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Revert "Proof read P34-35_P74-75 pages 0460-0462 for the Comanche055 …
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…program. Still many more to go."

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Froderick-Fronkensteen committed Jan 15, 2022
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# Page 460
# TRANSFER PHASE INITIATION (TPI) PROGRAMS (P34 AND P74)
#
# MOD NO -1 LOG SECTION - P32-P35, P72-P75
# MOD BY WHITE.P DATE: 1JUNE67
# MOD NO -1 LOG SECTION -- P32-P35, P72-P75
# MOD BY WHITE, P. DATE: 1 JUNE 67
#
# PURPOSE
# (1) TO CALCULATE THE REQUIRED DELTA V AND OTHER INITIAL CONDITIONS
# REQUIRED BY THE ACTIVE VEHICLE FOR EXECUTION OF THE TRANSFER
# PHASE INITIATION (TPI) MANEUVER, GIVEN -
#
# (A) TIME OF IGNITION TIG (TPI) OR THE ELEVATION ANGLE (E) OF
# THE ACTIVE/PASSIVE VEHICLE LOS AT TIG (TPI).
#
# (B) CENTRAL ANGLE OF TRANSFER (CENTANG) FROM TIG (TPI) TO
# INTERCEPT TIME (TIG (TPF)).
#
# (2) TO CALCULATE TIG (TPI) GIVEN E OR E GIVEN TIG (TPI).
#
# (3) TO CALCULATE THESE PARAMETERS BASED UPON MANEUVER DATA
# APPROVED AND KEYED INTO THE DSKY BY THE ASTRONAUT.
#
# (4) TO DISPLAY TO THE ASTRONAUT AND THE GROUND CERTAIN DEPENDENT
# VARIABLES ASSOCIATED WITH THE MANEUVER FOR APPROVAL BY THE
# ASTRONAUT/GROUND.
#
# (5) TO STORE THE TPI TARGET PARAMETERS FOR USE BY THE DESIRED
# THRUSTING PROGRAM.
# (1) TO CALCULATE THE REQUIRED DELTA V AND OTHER INITIAL CONDITIONS
# REQUIRED BY THE ACTIVE VEHICLE FOR EXECUTION OF THE TRANSFER
# PHASE INITIATION (TPI) MANEUVER, GIVEN --
# (A) TIME OF IGNITION TIG (TPI) OR THE ELEVATION ANGLE (E) OF
# THE ACTIVE/PASSIVE VEHICLE LOS AT TIG (TPI).
# (B) CENTRAL ANGLE OF TRANSFER (CENTANG) FROM TIG (TPI) TO
# INTERCEPT TIME (TIG (TPF)).
# (2) TO CALCULATE TIG (TPI) GIVEN E OR E GIVEN TIG (TPI).
# (3) TO CALCULATE THESE PARAMETERS BASED UPON MANEUVER DATA
# APPROVED AND KEYED INTO THE DSKY BY THE ASTRONAUT.
# (4) TO DISPLAY TO THE ASTRONAUT AND THE GROUND CERTAIN DEPENDENT
# VARIABLES ASSOCIATED WITH THE MANEUVER FOR APPROVAL BY THE
# ASTRONAUT/GROUND.
# (5) TO STORE THE TPI TARGET PARAMETERS FOR USE BY THE DESIRED
# THRUSTING PROGRAM.
#
# ASSUMPTIONS
# (1) LM ONLY -- THIS PROGRAM IS BASED UPON PREVIOUS COMPLETION OF
# THE CONSTANT DELTA ALTITUDE (CDH) PROGRAM (P33/P73).
# THEREFORE --
# (A) AT A SELECTED TPI TIME (NOW IN STORAGE) THE LINE OF SIGHT
# BETWEEN THE ACTIVE AND PASSIVE VEHICLES WAS SELECTED TO BE
# A PRESCRIBED ANGLE (E) (NOW IN STORAGE) FROM THE
# HORIZONTAL PLANE DEFINED BY THE ACTIVE VEHICLE POSITION.
# (B) THE TIME BETWEEN CDH IGNITION AND TPI IGNITION WAS
# COMPUTED TO BE GREATER THAN 10 MINUTES.
# (C) THE VARIATION OF THE ALTITUDE DIFFERENCE BETWEEN THE
# ORBITS WAS MINIMIZED.
