Apollo-11/Luminary099/ATTITUDE_MANEUVER_ROUTINE.agc

# Copyright:	Public domain.
# Filename:	ATTITUDE_MANEUVER_ROUTINE.agc
# Purpose: 	Part of the source code for Luminary 1A build 099.
#		It is part of the source code for the Lunar Module's (LM)
#		Apollo Guidance Computer (AGC), for Apollo 11.
# Assembler:	yaYUL
# Contact:	Ron Burkey <info@sandroid.org>.
# Website:	www.ibiblio.org/apollo.
# Pages:	342-363
# Mod history:	2009-05-16 RSB	Adapted from the corresponding
#				Luminary131 file, using page
#				images from Luminary 1A.
#
# This source code has been transcribed or otherwise adapted from
# digitized images of a hardcopy from the MIT Museum.  The digitization
# was performed by Paul Fjeld, and arranged for by Deborah Douglas of
# the Museum.  Many thanks to both.  The images (with suitable reduction
# in storage size and consequent reduction in image quality as well) are
# available online at www.ibiblio.org/apollo.  If for some reason you
# find that the images are illegible, contact me at info@sandroid.org
# about getting access to the (much) higher-quality images which Paul
# actually created.
#
# Notations on the hardcopy document read, in part:
#
#	Assemble revision 001 of AGC program LMY99 by NASA 2021112-061
#	16:27 JULY 14, 1969

