHAV=UR3(COSPHIE)+UH3(SINPHIE) PL02D CALL
LAT-LONG DLOAD
LAT STODL LAT(SPL) # LATITUDE LANDING SITE *****
LONG
STCALL LNG(SPL) # LONGITUDE LANDING SITE *****
SPRTEX COUNT* $$/RTE
# Page 905 # INITIAL VECTOR SUBROUTINE # # DESCRIPTION # A PRECISION INTEGRATION OF THE STATE VECTOR TO THE TIME OF IGNITION IS PERFORMED. PRECOMPUTATIONS OCCUR. # # CALLING SEQUENCE # L CALL # L+1 INVC100 # # NORMAL EXIT MODE # AT L+2 OF CALLING SEQUENCE WITH MPAC = 0 # # ALARM EXIT MODE # AT L+2 OF CALLING SEQUENCE WITH MPAC = OCTAL 612 FOR STATE VECTOR IN MOONS SPHERE OF INFLUENCE # # SUBROUTINES CALLED # CSMPREC # # ERASABLE INITIALIZATION REQUIRED # PUSHLIST # NONE # MPAC # NONE # OTHER # SPRTETIG TIME OF IGNITION DP B28 CS # CSM STATE VECTOR # # OUTPUT # R(T1)/ INITIAL POSITION VECTOR AT TIG VECTOR B29 METERS # V(T1)/ INITIAL VELOCITY VECTOR AT TIG VECTOR B7 METERS/CS # T1 INITIAL VECTOR TIME (TIG) DP B28 CS # UR1/ UNIT INITIAL VECTOR VECTOR B1 # UH/ UNIT HORIZONTAL VECTOR VECTOR B1 # CFPA COSINE OF INITIAL FLIGHT PATH ANGLE DP B1
INVC100 STQ DLOAD
SPRTEX
SPRTETIG
STCALL TDEC1
CSMPREC # PRECISION INTEGRATION R0,V0 TO R1,V1
VLOAD SXA,2
RATT
P(T1) STOVL R(T1)/
VATT STODL V(T1)/
TAT STORE T1 SLOAD BZE
P(T1) # Page 906
INVC109
INVC107 SLOAD GOTO
OCT612
RTEALRM # R1,V1 NOT IN PROPER SPHERE OF INFLUENCE
INVC109 VLOAD UNIT
R(T1)/ STODL UR1/ # UR1/ B1 36D STOVL R(T1) # R(T1) B29
V(T1)/
UNIT STORE UV1/
DOT SL1
UR1/ STORE CFPA # CFPA B1
ABS DSU
EPC1RTE
BMN DLOAD
INVC115 # NOT NEAR RECTILINEAR 1RTEB2
PDDL PUSH
ZERORTE
VDEF PUSH# N/ = (0,0,1)
GOTO
INVC120
INVC115 VLOAD VXV
UR1/
UV1/ PUSH# N/ = UR X UV B2
INVC120 CLEAR DLOAD
RETROFLG PUSH BPL
INVC125
VLOAD VCOMP # RETROGRADE ORBIT PUSH SET
RETROFLG
INVC125 VLOAD
VXV UNIT
UR1/ STORE UH/ # UH/ B1
GOTO
SPRTEX
# Page 907 # PRECISION TRAJECTORY COMPUTATION SUBROUTINE # # DESCRIPTION # A NUMERICALLY INTEGRATED TRAJECTORY IS GENERATED WHICH FOR THE RETURN TO EARTH PROBLEM SATISFIES THE REENTRY # CONSTRAINTS (RCON AND X(T2)) ACHIEVED BY THE INITIAL CONIC TRAJECTORY AND MEETS THE DVD REQUIREMENT AS CLOSELY # AS POSSIBLE. # # CALLING SEQUENCE # L CALL # L+1 PREC100 # # NORMAL EXIT MODE # AT L+2 OF CALLING SEQUENCE WITH MPAC = 0 # # ALARM EXIT MODE # AT L+2 OF CALLING SEQUENCE WITH MPAC = # OCTAL 605 FOR EXCESS ITERATIONS # OCTAL 613 FOR REENTRY ANGLE OUT OF LIMITS # # SUBROUTINES