# (D) THE PERICENTER ALTITUDES OF ORBITS FOLLOWING CSI AND
# CDH WERE COMPUTED TO BE GREATER THAN 35,000 FT FOR LUNAR
# Page 461
# ORBIT OR 85 NM FOR EARTH ORBIT.
# (E) THE CSI AND CDH MANEUVERS WERE ASSUMED TO BE PARALLEL TO
# THE PLANE OF THE PASSIVE VEHICLE ORBIT. HOWEVER, CREW
# MODIFICATION OF DELTA V (LV) COMPONENTS MAY HAVE RESULTED
# IN AN OUT-OF-PLANE MANEUVER.
# (2) STATE VECTOR UPDATED BY P27 ARE DISALLOWED DURING AUTOMATIC
# STATE VECTOR UPDATING INITIATED BY P20 (SEE ASSUMPTION (4)).
# (3) THIS PROGRAM MUST BE DONE OVER A TRACKING STATION FOR REAL
# TIME GROUND PARTICIPATION IN DATA INPUT AND OUTPUT. COMPUTED
# VARIABLES MAY BE STORED FOR LATER VERIFICATION BY THE GROUND.
# THESE STORAGE CAPABILITIES ARE LIMITED ONLY TO THE PARAMETERS
# FOR ONE THRUSTING MANEUVER AT A TIME EXCEPT FOR CONCENTRIC
# FLIGHT PLAN MANEUVER SEQUENCES.
# (4) THE RENDEZVOUS RADAR MAY OR MAY NOT BE USED TO UPDATE THE LM
# OR CSM STATE VECTORS FOR THIS PROGRAM. IF RADAR USE IS
# DESIRED THE RADAR WAS TURNED ON AND LOCKED ON THE CSM BY
# PREVIOUS SELECTION OF P20. RADAR SIGHTING MARKS WILL BE MADE
# AUTOMATICALLY APPROXIMATELY ONCE A MINUTE WHEN ENABLED BY THE
# TRACK AND UPDATE FLAGS (SEE P20). THE RENDEZVOUS TRACKING
# MARK COUNTER IS ZEROED BY THE SELECTION OF P20 AND AFTER EACH
# THRUSTING MANEUVER.
# (5) THE ISS NEED NOT BE ON TO COMPLETE THIS PROGRAM.
# (6) THE OPERATION OF THE PROGRAM UTILIZES THE FOLLOWING FLAGS --
#
# (1) LM ONLY - THIS PROGRAM IS BASED UPON PREVIOUS COMPLETION OF
# THE CONSTANT DELTA ALTITUDE (CDH) PROGRAM (P33/P73).
# THEREFORE -
#
# (A) AT A SELECTED TPI TIME (NOW IN STORAGE) THE LINE OF SIGHT
# BETWEEN THE ACTIVE AND PASSIVE VEHICLES WAS SELECTED TO BE
# A PRESCRIBED ANGLE (E) (NOW IN STORAGE) FROM THE
# HORIZONTAL PLANE DEFINED BY THE ACTIVE VEHICLE POSITION.
#
# (B) THE TIME BETWEEN CDH IGNITION AND TPI IGNITION WAS
# COMPUTED TO BE GREATER THAN 10 MINUTES.
# ACTIVE VEHICLE FLAG -- DESIGNATES THE VEHICLE WHICH IS
# DOING RENDEZVOUS THRUSTING MANEUVERS TO THE PROGRAM WHICH
# CALCULATES THE MANEUVER PARAMETERS. SET AT THE START OF
# EACH RENDEZVOUS PRE-THRUSTING PROGRAM.
#
# (C) THE VARIATION OF THE ALTITUDE DIFFERENCE BETWEEN THE
# ORBITS WAS MINIMIZED.
# FINAL FLAG -- SELECTS FINAL PROGRAM DISPLAYS AFTER CREW HAS
# SELECTED THE FINAL MANEUVER COMPUTATION CYCLE.
#
# (D) THE PERICENTER ALTITUDES OF ORBITS FOLLOWING CSI AND
# EXTERNAL DELTA V FLAG -- DESIGNATES THE TYPE OF STEERING
# REQUIRED FOR EXECUTION OF THIS MANEUVER BY THE THRUSTING
# PROGRAM SELECTED AFTER COMPLETION OF THIS PROGRAM.
#
# CDH WERE COMPUTED TO BE GREATER THAN 35,000 FT FOR LUNAR
# Page 461
# ORBIT OR 85 NM FOR EARTH ORBIT.