# Page 342
# BLOCK 2 LGC ATTITUDE MANEUVER ROUTINE -- KALCMANU
#
# MOD 2		DATE 5/1/67	BY DON KEENE
#
# PROGRAM DESCRIPTION
#
# KALCMANU IS A ROUTINE WHICH GENERATES COMMANDS FOR THE LM DAP TO CHANGE THE ATTITUDE OF THE SPACECRAFT
# DURING FREE FALL.  IT IS DESIGNED TO MANEUVER THE SPACECRAFT FROM ITS INITIAL ORIENTATION TO SOME DESIRED
# ORIENTATION SPECIFIED BY THE PROGRAM WHICH CALLS KALCMANU, AVOIDING GIMBAL LOCK IN THE PROCESS.  IN THE
# MOD 2 VERSION, THIS DESIRED ATTITUDE IS SPECIFIED BY A SET OF OF THREE COMMANDED CDU ANGLES STORES AS 2'S COMPLEMENT
# SINGLE PRECISION ANGLES IN THE THREE CONSECUTIVE LOCATIONS, CPHI, CTHETA, CPSI, WHERE
#
#	CPHI = COMMANDED OUTER GIMBAL ANGLE
# 	CTHETA = COMMANDED INNER GIMBAL ANGLE
#	CPSI = COMMANDED MIDDLE GIMBAL ANGLE
#
# WHEN POINTING A SPACECRAFT AXIS (I.E., X, Y, Z, THE AOT, THRUST AXIS, ETC.) THE SUBROUTINE VECPOINT MAY BE
# USED TO GENERATE THIS SET OF DESIRED CDU ANGLES (SEE DESCRIPTION IN R60).
#
# WITH THIS INFORMATION KALCMANU DETERMINES THE DIRECTION OF THE SINGLE EQUIVALENT ROTATION (COF ALSO U) AND THE
# MAGNITUDE OF THE ROTATION (AM) TO BRING THE S/C FROM ITS INITIAL ORIENTATION TO ITS FINAL ORIENTATION.
# THIS DIRECTION REMAINS FIXED BOTH IN INERTIAL COORDINATES AND IN COMMANDED S/C AXES THROUGHOUT THE
#                  _
# MANEUVER.  ONCE COF AND AM HAVE BEEN DETERMINED, KALCMANU THEN EXAMINES THE MANEUVER TO SEE IF IT WILL BRING
#				       _
# THE S/C THROUGH GIMBAL LOCK.  IF SO, COF AND AM ARE READJUSTED SO THAT THE S/C WILL JUST SKIM THE GIMBAL
# LOCK ZONE AND ALIGN THE X-AXIS.  IN GENERAL A FINAL YAW ABOUT X WILL BE NECESSARY TO COMPLETE THE MANEUVER.
# NEEDLESS TO SAY, NEITHER THE INITIAL NOR THE FINAL ORIENTATION CAN BE IN GIMBAL LOCK.
#
# FOR PROPER ATTITUDE CONTROL THE DIGITAL AUTOPILOT MUST BE GIVEN AN ATTITUDE REFERENCE WHICH IT CAN TRACK.
# KALCMANU DOES THIS BY GENERATING A REFERENCE OF DESIRED GIMBAL ANGLES (CDUXD, CDUYD, CDUZD) WHICH ARE UPDATED
# EVERY ONE SECOND DURING THE MANEUVER.  TO ACHIEVE A SMOOTHER SEQUENCE OF COMMANDS BETWEEN SUCCESSIVE UPDATES,
# THE PROGRAM ALSO GENERATES A SET OF INCREMENTAL CDU ANGLES (DELDCDU) TO BE ADDED TO CDU DESIRED BY THE DIGITAL
# AUTOPILOT.  KALCMANU ALSO CALCULATES THE COMPONENT MANEUVER RATES (OMEGAPD, OMEGAQD, OMEGARD), WHICH CAN
#				      _
# BE DETERMINED SIMPLY BY MULTIPLYING COF BY SOME SCALAR (ARATE) CORRESPONDING TO THE DESIRED ROTATIONAL RATE.
#
# AUTOMATIC MANEUVERS ARE TIMED WTH THE HELP OF WAITLIST SO THAT AFTER A SPECIFIED INTERVAL THE Y AND Z
# DESIRED RATES ARE SET TO ZERO AND THE DESIRED CDU ANGLES (CDUYD, CDUZD) ARE SET EQUAL TO THE FINAL DESIRED CDU
# ANGLES (CTHETA, CPSI).  IF ANY YAW REMAINS DUE TO GIMBAL LOCK AVOIDANCE, THE FINAL YAW MANEUVER IS
# CALCULATED AND THE DESIRED YAW RATE SET TO SOME FIXED VALUE (ROLLRATE = + OR - 2 DEGREES PER SEC).
# IN THIS CASE ONLY AN INCREMENTAL CDUX ANGLE (DELFROLL) IS SUPPLIED TO THE DAP.  AT THE END OF THE YAW
# MANEUVER OR IN THE EVENT THAT THERE WAS NO FINAL YAW, CDUXD IS SET EQUAL TO CPHI AND THE X-AXIS DESIRED
# RATE SET TO ZERO.  THUS, UPON COMPLETION OF THE MANEUVER THE S/C WILL FINISH UP IN A LIMIT CYCLE ABOUT THE
# DESIRED GIMBAL ANGLES.
#
# PROGRAM LOGIC FLOW
#
# KALCMANU IS CALLED AS A HIGH PRIORITY JOB WITH ENTRY POINTS AT KALCMAN3 AND VECPOINT.  IT FIRST PICKS
# UP THE CURRENT CDU ANGLES TO BE USED AS THE BASIS FOR ALL COMPUTATIONS INVOLVING THE INITIAL S/C ORIENTATION.
# Page 343
# IT THEN DETERMINES THE DIRECTION COSINE MATRICES RELATING BOTH THE INITIAL AND FINAL S/C ORIENTATION TO STABLE
#               *   *                                                                               *
# MEMBER AXES (MIS,MFS).  IT ALSO COMPUTES THE MATRIX RELATING FINAL S/C AXES TO INITIAL S/C AXES (MFI).  THE
# ANGLE OF ROTATION (AM) IS THEN EXTRACTED FROM THIS MATRIX, AND TEST ARE MADE TO DETERMINE IF
#
#	A)	AM LESS THAN .25 DEGREES (MINANG)
#	B)	AM GREATER THAN 170 DEGREES (MAXANG)
#
# IF AM IS LESS THAN .25 DEGREES, NO COMPLICATED AUTOMATIC MANEUVERING IS NECESSARY.  THEREFORE, WE CAN SIMPLY
# SET CDU DESIRED EQUAL TO THE FINAL CDU DESIRED ANGLES AND TERMINATE THE JOB.
#
# IF AM IS GREATER THAN .25 DEGREES BUT LESS THAN 170 DEGREES THE AXES OF THE SINGLE EQUIVALENT ROTATION
#   _                                                       *
# (COF) IS EXTRACTED FROM THE SKEW SYMMETRIC COMPONENTS OF MFI.
#                                                                                     *     *
# IF AM GREATER THAN 170 DEGREES AN ALTERNATE METHOD EMPLOYING THE SYMMETRIC PART OF MFI (MFISYM) IS USED
#               _
# TO DETERMINE COF.
#
# THE PROGRAM THEN CHECKS TO SEE IF THE MANEUVER AS COMPUTED WILL BRING THE S/C THROUGH GIMBAL LOCK.  IF
# SO, A NEW MANEUVER IS CALCULATED WHICH WILL JUST SKIM THE GIMBAL LOCK ZONE AND ALIGN THE S/C X-AXIS.  THIS
# METHOD ASSURES THAT THE ADDITIONAL MANEUVERING TO AVOID GIMBAL LOCK WILL BE KEPT TO A MINIMUM.  SINCE A FINAL
# P AXIS YAW WILL BE NECESSARY, A SWITCH IS RESET (STATE SWITCH 31) TO ALLOW FOR THE COMPUTATION OF THIS FINAL
# YAW.
#
# AS STATED PREVIOUSLY, KALCMANU GENERATES A SEQUENCE OF DESIRED GIMBAL ANGLES WHICH ARE UPDATED EVERY
#                                                                                              _
# SECOND.  THIS IS ACCOMPLISHED BY A SMALL ROTATION OF THE DESIRED S/C FRAME ABOUT THE VECTOR COF.  THE NEW
# DESIRED REFERENCE MATRIX IS THEN,
#	 *		 *	 *
#	MIS	=	MIS	DEL
#	   N+1		   N
#        *
# WHERE DEL IS THE MATRIX CORRESPONDING TO THIS SMALL ROTATION.  THE NEW CDU ANGLES CAN THEN BE EXTRACTED
#       *
# FROM MIS.
#
# AT THE BEGINNING OF THE MANEUVER THE AUTOPILOT DESIRED RATES (OMEGAPD, OMEGAQD, OMEGARD) AND THE
# MANEUVER TIMINGS ARE ESTABLISHED.  ON THE FIRST PASS AND ON ALL SUBSEQUENT UPDATES THE CDU DESIRED
# ANGLES ARE LOADED WITH THE APPROPRIATE VALUES AND THE INCREMENTAL CDU ANGLES ARE COMPUTED.  THE AGC CLOCKS
# (TIME1 AND TIME2) ARE THEN CHECKED TO SEE IF THE MANEUVER WILL TERMINATE BEFORE THE NEXT UPDATE.  IF
# NOT, KALCMANU CALLS FOR ANOTHER UPDATE (RUN AS A JOB WITH PRIORITY TBD) IN ONE SECOND.  ANY DELAYS IN THIS
# CALLING SEQUENCE ARE AUTOMATICALLY COMPENSATED IN CALLING FOR THE NEXT UPDATE.
#
# IF IT IS FOUND THAT THE MANEUVER IS TO TERMINATE BEFORE THE NEXT UPDATE A ROUTINE IS CALLED (AS A WAIT-
# LIST TASK) TO STOP THE MANEUVER AT THE APPROPRIATE TIME AS EXPLAINED ABOVE.