CALLED # INTSTALL # RTENCK2 # RTENCK3 # TIMERAD # PARAM # V2T100 # # ERASABLE INITIALIZATION REQUIRED # PUSHLIST # NONE # MPAC # NONE # OTHER # R(T1)/ INITIAL POSITION VECTOR VECTOR B29/B27 METERS # V2(T1)/ POST IMPULSE INITIAL VELOCITY VECTOR VECTOR B7/B5 METERS/CS # V(T1)/ INITIAL VELOCITY VECTOR VECTOR B7/B5 METERS/CS # T1 INITIAL VECTOR TIME DP B28 CS # T12 INITIAL TO FINAL POSITION TIME DP B28 CS # RCON CONIC FINAL RADIUS DP B29/B27 METERS # R(T1) MAGNITUDE OF INITIAL POSITION VECTOR DP B29/B27 METERS # X(T2) COTANGENT OF FINAL FLIGHT PATH ANGLE DP B0 # X(T1) COTANGENT OF INITIAL FLIGHT PATH ANGLE DP B5 # RTEDVD DELTA VELOCITY DESIRED DP B7/B5 METERS/CS # MAMAX1 MAJOR AXIS LIMIT FOR LOWER BOUND ON GAMDV ITERATOR DP B30/B28 METERS # MAMAX2 MAJOR AXIS LIMIT FOR UPPER BOUND ON GAMDV ITERATOR DP B30/B28 METERS # UR1/ UNIT INITIAL VECTOR VECTOR B1 # UH/ UNIT HORIZONTAL VECTOR VECTOR B1 # BETA1 1+X(T2)**2 DP B1 # PHI2 PERIGEE OR APOGEE INDICATOR DP B2 -1 PERIGEE, +1 APOGEE # # Page 908 # # OUTPUT # V2(T1)/ POST IMPULSE INITIAL VELOCITY VECTOR VECTOR B7 METERS/CS # R(T2)/ FINAL POSITION VECTOR VECTOR B29 METERS # V(T2)/ FINAL VELOCITY VECTOR VECTOR B7 METERS/CS # T2 FINAL TIME DP B28 CENTISECONDS # # DEBRIS # RD FINAL R DESIRED DP B29/B27 METERS # R/APRE R/A DP B6 # P/RPRE P/R DP B4 # RPRE MAGNITUDE OF R(T2)/ DP B29/B27 METERS # X(T2)PRE COTANGENT OF GAMMA2 DP B0 # DT12 CORRECTION TO FINAL TIME T2 DP B28 CENTISECONDS # RCON FINAL RADIUS DP B29/B27 METERS # DRCON DELTA RCON DP B29/B27 METERS
DLOAD BZE
NN1A
PREC132 # TOO MANY ITERATIONS
DSU BZE 10RTE
PREC207
PREC205 DLOAD DSU # NOT FIRST PASS OF ITERATION
RPRE'
RPRE # RPRE'-RPRE B29/B27
NORM BDDV
X2
DRCON
SL* PUSH# DRCON/(RPRE'-RPRE)=S B2 0 -2,2
DAD BOV # S GR +4 OR LS -4 1RTEB1
PREC205M
ABS DSU # Page 912 1RTEB1
BMN
PREC206
PREC205M DLOAD DCOMP # S GR 0 OR LS -4 2RTEB1
PDDL # S=-4 B2
PREC206 DLOAD DMP
SL2 STORE DRCON # DRCON=S(RERR) B29
DAD
RCON STORE RCON # RCON+DRCON=RCON
GOTO
PREC210
PREC207 DLOAD DSQ # FIRST PASS OF ITERATION
RD
NORM SR1
X1
PDDL NORM
RPRE
X2
XSU,1 BDDV
X2
SR* 0 -1,1 STORE RCON # RD**2/RPRE=RCON
DSU
RD STORE DRCON # RCON-RD=DRCON
PREC210 DLOAD# PREPARE FOR NEXT ITERATION
RPRE STODL RPRE'
NN1A
DSU 1RTEB28
STCALL NN1A
V2T100
BHIZ GOTO
PREC120
PRECX
# DESIRED RADIUS ACHIEVED
SETLOC RTE2 BANK
PREC220 DLOAD DSU
X(T2)
