https://github.com/virtualagc/virtualagc
Revision 3577d0b1de1ac147c1710524517c563b2bfe231c authored by Ronald Burkey on 30 May 2021, 19:14:00 UTC, committed by GitHub on 30 May 2021, 19:14:00 UTC
Issue 1143: Fix various symbol name and other minor typos
Tip revision: 3577d0b1de1ac147c1710524517c563b2bfe231c authored by Ronald Burkey on 30 May 2021, 19:14:00 UTC
Merge pull request #1147 from smithery1/Issue/1143
Merge pull request #1147 from smithery1/Issue/1143
Tip revision: 3577d0b
PADLOADS.agc
### FILE="Main.annotation"
## Copyright: Public domain.
## Filename: PADLOADS.agc
## Purpose: The main source file for Luminary revision 069.
## It is part of the source code for the original release
## of the flight software for the Lunar Module's (LM) Apollo
## Guidance Computer (AGC) for Apollo 10. The actual flown
## version was Luminary 69 revision 2, which included a
## newer lunar gravity model and only affected module 2.
## This file is intended to be a faithful transcription, except
## that the code format has been changed to conform to the
## requirements of the yaYUL assembler rather than the
## original YUL assembler.
## Reference: pp. 37-52
## Assembler: yaYUL
## Contact: Ron Burkey <info@sandroid.org>.
## Website: www.ibiblio.org/apollo/index.html
## Mod history: 2016-12-13 MAS Created from Luminary 99.
## 2016-12-20 MAS Began transcription.
## 2016-12-23 MAS Completed transcription.
## 2017-01-25 RSB Proofed comment text using octopus/prooferComments
## and fixed errors found.
## Page 37
# ****** FORMAT ******
# NAMETAG LENGTH TYPE ?? (GSOP NAME) PROGRAMS SAMPLE VALUE / UNITS
# DESCRIPTION
# MORE DESCRIPTION
# INCRE PRESENT ESTIMATED LGC SCALING SOURCE OF VALUE
# -MENT LENGTH AND VALUE
# ????? POSSIBLE TYPES ?????
# HOW INITIATED: P = PADLOADED
# U = UPLINKED
# D = DSKY (ASTRONAUT)
# IF MODIFIED, HOW: (I) = INVARIANT
# (PGM)= PROGRAM GENERATED
# (F) = FRESH START REINITIALIZED
# (U) = UPLINKED
# (D) = DSKY (ASTRONAUT)
#
# ****** EXAMPLE ******
# FREAKOUT (2D) P(I) (F-OMEGA) P88'S-RENDESVOUS AVOIDANCE (2 MICROGRAMS)
# RESULTANT QUANTITY AFTER LONG EXPOSURE
# TO A 'STATUS QUO' PHILOSOPHY
# +0 1OCT 00534 E3 B-12 (SUN)LITE DAWNS
# +1 1OCT 07381 E-4 B-12
#
# *************
#
# FLGWRD10 (1D) P(PGM) MANY PROGRAMS, DAP-R03 (00000 FOR DESCENT, 10000 FOR ASCENT )
# MUST BE SET TO ONE VALUE OR OTHER DEPEND
# ING ON MISSION PHASE BECAUSE APSFLAG IS
# NOT INITIALIZED IN FRESH START AS ARE
# OTHER FLAGBITS. MUST USE DSKY OR R03
# OCT 00000
#
# FLAGWRD3 (1D) P(PGM) MANY PROGRAMS (10000 FOR REFSMMAT GOOD; 00000 FOR NO
# GOOD) REFSMFLG IS NOT INITIALIZED BY
# FRESH START AS OTHER BITS ARE.
# OCT 00000
# OR OCT 10000
#
## Page 38
# FLAGWRD8 (1D) P(PGM) MANY PROGRAMS (THERE ARE 8 POSSIBLE CONFIGURATIONS)
# CMOON, LMOON, & SURFFLAG ARE NOT INITIAL
# IZED BY FRESH START AS OTHER BITS ARE.
# OCT; BITS 8,11,12 NEED TO BE SET AS YOU DESIRE
#
# HIASCENT (1D) P(F) (HIASCENT) DIGITAL AUTOPILOT (5000 KG.; 11,100 LBS.)