# Page 344
# CALLING SEQUENCE
#
# IN ORDER TO PERFORM A KALCMANU SUPERVISED MANEUVER, THE COMMANDED GIMBAL ANGLES MUST BE PRECOMPUTED AND
# STORED IN LOCATIONS CPHI, CTHETA, CPSI.  THE USER'S PROGRAM MUST THEN CLEAR STATE SWITCH NO 33 TO ALLOW THE
# ATTITUDE MANEUVER ROUTINE TO PERFORM ANY FINAL P-AXIS YAW INCURRED BY AVOIDING GIMBAL LOCK.  THE MANEUVER IS
# THEN INITIATED BY ESTABLISHING THE FOLLOWING EXECUTIVE JOB
#		       *
#	CAF	PRIO XX
#		     --
#	INHINT
#	TC	FINDVAC
#	2CADR	KALCMAN3
#	RELINT
#
# THE USER'S PROGRAM MAY EITHER CONTINUE OR WAIT FOR THE TERMINATION OF THE MANEUVER.  IF THE USER WISHES TO
# WAIT, HE MAY PUT HIS JOB TO SLEEP WITH THE FOLLOWING INSTRUCTIONS:
#
#	L	TC	BANKCALL
#	L+1	CADR	ATTSTALL
#	L+2	(BAD RETURN)
#	L+3	(GOOD RETURN)
#
# UPON COMPLETION OF THE MANEUVER, THE PROGRAM WILL BE AWAKENED AT L+3 IF THE MANEUVER WAS COMPLETED
# SUCCESSFULLY, OR AT L+2 IF THE MANEUVER WAS ABORTED.  THIS ABORT WOULD OCCUR IF THE INITIAL OR FINAL ATTITUDE
# WAS IN GIMBAL LOCK.
#
# *** NOTA BENE ***  IF IT IS ASSUMED THAT THE DESIRED MANEUVERING RATE (0.5, 2, 5, 10 DEG/SEC) HAS BEEN SELECTED BY
# KEYBOARD ENTRY PRIOR TO THE EXECUTION OF KALCMANU.
#
# IT IS ALSO ASSUMED THAT THE AUTOPILOT IS IN THE AUTO MODE.  IF THE MODE SWITCH IS CHANGED DURING THE
# MANEUVER, KALCMANU WILL TERMINATE VIA GOODEND WITHIN 1 SECOND SO THAT R60 MAY REQUEST A TRIM OF THE S/C ATTITUDE
# SUBROUTINES.
#
# KALCMANU USES A NUMBER OF INTERPRETIVE SUBROUTINES WHICH MAY BE OF GENERAL INTEREST.  SINCE THESE ROUTINES
# WERE PROGRAMMED EXCLUSIVELY FOR KALCMANU, THEY ARE NOT, AS YET, GENERALLY AVAILABLE FOR USE BY OTHER PROGRAMS.
#
# MXM3
# ----
#
# THIS SUBROUTINE MULTIPLIES TWO 3X3 MATRICES AND LEAVES THE RESULT IN THE FIRST 18 LOCATIONS OF THE PUSH
# DOWN LIST, I.E.,
#			[ M     M     M  ]
#			[  0     1     2 ]
#	*		[                ]		*		*
#	M	=	[ M     M     M  ]	=	M1	X	M2
#			[  3     4     5 ]
#			[                ]
#			[ M     M     M  ]
#			[  6     7     8 ]
# Page 345
#                                                                                  *
# INDEX REGISTER X1 MUST BE LOADED WITH THE COMPLEMENT OF THE STARTING ADDRESS FOR M1, AND X2 MUST BE
#                                                        *
# LOADED WITH THE COMPLEMENT OF THE STARTING ADDRESS FOR M2.  THE ROUTINE USES THE FIRST 20 LOCATIONS OF THE PUSH
# DOWN LIST.  THE FIRST ELEMENT OF THE MATRIX APPEARS IN PDO.  PUSH UP FOR M .
#                                                                           8
# TRANSPOS
# --------
#
# THIS ROUTINE TRANSPOSES A 3X3 MATRIX AND LEAVES THE RESULT IN THE PUSH DOWN LIST, I.E.,
#
#	*		* T
#	M	=	M1
#
# INDEX REGISTER X1 MUST CONTAIN THE COMPLEMENT OF THE STARTING ADDRESS FOR M1.  PUSH UP FOR THE FIRST AND SUB-
#                        *
# SEQUENT COMPONENTS OF M.  THIS SUBROUTINE ALSO USES THE FIRST 20 LOCATIONS OF THE PUSH DOWN LIST.
#
# CDU TO DCM
# ----------
#
# THIS SUBROUTINE CONVERTS THREE CDU ANGLES IN T(MPAC) TO A DIRECTION COSINE MATRIX (SCALED BY 2) RELATING
# THE CORRESPONDING S/C ORIENTATIONS TO THE STABLE MEMBER FRAME.  THE FORMULAS FOR THIS CONVERSION ARE
#
#	M	=	COSY COSZ
#	 0
#
#	M	=	-COSY SINZ COSX + SINY SINX
#	 1
#
#	M	=	COSY SINZ SINX + SINY COSX
#	 2
#
#	M	=	SINZ
#	 3
#
#	M	=	COSZ COSX
#	 4
#
#	M	=	-COSZ SINX
#	 5
#
#	M	=	-SINY COSZ
#	 6
#
#	M	=	SINY SINZ COSX + COSY SINX
#	 7
# Page 346
#	M	=	-SINY SINZ SINX + COSY COSX
#	 8
#
# WHERE		X	=	OUTER GIMBAL ANGLE
#		Y	=	INNER GIMBAL ANGLE
#		Z	=	MIDDLE GIMBAL ANGLE
#
# THE INTERPRETATION OF THIS MATRIX IS AS FOLLOWS:
#
# IF A , A , A  REPRESENT THE COMPONENTS OF A VECTOR IN S/C AXES THEN THE COMPONENTS OF THE SAME VECTOR IN
#     X   Y   Z
# STABLE MEMBER AXES (B , B , B ) ARE
#                      X   Y   Z
#
#	[ B  ]			[ A  ]
#	[  X ]			[  X ]
#	[    ]			[    ]
#	[ B  ]		  *	[ A  ]
#	[  Y ]	   =	  M	[  Y ]
#	[    ]			[    ]
#	[ B  ]			[ B  ]
#	[  Z ]			[  Z ]
#
# THE SUBROUTINE WILL STORE THIS MATRIX IN SEQUENTIAL LOCATIONS OF ERASABLE MEMORY AS SPECIFIED BY THE CALLING
#                                                                                                             *
# PROGRAM.  TO DO THIS THE CALLING PROGRAM MUST FIRST LOAD X2 WITH THE COMPLEMENT OF THE STARTING ADDRESS FOR M.
#
# INTERNALLY, THE ROUTINE USES THE FIRST 16 LOCATIONS OF THE PUSH DOWN LIST, ALSO STEP REGISTER S1 AND INDEX
# REGISTER X2.