X(T2)PRE
ABS DSU
EPC8RTE # Page 913
BMN SLOAD
PREC225
OCT613
GOTO
PRECX # IF REENTRY ANGLE OUT OF LIMITS
EPC8RTE 2DEC .002
OCT613 OCT613
# DESIRED FINAL ANGLE HAS BEEN REACHED.
SETLOC RTE BANK
PREC225 DLOAD
ZERORTE
PRECX GOTO
SPRTEX
# Page 914 # INTEGRATION CALLING SUBROUTINE # # DESCRIPTION # PERFORMS CONIC AND PRECISION INTEGRATIONS USING SUBROUTINE INTEGRVS. THERE ARE THREE ENTRANCES (RTENCK1, # RTENCK2, AND RTENCK3) FOR DIFFERENT SOURCES OF INPUT AND DIFFERENT OPTIONS. THERE IS A COMMON SET OF OUTPUT # WHICH INCLUDES SET UP OF INPUT FOR THE PARAM SUBROUTINE. # # RTENCK1 (CONIC INTEGRATION) # # CALLING SEQUENCE # L CALL # L+1 RTENCK1 # # ERASABLE INITIALIZATION REQUIRED # SAME AS FOR THE RTENCK3 ENTRANCE # # RTENCK2 (PRECISION INTEGRATION) # # CALLING SEQUENCE # L CALL # L+1 RTENCK2 # # ERASABLE INITIALIZATION REQUIRED # PUSHLIST # PUSHLOC-2 INTEGRATION TIME DT12 (CORRECTION TO T2) DP B28 CS # OTHER # R(T2)/ FINAL POSITION VECTOR VECTOR B29 METERS # V(T2)/ FINAL VELOCITY VECTOR VECTOR B7 METERS/CS # T2 FINAL TIME DP B28 CS # # RTENCK3 (PRECISION INTEGRATION) # # CALLING SEQUENCE # L CALL # L+1 RTENCK3 # # ERASABLE INITIALIZATION REQUIRED # R(T1)/ INITIAL POSITION VECTOR VECTOR B29 METERS # V2(T1)/ POST IMPULSE INITIAL VELOCITY VECTOR VECTOR B7 M/CS # T1 INITIAL VECTOR TIME DP B28 CS # T2 FINAL TIME DP B28 CS # # EXIT MODE # AT L+2 OF CALLING SEQUENCE # # SUBROUTINES CALLED # INTSTALL # INTEGRVS # # OUTPUT # PUSHLIST # Page 915 # PUSHLOC-6 FINAL POSITION VECTOR R(T2)/ VECTOR B29 METERS # X1 CONICS MUTABLE ENTRY FOR EARTH (-2) SP B14 # MPAC # FINAL VELOCITY VECTOR V(T2)/ VECTOR B7 M/CS # OTHER # R(T2)/ AS IN PUSHLIST # V(T2)/ AS IN MPAC # T2 FINAL TIME DP B28 CS
SETLOC RTE3 BANK
RTENCK1 STQ CALL
RTENCKEX
INTSTALL
VLOAD SET
R(T1)/
INTYPFLG
GOTO
RTENCK3B
RTENCK2 STQ CALL
RTENCKEX
INTSTALL
CLEAR VLOAD
INTYPFLG
R(T2)/ STOVL RCV
V(T2)/ STODL VCV
T2 STORE TET
DAD
GOTO
RTENCK3D
RTENCK3 STQ CALL
RTENCKEX
INTSTALL
RTENCK3A VLOAD CLEAR
R(T1)/
INTYPFLG
RTENCK3B STOVL RCV
V2(T1)/ STODL VCV
T1 STODL TET
T2 # Page 916
RTENCK3D STORE TDEC1
CLEAR CALL
MOONFLAG
INTEGRVS
VLOAD
RATT STORE R(T2)/
PDDL LXC,1
TAT
CONICX1 STOVL T2
VATT STORE V(T2)/
GOTO
RTENCKEX SETLOC RTE BANK