# INITIAL STAGED MASS
# 1DEC 5050 B-16 SUNLITER # 147
#
# DKTRAP (1D) P(F) (-THETA-MAX-C) DAP STATE ESTIMATOR PARAM. (.14 DEG SCALED AT 4.5 DEG OR -510 DEC)
# LEM-CSM DOCKED, THRESHOLD FOR MEASURE-
# MENT INCORPORATION
# 1OCT 77001 R557 GSOP SEC 3.3.2.3 JUNE68
#
# DKOMEGAN (1D) P(F) (N-OMEGA-C) DAP STATE ESTIMATOR PARAM. ( 10 DEC )
# LEM-CSM DOCKED, RATE GAIN CONSTANT
# 1OCT 00012 R557 GSOP SEC 3.3.2.3 JUNE68
#
# DKKAOSNN (1D) P(F) (N-ALPHA-C) DAP STATE ESTIMATOR PARAM. ( 60 DEC )
# LEM-CSM DOCKED, ACCELERATION GAIN
# CONSTANT
# 1OCT 00074 R557 GSOP SEC 3.3.2.3 JUNE68
#
# LMTRAP (1D) P(F) (-THETA-MAX-L) DAP STATE ESTIMATOR PARAM. (.14 DEG SCALED AT 4.5 DEG )
# LEM-ALONE, THRESHOLD FOR MEASUREMENT
# INCORPORATION
# 1OCT 77001 R557 GSOP SEC 3.3.2.3 JUNE68
#
# LMOMEGAN (1D) P(F) (N-OMEGA-L) DAP STATE ESTIMATOR PARAM. ( 0 DEC )
# LEM-ALONE, RATE GAIN CONSTANT
# 1OCT 00000 R557 GSOP SEC 3.3.2.3 JUNE68
#
# LMKAOSN (1D) P(F) (N-ALPHA-L) DAP STATE ESTIMATOR PARAM. ( 60 DEC )
# LEM-ALONE, ACCELERATION GAIN CONSTANT
# 1OCT 00074 R557 GSOP SEC 3.3.2.3 JUNE68
#
# DKDB (1D) P(F) DAP ( 1.4 DEGREES EXPRESSED IN RADIANS )
# WIDTH OF DEADBAND FOR DOCKED RCS AUTO-
# PILOT (PI/DKDB RADIANS = DEADBAND)
# 1OCT 00200 LUMINARY ERASABLES
#
## Page 39
# ROLLTIME (1D) P(D) (R-TRIM) D.A.P. AND R03 ( 3000 CENTISECONDS OR 30 SECS. )
# TIME TO TRIM DESCENT Z GIMBAL (ROLL)
# 1DEC 3000 SUNDANCE PADLOAD MEMO
#
# PITTIME (1D) P(D) (P-TRIM) D.A.P. AND R03 ( 3000 CENTISECONDS OR 30 SECS. )
# TIME TO TRIM DESCENT Z GIMBAL (ROLL)
# 1DEC 3000 SUNDANCE PADLOAD MEMO
#
# POSTORKP (1D) P(PGM) (POSTORKP) DAP ACCUMULATED JET TORQUE ABOUT +P AXIS
# SCALED AT 32 JET-SEC, OR ABOUT 2.0 JET-
# 1OCT 00000 PCR 616 MSEC PER BIT. PERMITTED TO OVERFLOW.
#
# NEGTORKP (1D) P(PGM) (NEGTORKP) DAP ACCUMULATED JET TORQUE ABOUT -P AXIS
# SCALED AS POSTORKP.
# 1OCT 00000 PCR 616
#
# POSTORKU (1D) P(PGM) (POSTORKU) DAP ACCUMULATED JET TORQUE ABOUT +U AXIS
# SCALED AS POSTORKP.
# 1OCT 00000 PCR 616
#
# NEGTORKU (1D) P(PGM) (NEGTORKU) DAP ACCUMULATED JET TORQUE ABOUT -U AXIS
# SCALED AS POSTORKP.
# 1OCT 00000 PCR 616
#
# POSTORKV (1D) P(PCM) (POSTORKV) DAP ACCUMULATED JET TORQUE ABOUT +V AXIS
# SCALED AS POSTORKP
# 1OCT 00000 PCR 616
#
# ZOOMTIME (1D) P(2) (TAU-T) P40'S , LUNAR LANDING ( 26 SEC )
# TIME BETWEEN ENGINE ON AND THROTTLE UP
# COMMAND IN ANY DPS BURN
# 1DEC 2600 CSEC. SUNDANCE PADLOAD MEMO
#
# MASS (2D) P(U) (M) ALL P40'S, SERVICER (FULL LOADED VALUE APPROX. 15,043.8 KG.)
# VALUE FOR DESCENT STAGE WITH VARYING
# FUEL LOADS
# 2DEC B-16
#
# PIPASCFX (1D) P(I) (SFE1) IMU COMPENSATION PARAMETERS ( PARTS PER MILLION)
# SCALE FACTOR ERROR CORRECTION FACTOR
# 1OCT 75155 B-9 SUNDANCE PADLOAD MEMO
## Page 40
#
# PIPASCFY (1D) P(I) (SFE2) IMU COMPENSATION PARAMETERS ( PARTS PER MILLION)
# SCALE FACTOR ERROR CORRECTION FACTOR
# 1OCT 77403 B-9 SUNDANCE PADLOAD MEMO
#
# PIPASCFZ (1D) P(I) (SFE3) IMU COMPENSATION PARAMETERS ( PARTS PER MILLION)
# SCALE FACTOR ERROR CORRECTION FACTOR
# 1OCT 65532 B-9 SUNDANCE PADLOAD MEMO
#
# PBIASX (1D) P(I) (BIAS1) IMU COMPENSATION PARAMETERS (PIPA PULSES PER CSEC OR CM PER SEC**2 )
# PIPA BIASES
# 1OCT 04554 B-5 SUNDANCE PADLOAD MEMO
#
# PBIASY (1D) P(I) (BIAS2) IMU COMPENSATION PARAMETERS (PIPA PULSES PER CSEC OR CM PER SEC**2 )
# PIPA BIASES