#
# DCM TO CDU
# ----------
#								       *
# THIS ROUTINE EXTRACTS THE CDU ANGLES FROM A DIRECTION COSINE MATRIX (M SCALED BY 2) RELATING S/C AXIS TO
#                                                                                 *
# STABLE MEMBER AXES.  X1 MUST CONTAIN THE COMPLEMENT OF THE STARTING ADDRESS FOR M.  THE SUBROUTINE LEAVES THE
# CORRESPONDING GIMBAL ANGLES IN V(MPAC) AS DOUBLE PRECISION 1'S COMPLEMENT ANGLES SCALED BY 2PI.  THE FORMULAS
# FOR THIS CONVERSION ARE
#
#	Z 	=	ARCSIN (M  )
#			         3
#
#	Y	=	ARCSIN (-M /COSZ)
#			          6
#
# IF M  IS NEGATIVE, Y IS REPLACED BY PI SGN Y - Y.
#     0
# Page 347
#	X	=	ARCSIN (-M /COSZ)
#			          5
#
# IF M  IS NEGATIVE, X IS REPLACED BY PI SGN X - X.
#     4
#
# THIS ROUTINE DOES NOT SET THE PUSH DOWN POINTER, BUT USES THE NEXT 8 LOCATIONS OF THE PUSH DOWN LIST AND
# RETURNS THE POINTER TO ITS ORIGINAL SETTING.  THIS PROCEDURE ALLOWS THE CALLER TO STORE THE MATRIX AT THE TOP OF
# THE PUSH DOWN LIST.
#
# DELCOMP
# -------
#                                                     *
# THIS ROUTINE COMPUTES THE DIRECTION COSINE MATRIX (DEL) RELATING ON
#                                                                          _
# IS ROTATED WITH RESPECT TO THE FIRST BY AN ANGLE, A, ABOUT A UNIT VECTOR U.  THE FORMULA FOR THIS MATRIX IS
#
#	 *		*	 _ _T              *
#	DEL	=	I COSA + U U  (1 - COSA) + V  SINA
#			                            X
#
# WHERE		*		[ 1    0    0 ]
#		I	=	[ 0    1    0 ]
#				[ 0    0    1 ]
#
#				[    2                             ]
#				[  U           U  U          U  U  ]
#				[   X           X  Y          X  Z ]
#				[                                  ]
#		_ _T		[                 2                ]
#		U U	=	[ U  U          U            U  U  ]
#				[  Y  X          Y            Y  Z ]
#				[                                  ]
#				[                               2  ]
#				[ U  U         U  U           U    ]
#				[  Z  X         Z  Y           Z   ]
#
#
#				[   0		-U		 U  ]
#				[		  Z		  Y ]
#		*		[				    ]
#		V	=	[  U		 0		-U  ]
#		 X		[   Z                             X ]
#				[				    ]
#				[ -U		 U		 0  ]
#				[   Y 		  X		    ]
#
# Page 348
#	_
#	U	=	UNIT ROTATION VECTOR RESOLVED INTO S/C AXES.
#	A	=	ROTATION ANGLE
#
#                        *
# THE INTERPRETATION OF DEL IS AS FOLLOWS:
#
# IF A , A , A  REPRESENT THE COMPONENTS OF A VECTOR IN THE ROTATED FRAME, THEN THE COMPONENTS OF THE SAME
#     X   Y   Z
# VECTOR IN THE ORIGINAL S/C AXES (B , B , B ) ARE
#                                   X   Y   Z
#
#	[ B  ]			[ A  ]
#	[  X ]			[  X ]
#	[    ]			[    ]
#	[ B  ]		  *	[ A  ]
#	[  Y ]	   =	 DEL	[  Y ]
#	[    ]			[    ]
#	[ B  ]			[ B  ]
#	[  Z ]			[  Z ]
#
# THE ROUTINE WILL STORE THIS MATRIX (SCALED UNITY) IN SEQUENTIAL LOCATIONS OF ERASABLE MEMORY BEGINNING WITH
#                                                                                             _
# THE LOCATION CALLED DEL.  IN ORDER TO USE THE ROUTINE, THE CALLING PROGRAM MUST FIRST STORE U (A HALF UNIT
# DOUBLE PRECISION VECTOR) IN THE SET OF ERASABLE LOCATIONS BEGINNING WITH THE ADDRESS CALLED COF.  THE ANGLE, A,
# MUST THEN BE LOADED INTO D(MPAC).
#
# INTERNALLY, THE PROGRAM ALSO USES THE FIRST 10 LOCATIONS OF THE PUSH DOWN LIST.
#
# READCDUK
# --------
#
# THIS BASIC LANGUAGE SUBROUTINE LOADS T(MPAC) WITH THE THREE CDU ANGLES.
#
# SIGNMPAC
# --------
#
# THIS IS A BASIC LANGUAGE SUBROUTINE WHICH LIMITS THE MAGNITUDE OF D(MPAC) TO + OR - DPOSMAX ON OVERFLOW.
#
# PROGRAM STORAGE ALLOCATION
#
#	1)	FIXED MEMORY		1059 WORDS
#	2)	ERASABLE MEMORY		  98
#	3)	STATE SWITCHES		   3
# Page 349
#	4)	FLAGS			   1
#
# JOB PRIORITIES
#
#	1)	KALCMANU		TBD
#	2)	ONE SECOND UPDATE	TBD
#
# SUMMARY OF STATE SWITCHES AND FLAGWORDS USED BY KALCMANU.
#
#	STATE		FLAGWRD 2	SETTING		MEANING
#	SWITCH NO.	BIT NO.
#
#	  *
#	31		14		0		MANEUVER WENT THROUGH GIMBAL LOCK
#					1		MANEUVER DID NOT GO THROUGH GIMBAL LOCK
#	  *
#	32		13		0		CONTINUE UPDATE PROCESS
#					1		START UPDATE PROCESS
#
#	33		12		0		PERFORM FINAL P AXIS YAW IF REQUIRED
#					1		IGNORE ANY FINAL P-AXIS YAW
#
#	34		11		0		SIGNAL END OF KALCMANU
#					1		KALCMANU IN PROCESS.	USER MUST SET SWITCH BEFORE INITIATING
#
#	* INTERNAL TO KALCMANU
#
# SUGGESTIONS FOR PROGRAM INTEGRATION
#
# THE FOLLOWING VARIABLES SHOULD BE ASSIGNED TO UNSWITCH ERASABLE:
#
#	CPHI
#	CTHETA
#	CPSI
#	POINTVSM +5
#	SCAXIS 	 +5
#	DELDCDU
#	DELDCDU1
#	DELDCDU2
#	RATEINDX
#
# THE FOLLOWING SUBROUTINES MAY BE PUT IN A DIFFERENT BANK
#
#	MXM3
# Page 350
#	TRANSPGS
#	SIGNMPAC
#	READCDUK
#	CDUTODCM

