Proof read P34-35_P74-75 pages 0460-0462 for the Comanche055 program.…

… Still many more to go.

Comanche055/P34-35_P74-75.agc

@@ -32,130 +32,154 @@
 
 # Page 460
 # TRANSFER PHASE INITIATION (TPI) PROGRAMS (P34 AND P74)
-# MOD NO -1			LOG SECTION -- P32-P35, P72-P75
-# MOD BY WHITE, P.		DATE: 1 JUNE 67
+#
+# MOD NO -1	  LOG SECTION - P32-P35, P72-P75
+# MOD BY WHITE.P  DATE: 1JUNE67
 #
 # 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 --
 #
-#			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.
+#	(1) LM ONLY - THIS PROGRAM IS BASED UPON PREVIOUS COMPLETION OF
+#	    THE CONSTANT DELTA ALTITUDE (CDH) PROGRAM (P33/P73).
+#	    THEREFORE -
 #
-#			FINAL FLAG -- SELECTS FINAL PROGRAM DISPLAYS AFTER CREW HAS
-#			SELECTED THE FINAL MANEUVER COMPUTATION CYCLE.
+#	    (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.
 #
-#			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.
+#	    (B)	THE TIME BETWEEN CDH IGNITION AND TPI IGNITION WAS
+#		COMPUTED TO BE GREATER THAN 10 MINUTES.
 #
-#	(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.
+#	    (C)	THE VARIATION OF THE ALTITUDE DIFFERENCE BETWEEN THE
+#		ORBITS WAS MINIMIZED.
 #
-#		THE ASTRONAUT WILL CALL THIS DISPLAY TO VERIFY THAT THE
-#		CENTRAL ANGLE OF TRANSFER OF THE ACTIVE VEHICLE IS NOT WITHIN
+#	    (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 -
+#
+#		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
 # Page 462
-#		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 --
+#	    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.
 #
-#			P34 IF THIS VEHICLE IS ACTIVE VEHICLE.
+#	(8) THIS PROGRAM IS SELECTED BY THE ASTRONAUT BY DSKY ENTRY -
 #
-#			P74 IF THIS VEHICLE IS PASSIVE VEHICLE.
+#		P34 IF THIS VEHICLE IS ACTIVE 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