# 1OCT 06433 B-5 SUNDANCE PADLOAD MEMO
#
# PBIASZ (1D) P(I) (BIAS3) IMU COMPENSATION PARAMETERS (PIPA PULSES PER CSEC OR CM PER SEC**2 )
# PIPA BIASES
# 1OCT 77220 B-5 SUNDANCE PADLOAD MEMO
#
# ADIAX (1D) P(I) (ADIAX) IMU COMPENSATION PARAMETERS ( GYRO PULSES PER PIPA PULSE)
# (MILLI-EARTH-RATE UNIT (MERU) / GRAVITY)
# GYRO DRIFTS DUE TO ACCELERATION ALONG
# INPUT AXIS
# 1OCT 00436 B-6 SUNDANCE PADLOAD MEMO
#
# ADIAY (1D) P(I) (ADIAY) IMU COMPENSATION PARAMETERS ( GYRO PULSES PER PIPA PULSE)
# (MILLI-EARTH-RATE UNIT (MERU) / GRAVITY)
# GYRO DRIFTS DUE TO ACCELERATION ALONG
# INPUT AXIS
# 1OCT 76277 B-6 SUNDANCE PADLOAD MEMO
#
# ADIAZ (1D) P(I) (ADIAZ) IMU COMPENSATION PARAMETERS ( GYRO PULSES PER PIPA PULSE)
# (MILLI-EARTH-RATE UNIT (MERU) / GRAVITY)
# GYRO DRIFTS DUE TO ACCELERATION ALONG
# INPUT AXIS
# 1OCT 00064 B-6 SUNDANCE PADLOAD MEMO
#
# ADSRAX (1D) P(I) (ADSRAX) IMU COMPENSATION PARAMETERS ( GYRO PULSES PER PIPA PULSE)
# (MILLI-EARTH-RATE UNIT (MERU) / GRAVITY)
## Page 41
# GYRO DRIFTS DUE TO ACCELERATION ALONG
# SPIN REFERENCE AXIS
# 1OCT 00064 B-6 SUNDANCE PADLOAD MEMO
#
# ADSRAY (1D) P(I) (ADSRAY) IMU COMPENSATION PARAMETERS ( GYRO PULSES PER PIPA PULSE)
# (MILLI-EARTH-RATE UNIT (MERU) / GRAVITY)
# GYRO DRIFTS DUE TO ACCELERATION ALONG
# SPIN REFERENCE AXIS
# 1OCT 00116 B-6 SUNDANCE PADLOAD MEMO
#
# ADSRAZ (1D) P(I) (ADSRAZ) IMU COMPENSATION PARAMETERS ( GYRO PULSES PER PIPA PULSE)
# (MILLI-EARTH-RATE UNIT (MERU) / GRAVITY)
# GYRO DRIFTS DUE TO ACCELERATION ALONG
# SPIN REFERENCE AXIS
# 1OCT 00064 B-6 SUNDANCE PADLOAD MEMO
#
# NBDX (1D) P(I) (NBDX) IMU COMPENSATION PARAMETERS ( GYRO PULSES PER CSEC.)
# OR (MILLI-EARTH-RATE UNIT CALLED 'MERU')
# GYRO BIAS DRIFTS
# 1OCT 77332 B-5 SUNDANCE PADLOAD MEMO
#
# NBDY (1D) P(I) (NBDY) IMU COMPENSATION PARAMETERS ( GYRO PULSES PER CSEC.)
# OR (MILLI-EARTH-RATE UNIT CALLED 'MERU')
# GYRO BIAS DRIFTS
# 1OCT 77415 B-5 SUNDANCE PADLOAD MEMO
#
# NBDZ (1D) P(I) (NBDZ) IMU COMPENSATION PARAMETERS ( GYRO PULSES PER CSEC.)
# OR (MILLI-EARTH-RATE UNIT CALLED 'MERU')
# GYRO BIAS DRIFTS
# 1OCT 00000 B-5 SUNDANCE PADLOAD MEMO
#
# WRENDPOS (1D) P(D-V67) (W-RR) P20 - RENDEZVOUS NAVIGATION (2440 METERS)
# W-MATRIX INERTIAL DIAGONAL ELEMENT
# PRESELECTED ERROR TRANSITION
# VALUE UNCERTAIN
#
# WRENDVEL (1D) P(D-V67) (W-RV) P20 - RENDEZVOUS NAVIGATION ( .0244 METERS PER CSEC.)
# W-MATRIX INERTIAL DIAGONAL ELEMENT
# PRESELECTED ERROR TRANSITION
# VALUE UNCERTAIN
#
# WSHAFT (1D) P(I) (W-THETA) P20-RENDESVOUS NAVIGATION ( 10 MILLIRADIANS)
## Page 42
# W-MATRIX INERTIAL DIAGONAL ELEMENT
# SHAFT PRESELECTED ERROR TRANSITION
# VALUE UNCERTAIN
#
# WTRUN (1D) P(I) (W-BETA) P20-RENDESVOUS NAVIGATION ( 10 MILLIRADIANS -MR- )
# W-MATRIX INERTIAL DIAGONAL ELEMENT
# TRUNNIUN PRESELECTED ERROR TRANSITION
# VALUE UNCERTAIN
#
# RMAX (1D) P(I) (DELTA-RMAX) P20-RENDESVOUS NAVIGATION ( 9.26 TIMES 10 TO 4TH POWER)
# THRESHOLD LIMIT FOR POSITION CORRECTION
# VALUE UNCERTAIN
#
# VMAX (1D) P(I) (DELTA-VMAX) P20-RENDESVOUS NAVIGATION (9.144 TIMES 10 METERS PER SECOND)
# THRESHOLD LIMIT FOR VELOCITY CORRECTION
# VALUE UNCERTAIN
#
# SHAFTVAR (1D) P(U) (VAR-BETA) P22-RENDESVOUS RADAR ( 10 TO 6TH POWER SQUARE RADIANS)
# RR SHAFT ANGLE ERROR VARIANCE
# VALUE UNCERTAIN
#
# TRUNVAR (1D) P(U) (VAR-THETA) P22-RENDESVOUS RADAR ( 10 TO 6TH POWER SQUARE RADIANS)
# RR TRUNNION ANGLE ERROR VARIANCE
# VALUE UNCERTAIN
#
# WSURFPOS (1D) P(D-V67) (W-LR) P20'S-LUNAR SURFACE NAVIGAT
#
# W-MATRIX INERTIAL DIAGONAL ELEMENT
# LUNAR ANALOG OF WRENPOS
#
# WSURFVEL (1D) P(D-V67) (W-LV) P20'S-LUNAR SURFACE NAVIGAT
#
# W-MATRIX INERTIAL DIAGONAL ELEMENT
# LUNAR ANALOG OF WRENVEL
#
# RANGEVAR (2D) P(I) (VAR-R)) P20 NAVIGATION'S STATE VECTOR INCORPORATION ROUTINE
# (1/3 % QUANTITY SQUARED OR .11111111 E-4
# RANGE ERROR VARIANCE CORRESPONDING TO
# A PERCENTAGE ERROR
# 2DEC* .111111111 E-4 B12* GSOP
#
## Page 43
# RATEVAR (2D) P(I) (VAR-V)) P20 NAVIGATION'S STATE VECTOR INCORPORATION ROUTINE
# (1.3/3 % QUANTITY SQUARED OR 1.8777 E-5
# VELOCITY ERROR VARIANCE CORRESPONDING TO
# A PERCENTAGE ERROR
# 2DEC 1.87777 E-5 B12 GSOP
#
# RVARMIN (1D) P(I) (VAR-RMIN) P20 NAVIGATION'S STATE VECTOR INCORPORATION ROUTINE
# (80/3 FT QUANTITY SQUARED)
# MIN. RENDESVOUS RADAR POSITION VARIANCE
# 1DEC 66.0 B-12 METERS**2 GSOP
#
# VVARMIN (1D) P(I) (VAR-VMIN) P20 NAVIGATION'S STATE VECTOR INCORPORATION ROUTINE (METERS/CSEC)**2
# (1.3 /3 FT PER SEC QUANTITY SQUARED)
# MINIMUM VELOCITY VARIANCE
# DEC .17445 E-5 B12 GSOP
#
# X789 (6D) P(PGM) (DELTA-BETA,DELTA-THETA,ZERO) P20S, MEAS.INCORP2 (MILLIRADIANS)
# 7,8,9TH COMPONENT NAVIGATION STATEVECTOR
# ALSO SHAFT + TRUNNION BIAS ESTIMATES
# +0 2DEC 0 INITIALLY
# +2 2DEC 0 INITIALLY LUMINARY LISTING
# +4 2DEC 0 ALWAYS
#
# ATIGINC (2D) P(I) (DELTA-TAU-3) P35 ( 7 MINUTES )
# ACTIVE VEHICLE TIME REQUIRED TO PREPARE
# FOR A TPM MANEUVER
# 2DEC 42000 B-28 (CSEC) SUNDANCE PADLOAD MEMO
#
# PTIGINC (2D) P(I) (DELTA-TAU-7) P75 (12 MINUTES )
# PASSIVE VEHICLE TIME REQUIRED TO PREPARE
# FOR A TPM MANEUVER
# 2DEC 72000 B-28 (CSEC) SUNDANCE PADLOAD MEMO
#
# AOTAZ (3D) P(I) (AZ1,AZ2,AZ3) AOTMARK (ALIGNMENT OPTICAL TELESCOPE) (-60 DEG, 0, +60 DEG)
# ANGLES BETWEEN THE LM NAVIGATION BASE Z
# AXIS AND AOT LINE OF SIGHT FOR DETENT1,
# 2,3. (AZIMUTH, 3 FORWARD VIEWING POSIT.)
# +0 OCT 65252
# +1 OCT 0 SUNDANCE PADLOAD MEMO
# +2 OCT 12525
#
# AOTEL (3D) P(I) (EL1,EL2,EL3) AOTMARK (ALIGNMENT OPTICAL TELESCOPE) (EACH IS 45 DEGREES)
# ANGLES BETWEEN THE LM NAVIGATION BASE
## Page 44
# Y-Z PLANE & AOT LINE OF SIGHT FOR
# DETENT1,2,3. (ELEVATION, 3 FORWARD POS.)
# +0 OCT 10000
# +1 OCT 10000 SUNDANCE PADLOAD MEMO
# +2 OCT 10000
#
# DUMPCNT (1D) P(I) DOWNLINK TELEMETRY HOLDS THE NUMBER 'N' INDICATING THAT A
# DOWNLINK ERASABLE DUMP WILL SEND ALL OF
# ERASABLE STORAGE N TIMES (N=1 TO 4)
# OCT 20000 IF 4 ERASABLE DUMPS DESIRED
# OCT 10000 IF 2 COMPLETE DUMPS DESIRED LUMINARY
# OCT 04000 IF 1 COMPLETE ERASABLE DUMP LISTING
#
# AGSK (2D) P(U) V47(R47) AGS INITIALIZATION ( MINS ?)