# Page 351
		BANK	15
		SETLOC	KALCMON1
		BANK

		EBANK=	BCDU

# THE THREE DESIRED CDU ANGLES MUST BE STORED AS SINGLE PRECISION TWO'S COMPLEMENT ANGLES IN THE THREE SUCCESSIVE
# LOCATIONS, CPHI, CTHETA, CPSI.

		COUNT*	$$/KALC
KALCMAN3	TC	INTPRET		# PICK UP THE CURRENT CDU ANGLES AND
		RTB			#	COMPUTE THE MATRIX FROM INITIAL S/C
			READCDUK	#	AXES TO FINAL S/C AXES.
		STORE	BCDU		# STORE INITIAL S/C ANGLES
		SLOAD	ABS		# CHECK THE MAGNITUDE OF THE DESIRED
			CPSI		# MIDDLE GIMBAL ANGLE
		DSU	BPL
			LOCKANGL	# IF GREATER THAN 70 DEG ABORT MANEUVER
			TOOBADF
		AXC,2	TLOAD
			MIS
			BCDU
		CALL			# COMPUTE THE TRANSFORMATION FROM INITIAL
			CDUTODCM	# S/C AXES TO STABLE MEMBER AXES
		AXC,2	TLOAD
			MFS		# PREPARE TO CALCULATE ARRAY MFS
			CPHI
		CALL
			CDUTODCM
SECAD		AXC,1	CALL		# MIS AND MFS ARRAYS CALCULATED		$2
			MIS
			TRANSPOS
		VLOAD	STADR
		STOVL	TMIS +12D
		STADR
		STOVL	TMIS +6
		STADR
		STORE	TMIS		# TMIS = TRANSPOSE(MIS) SCALED BY 2
		AXC,1	AXC,2
			TMIS
			MFS
		CALL
			MXM3
		VLOAD	STADR
		STOVL	MFI +12D
		STADR
		STOVL	MFI +6
		STADR
		STORE	MFI		# MFI = TMIS MFS (SCALED BY 4)
		SETPD	CALL		# TRANSPOSE MFI IN PD LIST
# Page 352
			18D
			TRNSPSPD
		VLOAD	STADR
		STOVL	TMFI 	+12D
		STADR
		STOVL	TMFI 	+6
		STADR
		STORE	TMFI		# TMFI = TRANSPOSE (MFI) SCALED BY 4

# CALCULATE COFSKEW AND MFISYM

		DLOAD	DSU
			TMFI 	+2
			MFI 	+2
		PDDL	DSU		# CALCULATE COF SCALED BY 2/SIN(AM)
			MFI 	+4
			TMFI 	+4
		PDDL	DSU
			TMFI 	+10D
			MFI 	+10D
		VDEF
		STORE	COFSKEW		# EQUALS MFISKEW