# Page 917 # V2(T1) COMPUTATION SUBROUTINE # # DESCRIPTION # A POST IMPULSE VELOCITY VECTOR (V2(T1)) IS COMPUTED WHICH EITHER # (1) MEETS THE INPUT VELOCITY CHANGE DESIRED (RTEDVD) IN A MINIMUM TIME OR # (2) IF A VELOCITY CHANGE ISN'T SPECIFIED (RTEDVD = 0), A V2(T1) IS COMPUTED WHICH MINIMIZES THE IMPULSE (DV) # AND CONSEQUENTLY FUEL. # # CALLING SEQUENCE # L CALL # L+1 V2T100 # # NORMAL EXIT MODE # AT L+2 OF CALLING SEQUENCE WITH MPAC = 0 # # ALARM EXIT MODE # AT L+2 OF CALLING SEQUENCE WITH MPAC = OCTAL 605 FOR EXCESS ITERATIONS. # # SUBROUTINES CALLED # GAMDV10 # XT1LIM # DVCALC # # ERASABLE INITIALIZATION REQUIRED # PUSHLIST # NONE # MPAC # NONE # OTHER # R(T1) MAGNITUDE OF INITIAL POSITION VECTOR DP B29/B27 METERS # RCON MAGNITUDE OF FINAL POSITION VECTOR DP B29/B27 METERS # V(T1)/ INITIAL VELOCITY VECTOR VECTOR B7/B5 METERS/CS # RTEDVD DELTA VELOCITY DESIRED DP B7/B5 METERS/CS # UR1/ UNIT INITIAL VECTOR VECTOR B1 # UH/ UNIT HORIZONTAL VECTOR VECTOR B1 # X(T2) COTANGENT OF FINAL FLIGHT PATH ANGLE DP B0 # X(T1) COTANGENT OF INITIAL FLIGHT PATH ANGLE (INPUT FOR PREC) DP B5 # CFPA COSINE OF INITIAL FLIGHT PATH ANGLE DP B1 # MAMAX1 MAJOR AXIS LIMIT FOR LOWER BOUND ON GAMDV ITERATOR DP B30/B28 METERS # MAMAX2 MAJOR AXIS LIMIT FOR UPPER BOUND ON GAMDV ITERATOR DP B30/B28 METERS # PHI2 REENTRY NEAR PERIGEE OR APOGEE INDICATE (RTE ONLY) DP B2 -1 PERIGEE, +1 APOGEE # N1 CONIC OR PRECISION ITERATION OPERATOR DP B28 NEGATIVE CONIC, PLUS PREC # # OUTPUT # V2(T1)/ POST IMPULSE INITIAL VELOCITY VECTOR VECTOR B7/B5 METERS/CS # DV INITIAL VELOCITY CHANGE DP B7/B5 METERS/CS # X(T1) COTANGENT OF INITIAL FLIGHT PATH ANGLE (POST IMPULSE) DP B5 # PCON SEMI-LATUS RECTUM DP B28/B26 METERS # BETA1 1+X(T2)**2 DP B1 # # Page 918 # # DEBRIS # PUSHLIST # 00D X(T1),,=PREVIOUS PRECISION X(T1) DP B5 # 02D THETA1=BETA5*LAMBDA-1 TP B17 # 05D THETA2=2*R(T1)*(LAMBDA-1) TP B38/B36 # 08D THETA3=MU**.5/R(T1) DP B-4/B-5 # 10D X(T1)MIN=LOWER BOUND ON X(T1) IN GAMDV ITERATOR DP B5 # 12D DX(T1)MAX=MAXIMUM DELTA X(T1) DP B5 # 14D X(T1)MAX=UPPER BOUND ON X(T1) IN GAMDV ITERATOR DP B5 # 16D DX(T1)=ITERATOR INCREMENT DP B5 # 31D GAMDV10 SUBROUTINE RETURN ADDRESS # 32D DVCALC SUBROUTINE RETURN ADDRESS # 33D V2T100 SUBROUTINE RETURN ADDRESS
V2T102 DLOAD
RTEDVD
BZE GOTO
V2T105
V2T140
V2T105 DLOAD BMN
CFPA
V2T140
GOTO
V2T145 # Page 920 # DURING A PRECISION TRAJECTORY ITERATION CONSTRAIN THE INDEPENDENT # VARIABLE TO INSURE THAT ALL CONICS PASS THROUGH RCON ON THE SAME PASS # THROUGH X(T2)