# GROUND ELAPSED TIME OF LATEST AGS CLOCK
# ZERO
#
# RBRFG (6D) P(I) (R-OFG) LUNAR LANDING TARGET PARAMETERS ( METERS )
# RANGE VECTOR, BRAKING PHASE, HIGHGATE
# +0 2DEC* +2.92362643 E+ 3 B-24 *
# +2 2DEC* +0.00000000 E+ 0 B-24 * 23A LUMAR LANDING PGM
# +4 2DEC* -1.00839629 E+ 4 B-24 *
#
# VBRFG (6D) P(I) (V-OFG) LUNAR LANDING TARGET PARAMETERS ( METERS PER CSEC )
# VELOCITY VECTOR, BRAKING PHASE, HIGHGATE
# +0 2DEC* -4.83907728 E- 1 B-10 *
# +2 2DEC* +0.00000000 E+ 0 B-10 * 23A LUNAR LANDING PGM
# +4 2DEC* +1.71785605 E+ 0 B-10 *
#
# ABRFG (6D) P(I) (A-OFG) LUNAR LANDING TARGET PARAMETERS ( METERS PER CSEC SQUARED ) HIGHGATE
# ACCELERATION VECTOR, BRAKING PHASE
# +0 2DEC* -5.22722473 E- 5 B+04 *
# +2 2DEC* +0.00000000 E+ 0 B+04 * 23A LUNAR LANDING PGM
# +4 2DEC* -2.86621213 E- 4 B+04 *
#
# VBRFG* (2D) P(I) LUNAR LANDING TARGET PARAMETERS ( METERS PER CSEC )
# VELOCITY SCALAR, BRAKING PHASE, HIGHGATE
# 2DEC* +3.86517612 E+ 0 B-10 * 23A LUNAR LANDING PGM
#
# ABRFG* (2D) P(I) LUNAR LANDING TARGET PARAMETERS ( METERS PER CSEC SQUARED ) HIGH GATE
# ACCELERATION SCALAR, BRAKING PHASE
# 2DEC* -1.71972727 E- 3 B+04 * 23A LUNAR LANDING PGM
#
## Page 45
# JBRFG* (2D) P(I) (J-OFZG) LUNAR LANDING TARGET PARAMETERS ( METERS PER CSEC CUBED )
# JERK SCALAR, BRAKING PHASE, HIGHGATE
# 2DEC* -2.90216724 E- 8 B+18 * 23A LUNAR LANDING PGM
#
# RAPFG (6D) P(I) (R-1FG) LUNAR LANDING TARGET PARAMETERS ( METERS )
# RANGE VECTOR, APPROACH PHASE, LOWGATE
# +0 2DEC* +2.35092239 E+ 1 B-24 *
# +2 2DEC* +0.00000000 E+ 0 B-24 * 23A LUNAR LANDING PGM
# +4 2DEC* -5.28319999 E- 1 B-24 *
#
# VAPFG (6D) P(I) (V-1FG) LUNAR LANDING TARGET PARAMETERS ( METERS PER CSEC )
# VELOCITY VECTOR, APPROACH PHASE, LOWGATE
# +0 2DEC* -9.44879999 E- 3 B-10 *
# +2 2DEC* +0.00000000 E+ 0 B-10 * 23A LUNAR LANDNNG PGM
# +4 2DEC* +3.96239999 E- 3 B-10 *
#
# AAPFG (6D) P(I) (A-1FG) LUNAR LANDING TARGET PARAMETERS ( METERS PER CSEC SQUARED ) LOW GATE
# ACCELERATION VECTOR, APPROACH PHASE
# +0 2DEC* +1.52399999 E- 6 B+04 *
# +2 2DEC* +0.00000000 E+ 0 B+04 * 23A LUNAR LANDING PGM
# +4 2DEC* -1.98119999 E- 5 B+04 *
#
# VAPFG* (2D) P(I) LUNAR LANDING TARGET PARAMETERS ( METERS PER CSEC )
# VELOCITY SCALAR, APPROACH PHASE, LOWGATE
# 2DEC* +8.91539999 E- 3 B-10 * 23A LUNAR LANDING PGM
#
# AAPFG* (2D) P(I) LUNAR LANDING TARGET PARAMETERS ( METERS PER CSEC SQUARED ) LOW GATE
# ACCELERATION SCALAR, APPROACH PHASE
# 2DEC* -1.18871999 E- 4 B+04 * 23A LUNAR LANDING PGM
#
# JAPFG* (2D) P(I) (J-1FZG) LUNAR LANDING TARGET PARAMETERS ( METERS PER CSEC CUBED )
# JERK SCALAR, APPROACH PHASE, LOWGATE
# 2DEC* +8.37249023 E- 8 B+18 * 23A LUNAR LANDING PGM
#
# VIGN (2D) P(I) (V-IGG) LUNAR LANDING TARGET PARAMETERS (16.99 METERS PER SECOND )
# DESIRED SPEED FOR IGNITION
# 2DEC* +1.69952182 E+ 1 B-10 * 23A LUNAR LANDING PGM
#
# RIGNX (2D) P(I) (R-IGXG) LUNAR LANDING TARGET PARAMETERS ( 40127 METERS )
# DESIRED X-COMPONENT IN GUIDANCE COORDIN-
# ATES FOR IGNITION ("ALTITUDE")
# 2DEC* -4.09432231 E+ 4 B-24 * 23A LUNAR LANDING PGM
## Page 46
#
# RIGNZ (2D) P(I) (R-IGZG) LUNAR LANDING TARGET PARAMETERS ( 437347 METERS )
# DESIRED Z-COMPONENT IN GUIDANCE COORDIN-
# ATES FOR IGNITION ("GROUND RANGE")
# 2DEC* -4.40014934 E+ 5 B-24 * 23A LUNAR LANDING PGM
#
# KIGNX/B4 (2D) P(I) (K-X) LUNAR LANDING TARGET PARAMETERS
# IGNITION ALGORITHM SENSITIVITY COEF.