# CALCULATE AM AND PROCEED ACCORDING TO ITS MAGNITUDE

		DLOAD	DAD
			MFI
			MFI 	+16D
		DSU	DAD
			DP1/4TH
			MFI 	+8D
		STORE	CAM		# CAM = (MFI0+MFI4+MFI8-1)/2 HALF SCALE
		ARCCOS
		STORE	AM		# AM=ARCCOS(CAM)	(AM SCALED BY 2)
		DSU	BPL
			MINANG
			CHECKMAX
		TLOAD			# MANEUVER LESS THAN .25 DEGREES
			CPHI		# GO DIRECTLY INTO ATTITUDE HOLD
		STCALL	CDUXD		# ABOUT COMMANDED ANGLES
			TOOBADI		# STOP RATE AND EXIT

CHECKMAX	DLOAD	DSU
			AM
			MAXANG
		BPL	VLOAD
			ALTCALC		# UNIT
			COFSKEW		# COFSKEW
		UNIT
		STORE	COF		# COF IS THE MANEUVER AXIS
# Page 353
		GOTO			# SEE IF MANEUVER GOES THRU GIMBAL LOCK
			LOCSKIRT
ALTCALC		VLOAD	VAD		# IF AM GREATER THAN 170 DEGREES
			MFI
			TMFI
		VSR1
		STOVL	MFISYM
			MFI 	+6
		VAD	VSR1
			TMFI 	+6
		STOVL	MFISYM 	+6
			MFI 	+12D
		VAD	VSR1
			TMFI 	+12D
		STORE	MFISYM 	+12D	# MFISYM=(MFI+TMFI)/2	SCALED BY 4

# CALCULATE COF

		DLOAD	SR1
			CAM
		PDDL	DSU		# PDO CAM				$4
			DPHALF
			CAM
		BOVB	PDDL		# PS2 1 - CAM				$2
			SIGNMPAC
			MFISYM 	+16D
		DSU	DDV
			0
			2
		SQRT	PDDL		# COFZ = SQRT(MFISYM8-CAM)/(1-CAM)
			MFISYM 	+8D	#				$ ROOT 2
		DSU	DDV
			0
			2
		SQRT	PDDL		# COFY = SQRT(MFISYM4-CAM)/(1-CAM)  $ROOT2
			MFISYM
		DSU	DDV
			0
			2
		SQRT	VDEF		# COFX = SQRT(MFISYM-CAM)/(1-CAM)  $ROOT 2
		UNIT
		STORE	COF

# DETERMINE LARGEST COF AND ADJUST ACCORDINGLY

COFMAXGO	DLOAD	DSU
			COF
			COF 	+2
		BMN	DLOAD		# COFY G COFX
# Page 354
			COMP12
			COF
		DSU	BMN
			COF 	+4
			METHOD3		# COFZ G COFX OR COFY
		GOTO
			METHOD1		# COFX G COFY OR COFZ
COMP12		DLOAD	DSU
			COF 	+2
			COF 	+4
		BMN
			METHOD3		# COFZ G COFY OR COFX

METHOD2		DLOAD	BPL		# COFY MAX
			COFSKEW +2	# UY
			U2POS
		VLOAD	VCOMP
			COF
		STORE	COF
U2POS		DLOAD	BPL
			MFISYM 	+2	# UX UY
			OKU21
		DLOAD	DCOMP		# SIGN OF UX OPPOSITE garbled
			COF
		STORE	COF
OKU21		DLOAD	BPL
			MFISYM +10D	# UY UZ
			LOCSKIRT
		DLOAD	DCOMP		# SIGN OF UZ OPPOSITE TO UY
			COF 	+4
		STORE	COF 	+4
		GOTO
			LOCSKIRT
METHOD1		DLOAD	BPL		# COFX MAX
			COFSKEW		# UX
			U1POS
		VLOAD	VCOMP
			COF
		STORE	COF
U1POS		DLOAD	BPL
			MFISYM 	+2	# UX UY
			OKU12
		DLOAD	DCOMP
			COF 	+2	# SIGN OF UY OPPOSITE TO UX
		STORE	COF 	+2
OKU12		DLOAD	BPL
			MFISYM 	+4	# UX UZ
			LOCSKIRT
		DLOAD	DCOMP		# SIGN OF UZ OPPOSITE TO UY
			COF 	+4
# Page 355
		STORE	COF 	+4
		GOTO
			LOCSKIRT
METHOD3		DLOAD	BPL		# COFZ MAX
			COFSKEW +4	# UZ
			U3POS
		VLOAD	VCOMP
			COF
		STORE	COF
U3POS		DLOAD	BPL
			MFISYM 	+4	# UX UZ
			OKU31
		DLOAD	DCOMP
			COF		# SIGN OF UX OPPOSITE TO UZ
		STORE	COF
OKU31		DLOAD	BPL
			MFISYM 	+10D	# UY UZ
			LOCSKIRT
		DLOAD	DCOMP
			COF 	+2	# SIGN OF UY OPPOSITE TO UZ
		STORE	COF 	+2
		GOTO
			LOCSKIRT
# Page 356
# MATRIX OPERATIONS

		BANK	13
		SETLOC	KALCMON2
		BANK

		EBANK=	BCDU

MXM3		SETPD	VLOAD*		# MXM3 MULTIPLIES 2 3X3 MATRICES
			0		# AND LEAVES RESULT IN PD LIST
			0,1		# AND MPAC
		VXM*	PDVL*
			0,2
			6,1
		VXM*	PDVL*
			0,2
			12D,1
		VXM*	PUSH
			0,2
		RVQ