# (7) ONCE THE PARAMETERS REQUIRED FOR COMPUTATION OF THE MANEUVER
# HAVE BEEN COMPLETELY SPECIFIED, THE VALUE OF THE ACTIVE
# VEHICLE CENTRAL ANGLE OF TRANSFER IS COMPUTED AND STORED.
# THIS NUMBER WILL BE AVAILABLE FOR DISPLAY TO THE ASTRONAUT
# THROUGH THE USE OF V06N52.
#
# (E) THE CSI AND CDH MANEUVERS WERE ASSUMED TO BE PARALLEL TO
# THE PLANE OF THE PASSIVE VEHICLE ORBIT. HOWEVER, CREW
# MODIFICATION OF DELTA V (LV) COMPONENTS MAY HAVE RESULTED
# IN AN OUT-OF-PLANE MANEUVER.
#
# (2) STATE VECTOR UPDATED BY P27 ARE DISALLOWED DURING AUTOMATIC
# STATE VECTOR UPDATING INITIATED BY P20 (SEE ASSUMPTION (4)).
#
# (3) THIS PROGRAM MUST BE DONE OVER A TRACKING STATION FOR REAL
# TIME GROUND PARTICIPATION IN DATA INPUT AND OUTPUT. COMPUTED
# VARIABLES MAY BE STORED FOR LATER VERIFICATION BY THE GROUND.
# THESE STORAGE CAPABILITIES ARE LIMITED ONLY TO THE PARAMETERS
# FOR ONE THRUSTING MANEUVER AT A TIME EXCEPT FOR CONCENTRIC
# FLIGHT PLAN MANEUVER SEQUENCES.
#
# (4) THE RENDEZVOUS RADAR MAY OR MAY NOT BE USED TO UPDATE THE LM
# OR CSM STATE VECTORS FOR THIS PROGRAM. IF RADAR USE IS
# DESIRED THE RADAR WAS TURNED ON AND LOCKED ON THE CSM BY
# PREVIOUS SELECTION OF P20. RADAR SIGHTING MARKS WILL BE MADE
# AUTOMATICALLY APPROXIMATELY ONCE A MINUTE WHEN ENABLED BY THE
# TRACK AND UPDATE FLAGS (SEE P20). THE RENDEZVOUS TRACKING
# MARK COUNTER IS ZEROED BY THE SELECTION OF P20 AND AFTER EACH
# THRUSTING MANEUVER.
#
# (5) THE ISS NEED NOT BE ON TO COMPLETE THIS PROGRAM.
#
# (6) THE OPERATION OF THE PROGRAM UTILIZES THE FOLLOWING FLAGS -
#
# ACTIVE VEHICLE FLAG - DESIGNATES THE VEHICLE WHICH IS
# DOING RENDEZVOUS THRUSTING MANEUVERS TO THE PROGRAM WHICH
# CALCULATES THE MANEUVER PARAMETERS. SET AT THE START OF
# EACH RENDEZVOUS PRE-THRUSTING PROGRAM.
#
# FINAL FLAG - SELECTS FINAL PROGRAM DISPLAYS AFTER CREW HAS
# SELECTED THE FINAL MANEUVER COMPUTATION CYCLE.
#
# EXTERNAL DELTA V FLAG - DESIGNATES THE TYPE OF STEERING
# REQUIRED FOR EXECUTION OF THIS MANEUVER BY THE THRUSTING
# PROGRAM SELECTED AFTER COMPLETION OF THIS PROGRAM.
#
# (7) ONCE THE PARAMETWRS REQUIRED FOR COMPUTION OF THE MANEUVER
# HAVE BEEN COMPLETELY SPECIFIED, THE VALUE OF THE ACTIVE
# VEHICLE CENTRAL ANGLE OF TRANSFER IS COMPUTED AND STORED.
# THIS NUMBER WILL BE AVAILABLE FOR DISPLAY TO THE ASTRONAUT
# THROUGH THE USE OF V06N52.
#
# THE ASTRONAUT WILL CALL THIS DISPLAY TO VERIFY THAT THE
# CENTRAL ANGLE OF TRANSFER OF THE ACTIVE VEHICLE IS NOT WITHIN
# THE ASTRONAUT WILL CALL THIS DISPLAY TO VERIFY THAT THE
# CENTRAL ANGLE OF TRANSFER OF THE ACTIVE VEHICLE IS NOT WITHIN
# Page 462
# 170 TO 190 DEGREES. IF THE ANGLE IS WITHIN THIS ZONE THE
# ASTRONAUT SHOULD REASSESS THE INPUT TARGETING PARAMETERS BASED
# UPON DELTA V AND EXPECTED MANEUVER TIME.