# 2DEC -.022499999 23A LUNAR LANDING PGM
#
# KIGNY/B8 (2D) P(I) (K-Y) LUNAR LANDING TARGET PARAMETERS
# IGNITION ALGORITHM SENSITIVITY COEF.
# 2DEC -.174716605 23A LUNAR LANDING PGM
#
# KIGNV/B4 (2D) P(I) (K-V) LUNAR LANDING TARGET PARAMETERS
# IGNITION ALGORITHM SENSITIVITY COEF.
# 2DEC -.165939331 23A LUNAR LANDING PGM
#
# LOWCRIT (1D) P(I) LUNAR LANDING TARGET PARAMETERS (2.7 LBS/BIT) (57% NOMINAL MAX THRUST )
# LOWER LIMIT BEYOND WHICH THROTTLE SET TO
# EITHER MAXIMUM OR TRUE VALUE
# 1OCT 04251
#
# HIGHCRIT (1D) P(I) LUNAR LANDING TARGET PARAMETERS ( LBS / BIT : 63% NOMINAL MAX THRUST)
# UPPER LIMIT BEYOND WHICH THROTTLE SET TO
# EITHER MAXIMUM OR TRUE VALUE ?
# 1OCT 04622
#
# TENDAPPR (1D) P(I) LUNAR LANDING TARGET PARAMETERS ( 10 SECONDS )
# TIME CRITERION FOR SWITCHING OUT OF
# APPROACH PHASE QUADRATIC GUIDANCE
# DEC +10 E2 B-17 (BOTH ONEAND TWO-PHASE)
# LUM MEMO # 45
# TENDBRAK (1D) P(I) LUNAR LANDING TARGET PARAMETER ( 200 SECONDS )
# TIME CRITERION FOR SWITCH TO APPROACH
# PHASE (P64 )
# DEC +20 E2 B-17 (TWO-PHASE LANDING MODE) LUM MEMO
# DEC +200 E2 B-17 (ONE-PHASE LANDING MODE) #45
#
# RPCRTIME (1D) P(I) LUNAR LANDING TARGET PARAMETERS (300 SECONDS )
# TIME CRITERION FOR REPOSITIONING LR
## Page 47
# ANTENNA
# DEC +5 E2 B-17 (TWO-PHASE LANDING MODE) LUM MEMO
# DEC +300 E2 B-17 (ONE-PHASE LANDING MODE) #45
#
# RPCRTQSW (1D) P(2) LUNAR LANDING TARGET PARAMETERS ( COS 45 DEGREES SCALED AT B+1 )
# X COMPONENT OF X-AXIS OF VEHICLE IN
# STABLE MEMBER COORDINATES: CRITERION FOR
# REPOSITIONING LR ANTENNA
# DEC 00000 (TWO-PHASE LANDING MODE) SUNLITER
# DEC .35356 (ONE-PHASE LANDING MODE) # 260
#
# LRALPHA (1D) P(I) (ALPHA-1) LANDING RADAR P63-67 ( 6 DEGREES)
# POSITION 1, X ROTATION
# 1OCT 01042 SUNLITER # 168
#
# LRBETA1 (1D) P(I) (BETA-1) LANDING RADAR P63-67 ( 24 DEGREES)
# POSITION 1, Y ROTATION
# 1OCT 04210
#
# LRALPHA2 (1D) P(I) (ALPHA-2) LANDING RADAR P63-67 ( 6 DEGREES)
# POSITION 2, X ROTATION
# 1OCT 01042 SUNLITER # 168
#
# LRBETA2 (1D) P(I) (BETA-2) LANDING RADAR P63-67 ( 0 DEGREES)
# POSITION 2, Y ROTATION
# 1OCT 00000 SUNLITER # 168
#
# LRHMAX (1D) P(I) (H-M) LANDING RADAR P63-67 (50,000 FEET)
# ALTITUDE WEIGHTING FUNCTION PARAMETER
# 1DEC 15240 PCR # 253
#
# LRVMAX (1D) P(I) (V-M) LANDING RADAR P63-67 (2000 FT PER SECOND)
# VELOCITY WEIGHTING FUNCTION PARAMETER
# 1DEC .047625 SUNLITER # 168
#
# LRWH (1D) P(I) (K-H) LANDING RADAR P63-67 (.35 DEC)
# ALTITUDE WEIGHTING FUNCTION PARAMETER
# 1DEC .35 PCR # 253
#
# LRWVZ (1D) P(I) (K-VZ) LANDING RADAR P63-67 ( .7 DEC )
# Z VELOCITY WEIGHTING FUNCTION PARAMETER
## Page 48
# 1DEC .7 SUNLITER # 168
#
# LRWVY (1D) P(I) (K-VY) LANDING RADAR P63-67 ( .7 DEC )
# Y VELOCITY WEIGHTING FUNCTION PARAMETER
# 1DEC .7 SUNLITER # 168
#
# LRWVX (1D) P(I) (K-VX) LANDING RADAR P63-67 ( .4 DEC )
# X VELOCITY WEIGHTING FUNCTION PARAMETER
# 1DEC .4 SUNLITER # 168
#
# DELQFIX (2D) P(I) DELQFIX R12 50 FEET
# LR ALT DATA REASONABLENESS TEST PARM.