# RETURN WITH MIXM2 IN PD LIST

TRANSPOS	SETPD	VLOAD*		# TRANSPOS TRANSPOSES A 3X3 MATRIX
			0		# 	AND LEAVES RESULT IN PD LIST
			0,1		# MATRIX ADDRESS IN XR1
		PDVL*	PDVL*
			6,1
			12D,1
		PUSH			# MATRIX IN PD
TRNSPSPD	EXIT			# ENTER WITH MATRIX AT 0 IN PD LIST
		INDEX	FIXLOC
		DXCH	12
		INDEX	FIXLOC
		DXCH	16
		INDEX	FIXLOC
		DXCH	12
		INDEX	FIXLOC
		DXCH	14
		INDEX	FIXLOC
		DXCH	4
		INDEX	FIXLOC
		DXCH	14
		INDEX	FIXLOC
		DXCH	2
		INDEX	FIXLOC
		DXCH	6
		INDEX	FIXLOC
		DXCH	2
# Page 357
		TC	INTPRET
		RVQ

		BANK	15
		SETLOC	KALCMON1
		BANK

		EBANK=	BCDU

MINANG		2DEC	0.00069375

MAXANG		2DEC	0.472222222

# GIMBAL LOCK CONSTANTS

# D = MGA CORRESPONDING TO GIMBAL LOCK = 60 DEGREES
#	NGL = BUFFER ANGLE (TO AVOID DIVISIONS BY ZERO) = 2 DEGREES

SD		2DEC	.433015		# = SIN(D)			$2

K3S1		2DEC	.86603		# = SIN(D)			$1

K4		2DEC	-.25		# = -COS(D)			$2

K4SQ		2DEC	.125		# = COS(D)COS(D)		$2

SNGLCD		2DEC	.008725		# = SIN(NGL)COS(D)		$2

CNGL		2DEC	.499695		# COS(NGL)			$2

LOCKANGL	DEC	.388889		# = 70 DEGREES

# INTERPRETIVE SUBROUTINE TO READ THE CDU ANGLES

READCDUK	CA	CDUZ		# LOAD T(MPAC) WITH CDU ANGLES
		TS	MPAC 	+2
		EXTEND
		DCA	CDUX		# AND CHANGE MODE TO TRIPLE PRECISION
		TCF	TLOAD 	+6

CDUTODCM	AXT,1	SSP
		OCT	3
			S1
		OCT	1		# SET XR1, S1, AND PD FOR LOOP
		STORE	7
		SETPD
			0
LOOPSIN		SLOAD*	RTB
			10D,1
			CDULOGIC
# Page 358
		STORE	10D		# LOAD PD WITH 	0 SIN(PHI)
		SIN	PDDL		#		2 COS(PHI)
			10D		#		4 SIN(THETA)
		COS	PUSH		#		6 COS(THETA)
		TIX,1	DLOAD		#		8 SIN(PSI)
			LOOPSIN		#		10 COS(PSI)
			6
		DMP	SL1
			10D
		STORE	0,2		# C0 = COS(THETA)COS(PSI)
		DLOAD	DMP
			4
			0
		PDDL	DMP		# (PD6 SIN(THETA)SIN(PHI))
			6
			8D
		DMP	SL1
			2
		BDSU	SL1
			12D
		STORE	2,2		# C1=-COS(THETA)SIN(PSI)COS(PHI)
		DLOAD	DMP
			2
			4
		PDDL	DMP		# (PD7 COS(PHI)SIN(THETA)) SCALED 4
			6
			8D
		DMP	SL1
			0
		DAD	SL1
			14D
		STORE	4,2		# C2=COS(THETA)SIN(PSI)SIN(PHI)
		DLOAD
			8D
		STORE	6,2		# C3=SIN(PSI)
		DLOAD
			10D
		DMP	SL1
			2
		STORE	8D,2		# C4=COS(PSI)COS(PHI)
		DLOAD	DMP
			10D
			0
		DCOMP	SL1
		STORE	10D,2		# C5=-COS(PSI)SIN(PHI)
		DLOAD	DMP
			4
			10D
		DCOMP	SL1
		STORE	12D,2		# C6=-SIN(THETA)COS(PSI)
# Page 359
		DLOAD
		DMP	SL1		# (PUSH UP 7)
			8D
		PDDL	DMP		# (PD7 COS(PHI)SIN(THETA)SIN(PSI)) SCALE 4
			6
			0
		DAD	SL1		# (PUSH UP 7)
		STADR			# C7=COS(PHI)SIN(THETA)SIN(PSI)
		STORE	14D,2		# 	+COS(THETA)SIN(PHI)
		DLOAD
		DMP	SL1		# (PUSH UP 6)
			8D
		PDDL	DMP		# (PD6 SIN(THETA)SIN(PHI)SIN(PSI)) SCALE 4
			6
			2
		DSU	SL1		# (PUSH UP 6)
		STADR
		STORE	16D,2		# C8=-SIN(THETA)SIN(PHI)SIN(PSI)
		RVQ			# +COS(THETA)COS(PHI)

# CALCULATION OF THE MATRIX DEL......
#
#	 *         *           __T           *
#	DEL = (IDMATRIX)COS(A)+UU (1-COS(A))+UX SIN(A)		SCALED 1
#	      _
#	WHERE U IS A UNIT VECTOR (DP SCALED 2) ALONG THE AXIS OF ROTATION.
#	A IS THE ANGLE OF ROTATION (DP SCALED 2)
#	                                    _
#	UPON ENTRY, THE STARTING ADDRESS OF U IS COF, AND A IS IN MPAC

DELCOMP		SETPD	PUSH		# MPAC CONTAINS THE ANGLE A
 			0
		SIN	PDDL		# PD0 = SIN(A)
		COS	PUSH		# PD2 = COS(A)
		SR2	PDDL		# PD2 = COS(A)				$8
		BDSU	BOVB
			DPHALF
			SIGNMPAC
		PDDL			# PDA = 1-COS(A)

