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Proof-read Comanche055\P40-P47 (pg. 0700-0715)

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arda-guler 2021-11-15 19:43:08 +03:00
parent 4ed1904211
commit c6df2f3b02
1 changed files with 48 additions and 65 deletions
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43
Comanche055/P40-P47.agc
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@ -750,7 +750,6 @@ UPDATEVG STQ BON
NBRCYCLS
SETUP.9
# Page 700
VLOAD VAD
DELVSUM
DELVREF
@ -760,7 +759,7 @@ UPDATEVG STQ BON
AD NBRCYCLS
TS NBRCYCLP
TC PHASCHNG # TYPE B RESTART RESTART BELOW AND 5.3 REREADACCS
TC PHASCHNG # TYPE B RESTART BELOW AND 5.3 REREADACCS
OCT 10035
CA NBRCYCLP
@ -913,7 +912,7 @@ SETUPDYN CAF PRIO27 # SET UP A JOB TO UPDATE N85 (FOR P41=V06)
TCF SETTB6 # CLOSE OUT CLOCKTASK
# Page 704
DYNDISP TC INTPRET # UPDATE N85 FOR A DYNAMIC V06N85 IN P41.
DYNDISP TC INTPRET # UPDATE N85 FOR A DYNAMIC V06N85 IN P41,
CALL # PRIOR TO BLANKING AND AVEG (V16N85)
P40CNV85
EXIT
@ -945,7 +944,7 @@ FAILDSP CAF V06N40 # SPS ENGINE-FAILED V97 FLASH
ENGREQST CAF V06N40
TC BANKCALL
CADR CLOCPLAY # LINUS MAKES IT A REDO, INHINT OK
CADR CLOCPLAY
TCF V99T # TERMINATE
TCF V99P # PROCEED
TCF V99E # ENTER
@ -1039,6 +1038,7 @@ V97TRCS TC IBNKCALL # RCS DAP IN 0.6SEC, SETTING T5 BITS TO
ENDV97T TCF TASKOVER
EBANK= V97VCNTR
V97P TC PHASCHNG
OCT 40734 # A, 4.73 = V97PTASK (-0 CS), TBASE NOW
@ -1071,6 +1071,7 @@ R40ENABL TC DOWNFLAG # RE-ENABLE R40 BY CLEARING IDLEFAIL
# Page 708
ENDV97P TCF TASKOVER
EBANK= WHOCARES
V97E TC PHASCHNG
OCT 40534 # A, 4.53 = V97ETASK (-0 CS), TBASE NOW
@ -1108,7 +1109,6 @@ V97E40.6 CAF BIT1
TC IBNKCALL # RCS DAP IN 0.6SEC, SETTING T5 BITS TO
CADR RCSDAPON # KILL TVCEXEC/TVCROLLDAP STARTS.
# LEAVE NARROW DEADBAND FOR REIGNITE.
TC 2PHSCHNG
OCT 00026 # A, 6.2 = PRE40.6 (-0 CS), CLOKTASK (1SEC)