# 2DEC 15.24 B-24 PCRS 639 &248
#
# TBRKPNT (1D) P(I) P70-71 ASCENT (540 SEC OR 54000 CSEC )
# TFI BRANCH TIME; ABORT TARGET
# 1DEC 54000 B-17 PCR # 133
#
# ABTVINJ1 (2D) P(I) P70-71 ASCENT (5551 FEET / SEC)
# DESIRED INJECTION VELOCITY FOR TFI
# BRANCH TIME LESS THAN TBRKPNT; VELOCITY
# REQUIRED TO GAIN 60 NM APOLUNE ORBIT
# 2DEC 16.91945 B-7 PCR # 133
#
# ABTVINJ2 (2D) P(I) P70-71 ASCENT (5510 FEET / SEC)
# DESIRED INJECTION VELOCITY FOR TFI
# BRANCH TIME GREATER THAN TBRKPNT; VEL
# REQUIRED TO GAIN 30 NM APOLUNE ORBIT
# 2DEC 16.79448 B-7 PCR # 133
#
# TLAND (2D) P(U) LUNAR LANDING TARGET PARAMETERS ( 2DEC 34573411 <CSEC>)
# BRAKING PHASE TIME OF LANDING ON MOON
# LAUNCH DATE DEPENDENT
#
# RLS (6D) P(U) (R-LS) P20-22 LUNAR SURFACE NAVIGATION (1.7 TIMES 10**6 METERS; 0 M; 0 METER)
# SAMPLE VALUE AT 0DEG LATITUDE & LONGITUD
# LANDING SITE VECTOR, MOON REFERENCE
# LAUNCH DATE DEPENDENT
#
# 504LM (6D) P(I) (L-M) PLANETARY INERTIAL ORIENTATION ( RADIANS) 8.5 X 10**-5
# 73.9 X 10**-5
## Page 49
# 6.6 X 10**-5
# MOON LIBRATION VECTOR EXPRESSED AT MID-
# POINT OF MISSION IN MOON FIXED COORDIN.
# LAUNCH DATE DEPENDENT
#
# TEPHEM (3D) P(U) (T-0) LUNAR + SOLAR EPHEMERIDES,P50S (2.23452 X 10**9 CSEC )
# LAUNCH TIME - ELAPSED TIME BETWEEN MID-
# NITE JULY 1 UNIVERSAL TIME PRECEEDING
# LAUNCH AND THE TIME THAT THE COMPUTER
# CLOCK WAS ZEROED AT TIME OF LAUNCH
# +0 DEC LAUNCH DATE DEPENDENT
# +1 2DEC
#
# AXO (2D) P(I) (A-X-TLO) PLANETARY INERTIAL ORIENTATION ( 4.65 X 10**-5 RADIANS)
# EARTH ANALOGS OF 504LM
# FUNCTION OF LAUNCH TIME USED BY NAVIGA-
# TION PROGRAMS
# SMALL ANGLE ABOUT THE X-AXIS OF BASIC
# REFERENCE COORDINATE SYSTEM.....
# LAUNCH DATE DEPENDENT
#
# -AYO (2D) P(I) (A-Y-TLO) PLANETARY INERTIAL ORIENTATION ( 2.147 X 10**-5 RADIANS)
# SEE AXO COMMENTS
# SMALL ANGLE ABOUT THE Y AXIS OF BASIC
# REFERENCE COORDINATE SYSTEM THAT DES-
# CRIBES THE PRECESSION AND NUTATION OF
# THE EARTH'S POLAR AXIS
# LAUNCH DATE DEPENDENT
#
# AZO (2D) P(I) (A-Z-O) PLANETARY INERITAL ORIENTATION ( .7753 REVOLUTIONS)
# ANGLE BETWEEN THE X AXIS OF BASIC REF
# COORDINATE SYSTEM AND THE X AXIS OF THE
# EARTH-FIXED COORDINATE SYSTEM AT
# --,196- UNIVERSAL TIME
# LAUNCH DATE DEPENDENT
#
# REFSMMAT (18D) PGM P50'S COMPUTE; MOST MAJOR PGMS. ( ORTHOGONAL UNIT VECTORS ) SEE BELOW
# TRANSFORMATION MATRIX BETWEEN
# STABLE MEMBER COORDINATE SYSTEM AND
# INERTIAL COORDINATE SYSTEM
# A S V +0 2DEC +.155540134
# A A +2 2DEC -.441118568
# M L +4 2DEC -.176696562
# P U +6 2DEC -.001190874
# L E +10 2DEC -.186282563 23A LUNAR LANDING PGM
## Page 50
# E . +12 2DEC +.464001495
# . . +14 2DEC -.475190328
# . . +16 2DEC -.143920862
# . . +20 2DEC -.058999463
#
# RRECTCSM (6D) U(PGM) (R-C0) INTEGRATION INITIALIZATION (METERS,B-29 OR B-27 IF EARTH OR MOON
# PERMANENT STATE VECTORS AND TIMES
# RECTIFICATION POSITION VECTOR FOR CSM
#
# RRECTLEM (6D) U(PGM) (R-L-0) INTEGRATION INITIALIZATION (METERS,B-29 OR B-27 IF EARTH OR MOON
# PERMANENT STATE VECTORS AND TIMES
# RECTIFICATION POSITION VECTOR FOR LEM
#
# VRECTCSM (6D) U(PGM) (V-C-0) INTEGRATION INITIALIZATION (M/CSEC, B-7 OR B-5 IF EARTH OR MOON)
# PERMANENT STATE VECTORS AND TIMES
# RECTIFICATION VELOCITY VECTOR FOR CSM
#
# VRECTLEM (6D) U(PGM) (V-L-0) INTEGRATION INITIALIZATION (M/CSEC, B-7 OR B-5 IF EARTH OR MOON)
# PERMANENT STATE VECTORS AND TIMES
# RECTIFICATION