Proof AUTOMATIC_MANEUVERS (#194) (#335)

* Proof FIXED_FIXED_CONSTANT_POOL (#207)

* Proof AUTOMATIC_MANEUVERS (#194)

Comanche055/AUTOMATIC_MANEUVERS.agc

@@ -51,6 +51,7 @@ AHFNOROT	EXTEND
 		EXTEND
 		BZMF	HOLDFUNC
 
+
 AUTOCONT	CA	HOLDFLAG	# IF HOLDFLAG IS +, GO TO GRABANG.
 		EXTEND			# OTHERWISE, GO TO ATTHOLD.
 		BZMF	ATTHOLD
@@ -81,27 +82,29 @@ FREECONT	CAF	ONE
 		TS	TAU2
 		TCF	T6PROGM
 
+
 MINTAU		DEC	0
 		DEC	23		# = 14MS
 		DEC	-23		# = -14MS
 		DEC	0
 
 # Page 1027
-# CALCULATION OF ATTITUDE ERRORS:
+# 	CALCULATION OF ATTITUDE ERRORS-
-#	_    *     _      _          _
+#	-    *     -      -          -
 #	AK = AMGB (CDUX - THETADX) + BIAS
 #
-# I.E.,	*AK *   * 1        SIN(PSI)        0	** CDUX - THETADX *    *BIAS *
+# IE	*AK *   * 1        SIN(PSI)        0	** CDUX - THETADX *    *BIAS *
 #	*   *   *                               **                *    *     *
 #	*AK1* = * 0   COS(PSI)COS(PHI)  SIN(PHI)** CDUY - THETADY *  + *BIAS1*
 #	*   *   *                               **                *    *     *
 #	*AK2*   * 0  -COS(PSI)SIN(PHI)  COS(PHI)** CDUZ - THETADZ *    *BIAS2*
 #
-# THE BIASES ARE ADDED ONLY WHILE PERFORMING AUTOMATIC MANEUVERS (ESP KALCMANU) TO PROVIDE ADDITIONAL LEAD
+# 	THE BIASES ARE ADDED ONLY WHILE PERFORMING AUTOMATIC MANEUVERS (ESP KALCMANU) TO PROVIDE ADDITIONAL LEAD
 # AND PREVENT OVERSHOOT WHEN STARTING AN AUTOMATIC MANEUVER.  NORMALLY THE REQUIRED LEAD IS ONLY 1-2 DEGREES.
 # BUT DURING HIGH RATE MANEUVERS IT CAN BE AS MUCH AS 7 DEGREES.  THE BIASES ARE COMPUTED BY KALCMANU AND REMAIN
 # FIXED UNTIL THE MANEUVER IS COMPLETED AT WHICH TIME THEY ARE RESET TO ZERO.
 
+
 ATTHOLD		CA	CDUX
 		EXTEND
 		MSU	THETADX
@@ -144,6 +147,7 @@ ATTHOLD		CA	CDUX
 		ADS	ERRORZ
 		TCF	JETS
 
+
 HOLDFUNC	CCS	HOLDFLAG
 		TCF	+3
 		TCF	ATTHOLD
@@ -182,8 +186,7 @@ ENDDAMP		TS	HOLDFLAG	# SET HOLDFLAG +0
 #
 # DETERMINE THE LOCATION OF THE RATE ERROR AND THE ATTITUDE ERROR RELATIVE TO THE SWITCHING LOGIC IN THE PHASE
 # PLANE.
-#
+# COMPUTE THE CHANGE IN RATE CORRESPONDING TO THE ATTITUDE ERROR NECESSARY TO DRIVE THE THE S/C INTO THE
-# COMPUTE THE CHANGE IN RATE CORRESPONDING TO THE ATTITUDE ERROR NECESSARY TO DRIVE THE S/C INTO THE
 # APPROPRIATE DEADZONE.
 #
 #                                     .
@@ -210,12 +213,15 @@ ENDDAMP		TS	HOLDFLAG	# SET HOLDFLAG +0
 #                                   * .                *
 #                                    *.               - *
 #                                     .                - *****************
-#                                     .*-
+#                                     .*                -
 #                                     . * --------------------------------
+#                                     .  *
+#                                     .   ********************************
 #                                     .
-#                                     .
+
 #			FIG. 1	PHASE PLANE SWITCHING LOGIC
-#
+
+
 # CONSTANTS FOR JET SWITCHING LOGIC
 
 WLH/SLOP	DEC	.00463		# = WL+H/SLOPE = .83333 DEG	$180
@@ -435,7 +441,7 @@ J24		CS	AERR
 		DAS	KMPAC
 
 # Page 1035
-# COMPUTE THE JET ON TIME NECESSARY TO ACCOMPLISH THE DESIRED CHANGE IN RATE, I.E.,
+# 	COMPUTE THE JET ON TIME NECESSARY TO ACCOMPLISH THE DESIRED CHANGE IN RATE, IE
 #
 #	     T  = J/M(DELTA W)
 #	      J
@@ -443,14 +449,14 @@ J24		CS	AERR
 #	DELTA W = DESIRED CHANGE IN S/C ANGULAR RATE AS DETERMINED BY THE
 #		  SWITCHING LOGIC, AT THIS POINT STORED IN KMPAC.
 #
-#	    J/M = S/C INERTIA TO TORQUE RATIO SCALED BY
+#	    J/M = S/C INERTIA TO TORQUE 9ATIO SCALED BY
 #		  	(57.3/450)(B24/1600)(1/.8)
 #		  FOR 1 JET OPERATION  (M = 700 FT-LB).
-#		  I.E., J/M = J(SLUG-FTFT) x 0.00000085601606
+#		  IE  J/M = J(SLUG-FTFT) x 0.00000085601606
 #
 #	          THE CORRESPONDING COMPUTER VARIABLES ESTABLISHED BY
 #		  KEYBOARD ENTRY ARE
-#			J/M  (ROLL)
+#			J/M (ROLL)
 #			J/M1 (PITCH)
 #			J/M2 (YAW)
 #
@@ -496,4 +502,3 @@ T6PROG		EXTEND			# WHEN THE ROTATION COMMANDS (TAUS)
 
 		EBANK=	KMPAC
 JETADDR		2CADR	JETSLECT
-