#
# (8) THIS PROGRAM IS SELECTED BY THE ASTRONAUT BY DSKY ENTRY -
# 170 TO 190 DEGREES. IF THE ANGLE IS WITHIN THIS ZONE THE
# ASTRONAUT SHOULD REASSES THE INPUT TARGETING PARAMETERS BASED
# UPON DELTA V AND EXPECTED MANEUVER TIME.
# (8) THIS PROGRAM IS SELECTED BY THE ASTRONAUT BY DSKY ENTRY --
#
# P34 IF THIS VEHICLE IS ACTIVE VEHICLE.
# P34 IF THIS VEHICLE IS ACTIVE VEHICLE.
#
# P74 IF THIS VEHICLE IS PASSIVE VEHICLE.
# P74 IF THIS VEHICLE IS PASSIVE VEHICLE.
#
# INPUT
#
# (1) TTPI TIME OF THE TPI MANEUVER
# (2) ELEV DESIRED LOS ANGLE AT TPI
# (3) CENTANG ORBITAL CENTRAL ANGLE OF THE PASSIVE VEHICLE DURING
# TRANSFER FROM TPI TO TIME OF INTERCEPT
# (1) TTPI TIME OF THE TPI MANEUVER.
# (2) ELEV DESIRED LOS ANGLE AT TPI
# (3) CENTANG ORBITAL CENTRAL ANGLE OF THE PASSIVE VEHICLE DURING
# TRANSFER FROM TPI TO TIME OF INTERCEPT
#
# OUTPUT
#
# (1) TRKMKCNT NUMBER OF MARKS
# (2) TTOGO TIME TO GO
# (3) +MGA MIDDLE GIMBAL ANGLE
# (4) TTPI COMPUTED TIME OF TPI MANEUVER
# OR
# ELEV COMPUTED LOS ANGLE AT TPI
# (5) POSTTPI PERIGEE ALTITUDE AFTER THE TPI MANEUVER
# (6) DELVTPI MAGNITUDE OF DELTA V AT TPI
# (7) DELVTPF MAGNITUDE OF DELTA V AT INTERCEPT
# (8) DVLOS DELTA VELOCITY AT TPI - LINE OF SIGHT
# (9) DELVLVC DELTA VELOCITY AT TPI - LOCAL VERTICAL COORDINATES
# (1) TRKMKCNT NUMBER OF MARKS
# (2) TTOGO TIME TO GO
# (3) +MGA MIDDLE GIMBAL ANGLE
# (4) TTPI COMPUTED TIME OF TPI MANEUVER
# OR
# ELEV COMPUTED LOS ANGLE AT TPI
# (5) POSTTPI PERIGEE ALTITUDE AFTER THE TPI MANEUVER
# (6) DELVTPI MAGNITUDE OF DELTA V AT TPI
# (7) DELVTPF MAGNITUDE OF DELTA V AT INTERCEPT
# (8) DVLOS DELTA VELOCITY AT TPI -- LINE OF SIGHT
# (9) DELVLVC DELTA VELOCITY AT TPI -- LOCAL VERTICAL COORDINATES
#
# DOWNLINK
# (1) TTPI TIME OF TPI MANEUVER
# (2) TIG TIME OF TPI MANEUVER
# (3) ELEV DESIRED LOS ANGLE AT TPI
# (4) CENTANG ORBITAL CENTRAL ANGLE OF THE PASSIVE VEHICLE DURING
# TRANSFER FROM TPI TO TIME OF INTERCEPT
# (5) DELVEET3 DELTA VELOCITY AT TPI -- REFERENCE COORDINATES
# (6) TPASS4 TIME OF INTERCEPT
#
# (1) TTPI TIME OF THE TPI MANEUVER
# (2) TIG TIME OF THE TPI MANEUVER
# (3) ELEV DESIRED LOS ANGLE AT TPI
# (4) CENTANG ORBITAL CENTRAL ANGLE OF THE PASSIVE VEHICLE DURING
# TRANSFER FROM TPI TO TIME OF INTERCEPT
# (5) DELVEET3 DELTA VELOCITY AT TPI - REFERENCE COORDINATES
# (6) TPASS4 TIME OF INTERCEPT
# COMMUNICATION TO THRUSTING PROGRAMS
#
# (1) TIG TIME OF THE TPI MANEUVER
# (2) RTARG OFFSET TARGET POSITION
# (3) TPASS4 TIME OF INTERCEPT
# (4) XDELVFLG RESET TO INDICATE LAMBERT (AIMPOINT) VG COMPUTATION
# (1) TIG TIME OF THE TPI MANEUVER
# (2) RTARG OFFSET TARGET POSITION
# (3) TPASS4 TIME OF INTERCEPT
# (4) XDELVFLG RESET TO INDICATE LAMBERT (AIMPOINT) VG COMPUTATION
#
# SUBROUTINES USED
#
# AVFLAGA
# Page 463
# AVFLAGP
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