# COMPUTE THE DIAGONAL COMPONENTS OF DEL

			COF
		DSQ	DMP
			4
		DAD	SL3
			2
		BOVB
			SIGNMPAC
# Page 360
		STODL	KEL		# UX UX(1-COS(A)) +COS(A)		$1
			COF 	+2
		DSQ	DMP
			4
		DAD	SL3
			2
		BOVB
			SIGNMPAC
		STODL	KEL 	+8D	# UY UY(1-COS(A)) +COS(A)		$1
			COF 	+4
		DSQ	DMP
			4
		DAD	SL3
			2
		BOVB
			SIGNMPAC
		STORE	KEL 	+16D	# UZ UZ(1-COS(A)) +COS(A)		$1

# COMPUTE THE OFF DIAGONAL TERMS OF DEL

		DLOAD	DMP
			COF
			COF	+2
		DMP	SL1
			4
		PDDL	DMP		# D6	 UX UY (1-COS A)		$4
			COF 	+4
			0
		PUSH	DAD		# D8 	UZ SIN A			$4
			6
		SL2	BOVB
			SIGNMPAC
		STODL	KEL 	+6
		BDSU	SL2
		BOVB
			SIGNMPAC
		STODL	KEL 	+2
			COF
		DMP	DMP
			COF 	+4
			4
		SL1	PDDL		# D6 	UX UZ (1-COS A)			$4
			COF 	+2
		DMP	PUSH		# D8	UY SIN(A)
			0
		DAD	SL2
			6
		BOVB
			SIGNMPAC
		STODL	KEL 	+4	# UX UZ (1-COS(A))+UY SIN(A)
# Page 361
		BDSU	SL2
		BOVB
			SIGNMPAC
		STODL	KEL	 +12D	# UX UZ (1-COS(A))-UY SIN(A)
			COF 	+2
		DMP	DMP
			COF 	+4
			4
		SL1	PDDL		# D6	UY UZ (1-COS(A))		$ 4
			COF
		DMP	PUSH		# D8	UX SIN(A)
			0
		DAD	SL2
			6
		BOVB
			SIGNMPAC
		STODL	KEL 	+14D	# UY UZ(1-COS(A)) +UX SIN(A)
		BDSU	SL2
		BOVB
			SIGNMPAC
		STORE	KEL 	+10D	# UY UZ (1-COS(A)) -UX SIN(A)
		RVQ

# DIRECTION COSINE MATRIX TO CDU ANGLE ROUTINE
# X1 CONTAINS THE COMPLEMENT OF THE STARTING ADDRESS FOR MATRIX (SCALED 2).
# LEAVE CDU ANGLES SCALED 2PI IN V(MPAC).
# COS(MGA) WILL BE LEFT IN S1 (SCALED 1).
#
# THE DIRECTION COSINE MATRIX RELATING S/C AXES TO STABLE MEMBER AXES CAN BE WRITTEN AS:
#
#	C  = COS(THETA) COS(PSI
#	 0
#
#	C  = -COS(THETA) SIN(PSI) COS(PHI) + SIN(THETA) SIN(PHI)
#	 1
#
#	C  = COS(THETA) SIN(PSI) SIN(PHI) + SIN(THETA) COS(PHI)
#	 2
#
#	C  = SIN(PSI)
#	 3
#
#	C  = COS(PSI) COS(PHI)
#	 4
#
#	C  = -COS(PSI) SIN(PHI)
#	 5
#
#	C  = -SIN(THETA) COS(PSI)
#	 6
#
#	C  = SIN(THETA) SIN(PSI) COS(PHI) + COS (THETA) SIN(PHI)
#	 7
#
#	C  = -SIN(THETA) SIN(PSI) SIN(PHI) + COS(THETA)COS(PHI)
#	 8
# Page 362
#
# WHERE	PHI = OGA
#	THETA = IGA
#	PSI = MGA

DCMTOCDU	DLOAD*	ARCSIN
			6,1
		PUSH	COS		# PD +0 	PSI
		SL1	BOVB
			SIGNMPAC
		STORE	S1
		DLOAD*	DCOMP
			12D,1
		DDV	ARCSIN
			S1
		PDDL*	BPL		# PD +2		THETA
			0,1		# MUST CHECK THE SIGN OF COS(THETA)
			OKTHETA		# TO DETERMINE THE PROPER QUADRANT.
		DLOAD	DCOMP
		BPL	DAD
			SUHALFA
			DPHALF
		GOTO
			CALCPHI
SUHALFA		DSU
			DPHALF
CALCPHI		PUSH
OKTHETA		DLOAD*	DCOMP
			10D,1
		DDV	ARCSIN
			S1
		PDDL*	BPL		# PUSH DOWN PHI
			8D,1
			OKPHI
		DLOAD	DCOMP		# PUSH UP PHI
		BPL	DAD
			SUHALFAP
			DPHALF
		GOTO
			VECOFANG
SUHALFAP	DSU	GOTO
			DPHALF
			VECOFANG
OKPHI		DLOAD			# PUSH UP PHI
VECOFANG	VDEF	RVQ
# Page 363
# ROUTINES FOR TERMINATING THE AUTOMATIC MANEUVER AND RETURNING TO USER.

TOOBADF		EXIT
		TC	ALARM
		OCT	00401

		TCF	NOGO		# DO NOT ZERO ATTITUDE ERRORS

		TC	BANKCALL
		CADR	ZATTEROR	# ZERO ATTITUDE ERRORS

NOGO		TC	BANKCALL
		CADR	STOPRATE	# STOP RATES

		CAF	TWO
		INHINT			# ALL RETURNS ARE NOW MADE VIA GOODEND
		TC	WAITLIST
		EBANK=	BCDU
		2CADR	GOODMANU

		TCF	ENDOFJOB

TOOBADI		EXIT
		TCF	NOGO