OCT 05014 # C, DELTAT NEXT, TASK BELOW, IN
@ -1141,28 +1141,23 @@ ENDV97E TCF TASKOVER # WAIT FOR CLOCKJOB (IMMEDIATE) REACTION
# FUNCTIONAL DESCRIPTION
# COMPUTE INITIAL THRUST DIRECTION(UT) AND INITIAL VALUE OF VG
# VECTOR(VGTIG).
#
# CALLING SEQUENCE
# L CALL
# L+1 S40.1
#
# NORMAL EXIT MODE
# AT L+2 OF CALLING SEQUENCE (GOTO L+2) NORMAL RETURN OR
# ERROR RETURN IF NOSOFLAG =1
#
# SUBROUTINES CALLED
# CSMPREC
# INITVEL
# CALCGRAV
# MIDGIM
#
# ALARM OR ABORT EXIT MODES
# L+2 OF CALLING SEQUENCE,UNSOLVABLE CONIC IF NOSOFLAG=1
#
# ERASABLE INITIALIZATION REQUIRED
# WEIGHT/G ANTICIPATED VEHICLE MASS SP B16KGM
# XDELVFLG 1=DELTA-V MANEUVER,0=AIMPT STEER
# IF DELTA-V MANEUVER:
# IF DELTA-V MANEUVER
# DELVSIN SPECIFIED DELTA-V REQUIRED IN
# INERTIAL COORDS. OF ACTIVE VEHICLE
# AT TIME OF IGNITION VECTOR B7M/CS
@ -1170,14 +1165,13 @@ ENDV97E TCF TASKOVER # WAIT FOR CLOCKJOB (IMMEDIATE) REACTION
# RTIG POSITION AT TIME OF IGNITION VECTOR B29M
# VTIG VELOCITY AT TIME OF IGNITION VECTOR B7M/CS.
# CSTEER = 0 DP
# IF AIMPOINT STEERING:
# IF AIMPOINT STEERING
# IF AIMPT STEER
# TIG TIME OF IGNITION DP B28CS
# RTARG POSITION TARGET TIME VECTOR B29M
# CSTEER = ECSTEER(GR 0) DP B1
# Page 710
# TPASS4 -- TIME OF ARRIVAL AT AIMPOINT
#
# TPASS4 - TIME OF ARRIVAL AT AIMPOINT
# OUTPUT
# UT 1/2 UNIT VECTOR ALIGNED WITH THRUST DIRETION IN REF COOR
# VGTIG INITIAL VALUE OF VELOCITY
@ -1188,7 +1182,6 @@ ENDV97E TCF TASKOVER # WAIT FOR CLOCKJOB (IMMEDIATE) REACTION
# -GDT FOR S40.13 VECT B7M/CS
# RTIG CALC IN S40.1B (AIMPT) FOR S40.2,3 VECTOR B29M
# POSITION AT TIME OF IGNITION
#
# DEBRIS QTEMP1
# MPAC, QPRET
# PUSHLIST
@ -1246,7 +1239,7 @@ S40.1 SET VLOAD
VXV UNIT
UT
VXSC STADR
STOVL VGTIG # UNIT(VP X UP)SIN(THETAT/2) IN VGTIG.
STOVL VGTIG # UNIT(VP X UP)SIN(THETAT) IN VGTIG.
UNIT PDDL # UNIT(DELTA VP) IN P.D.L. 6
14D
COS VXSC
@ -1360,7 +1353,7 @@ CALCUT VLOAD CALL
SRR DDV
4
WEIGHT/G
DSQ PDVL # F/MASS SQUARED PDL 6 AT 2(-10M/(CS.CS)
DSQ PDVL # F/MASS SQUARED PDL 6 AT 2(-10)M/(CS.CS)
12D
VSQ
BDSU SQRT
@ -1372,54 +1365,44 @@ CALCUT VLOAD CALL
200CS 2DEC 200 B-12
# Page 714
# PROGRAM DESCRIPTION S40.2,3 DATE 15 NOV 66
# PROGRAM DESCRIPTION S40.2,3 DATE 15,NOV,66
# MOD NO 2 LOG SECTIONS P40-P47
# MOD BY ZELDIN
#
# FUNCTIONAL DESCRIPTION
#
# COMPUTE GIMBAL ANGLES IF THRUSTING OCCURRED WITH PRESENT IMU
# ORIENTATION, WINGS LEVEL SPACECRAFT,HEADS UP
# COMPUTE X AXIS OF ENGINE BELL
# COMPUTE PREFERRED IMU ORIENTATION(XSCREF)
# FOR THIS CALCULATION,ASSUME X AXIS OF SC ALONG UT INITIALLY,
# YSC=UNIT(XXR), ZSC=UNIT(XX(XXR)) AND ROTATE ENGINE BELL ALONG UT.
# YSC=UNIT(XXR),ZSC=UNIT(XX(XXR)) AND ROTATE ENGINE BELL ALONG UT
# NEW SC AXES WILL BE APPROX. WINGS LEVEL AND NEW SC AXES IN REF.
# COORDS. WILL BE PREFERRED IMU ORIENTATION.
# COMPUTE DESIRED THRUST DIRECTION IN SM COORDS.
#
# CALLING SEQUENCE
# L CALL
# L+1 S40.2,3
#
# NORMAL EXIT MODE
# AT L+2 OF CALLING SEQUENCE (GOTO L+2)
#
# SUBROUTINES CALLED
# CALCGA
#
# ALARM OR ABORT MODES
# NONE
#
# ERASABLE INITIALIZATION REQUIRED
# PACTOFF TOTAL PITCH TRIM ANGLE SP AT 1.0795111 REV.
# YACTOFF TOTAL YAW TRIM ANGLE SP AT 1.0795111 REV.
# UT DESIRED THRUST DIRECTION VECT.B2M/(CS.CS)
# RTIG POSITION AT TIME OF IGNITION VECT. B29M
# ENG2FLAG ON=RCS OFF=SPS
#
# OUTPUT
# SCAXIS UNIT VECT. ALIGNED WITH ENG BELL IN SC COOR. B1
# SCAXIS UNIT VECT. ALIGNED WITH ENG BELL IN SC COOR B1
# XSCREF UNIT VECTORS ALIGNED WTH PREFERRED IMU B1
# YSCREF
# ZSCREF
# GIMBAL ANGLES IN THETAD
# POINTVSM UNIT VECT ALONG DESIRED THRUST DIRECTION IN SM B1
#
# DEBRIS
# PUSHLIST,QPRET,MPAC
# QTEMP TEMP. ERASABLE
BANK 24
SETLOC P40S
BANK