VELOCITY VECTOR FOR LEM
#
# RCVCSM (6D) U(PGM) (R-C-CON) INTEGRATION INITIALIZATION (METERS,B-29 OR B-27 IF EARTH OR MOON
# PERMANENT STATE VECTORS AND TIMES
# CONIC POSITION VECTOR FOR CSM
# EQUALS RRECTCSM IF TCCSM =0
#
# RCVLEM (6D) U(PGM) (R-L-CON) INTEGRATION INITIALIZATION (METERS,B-29 OR B-27 IF EARTH OR MOON
# PERMANENT STATE VECTORS AND TIMES
# CONIC POSITION VECTOR FOR LEM
# EQUALS RRECTLEM IF TCLEM =0
#
# VCVCSM (6D) U(PGM) (V-C-CON) INTEGRATION INITIALIZATION (M/CSEC, B-7 OR B-5 IF EARTH OR MOON)
# PERMANENT STATE VECTORS AND TIMES
# CONIC VELOCITY VECTOR FOR CSM
# EQUALS VRECTCSM IF TCCSM =0
#
# VCVLEM (6D) U(PGM) (V-L-CON) INTEGRATION INITIALIZATION (M/CSEC, B-7 OR B-5 IF EARTH OR MOON)
# PERMANENT STATE VECTORS AND TIMES
# CONIC VELOCITY VECTOR FOR LEM
# EQUALS VRECTLEM IF TCLEM =0
#
## Page 51
# DELTACSM (6D) P(U) (DELTA-C) INTEGRATION INITIALIZATION (METERS, B-22 OR B-18 IF EARTH OR MOON)
# PERMANENT STATE VECTORS AND TIMES
# POSITION DEVIATION VECTOR FOR CSM
# = 0 IF TCCSM =0
# 6DEC 0 LUMINARY LIST, INT. INIT.
#
# DELTALEM (6D) P(U) (DELTA-L) INTEGRATION INITIALIZATION (METERS, B-22 OR B-18 IF EARTH OR MOON)
# PERMANENT STATE VECTORS AND TIMES
# POSITION DEVIATION VECTOR FOR LEM
# = 0 IF TCLEM =0
# 6DEC 0 LUMINARY LIST, INT. INIT.
#
# NUVCSM (6D) P(U) (UPSILON-C) INTEGRATION INITIALIZATION (M/CSEC, B-3 OR B-(-1) IF EARTH OR MOON
# PERMANENT STATE VECTORS AND TIMES
# VELOCITY DEVIATION VECTOR FOR CSM
# = 0 IF TCCSM =0
# 6DEC 0 LUMINARY LIST, INT. INIT.
#
# NUVLEM (6D) P(U) (UPSILON-L) INTEGRATION INITIALIZATION (M/CSEC, B-3 OR B-(-1) IF EARTH OR MOON
# PERMANENT STATE VECTORS AND TIMES
# VELOCITY DEVIATION VECTOR FOR LEM
# = 0 IF TCLEM =0
# 6DEC 0 LUMINARY LIST, INT. INIT.
#
# TCCSM (2D) P(U) (TAU-C) INTEGRATION INITIALIZATION ( 0 CSEC, B-28 )
# PERMANENT STATE VECTORS AND TIMES
# TIME SINCE RECTIFICATION FOR CSM
# TIME ASSOCIATED WITH CSM CONIC POSITION,
# CONIC VELOCITY, POSITION DEVIATION AND
# VELOCITY DEVIATION VECTORS
# 2DEC 0 LUMINARY LIST, INT. INIT.
#
# TCLEM (2D) P(U) (TAU-L) INTEGRATION INITIALIZATION ( 0 CSEC, B-28 )
# PERMANENT STATE VECTORS AND TIMES
# TIME SINCE RECTIFICATION FOR LEM
# TIME ASSOCIATED WITH LEM CONICS AS ABOVE
# 2DEC 0 LUMINARY LIST, INT. INIT.
#
# TETCSM (2D) U(PGM) (T-C) INTEGRATION INITIALIZATION ( CSEC, B-28 )
# PERMANENT STATE VECTORS AND TIMES
# THE TIME THAT STATE VECTOR IS VALID;
# LUNAR ORBIT DEPENDENCE ON REAL TIME
#
## Page 52
# TETLEM (2D) U(PGM) (T-L) INTEGRATION INITIALIZATION ( CSEC, B-28 )
# PERMANENT STATE VECTORS AND TIMES
# THE TIME THAT STATE VECTOR IS VALID;
# LUNAR ORBIT DEPENDENCE ON REAL TIME
#
# XKEPCSM (2D) P(U) (X-C) INTEGRATION INITIALIZATION (M**1/2, B-17 OR B-16 IF EARTH OR MOON)
# PERMANENT STATE VECTORS AND TIMES
# ROOT OF KEPLER'S EQUATION FOR CSM
# = 0 IF TCCSM =0
# 2DEC 0 LUMINARY LIST, INT. INIT.
#
# XKEPLEM (2D) P(U) (X-L) INTEGRATION INITIALIZATION (M**1/2, B-17 OR B-16 IF EARTH OR MOON)
# PERMANENT STATE VECTORS AND TIMES
# ROOT OF KEPLER'S EQUATION FOR LEM
# = 0 IF TCLEM =0
# 2DEC 0 LUMINARY LIST, INT. INIT.
#
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