### FILE="Main.annotation"
## Copyright:   Public domain.
## Filename:    ENTRY_LEXICON.agc
## Purpose:     Part of the source code for Comanche, build 055. It
##              is part of the source code for the Command Module's
##              (CM) Apollo Guidance Computer (AGC), Apollo 11.
## Assembler:   yaYUL
## Reference:   pp. 837-843
## Contact:     Ron Burkey <info@sandroid.org>
## Website:     http://www.ibiblio.org/apollo.
## Mod history: 2009-05-12 RSB	Adapted from Colossus249 file of the same
##				name and Comanche 055 page images.
##		2016-12-11 RSB	Proofed comments with octopus/ProoferComments
##				and fixed the errors found.
##		2017-01-08 RSB	Fixed comment errors detected in cross-diff vs
##				Colossus 249.
##		2017-01-22 RSB	Fixed comment errors detected in cross-diff vs
##				Artemis 72.
##
## The contents of the "Comanche055" files, in general, are transcribed 
## from scanned documents. 
##
##       Assemble revision 055 of AGC program Comanche by NASA
##       2021113-051.  April 1, 1969.  
##
##       This AGC program shall also be referred to as Colossus 2A
##
##       Prepared by
##                       Massachusetts Institute of Technology
##                       75 Cambridge Parkway
##                       Cambridge, Massachusetts
##
##       under NASA contract NAS 9-4065.
##
## Refer directly to the online document mentioned above for further
## information.  Please report any errors to info@sandroid.org.

## Page 837
# VARIABLE	DESCRIPTION				MAXIMUM VALUE *		COMPUTER NAME
# --------	-----------				------- -----		-------- ----
# -
# URT0		INITIAL TARGET VECTOR			2 (UNIT VECTOR)		= RTINIT
# -
# UZ		UNIT VECTOR NORTH			1			= UNITW
# -
# V		VELOCITY VECTOR				2 VSAT			= VEL
# -
# R		POSITION VECTOR				2 EXP 29 METERS		= RN
# -
# VI 		INERTIAL VELOCITY			128 M/CENTISEC		= VN
# -
# RTE		VECTOR EAST AT INITIAL TARGET		2			= RTEAST
# -
# UTR		NORMAL TO RTE AND UZ			2			= RTNORM
# -
# URT		TARGET VECTOR				2			= RT
# -
# UNI		UNIT NORMAL TO TRAJECTORY PLANE		2	
# -
# DELV		INTEGRATED ACCEL. FROM PIPAS		5.85 16384 CM/S
# -
# G		GRAVITY VECTOR				128 M/CENTISEC		= GDT/2
#
# A0		INITIAL DRAG FOR UPCONTRL		805 FPSS		FPSS=FT/SEC/SEC
#
# AHOOKDV	TERM IN GAMMAL CALC. = AHOOK DVL	16
#
# A1		DRAG VALUE IN FACTOR CALCULATION	805 FPSS
#
# ALP		CONST FOR UPCONTRL			1
#
# ASKEP		KEPLER RANGE				21600 NM		NM = NAUTICAL MILE
#
# ASP1		FINAL PHASE RANGE			21600 NM
#
# ASPUP		UP-RANGE				21600 NM
#
# ASP3		GAMMA CORRECTION			21600 NM
#
# ASPDWN	RANGE DOWN TO PULL-UP			21600 NM
#
# ASP		PREDICTED RANGE				21600 NM		NOT STORED
#
# COSG		COSINE(GAMMAL)				2			= COSG/2
#
# C/D0		RECIPROCAL DRAG, -4/D0 B-8		64/FPSS
#
# D		TOTAL ACCELERATION			805 FPSS
#
# D0		CONTROLLED CONSTANT D			805 FPSS
#
# DHOOK		TERM IN GAMMAL COMPUTATION		805 FPSS
#
# DIFF		THETNM-ASP (RANGE DIFFERENCE)		21600 NM
#
# DIFFOLD	PREVIOUS VALUE OF DIFF			21600 NM
#
# DLEWD		CHANGE IN LEWD				1
#
# DR		REFERENCE DRAG FOR DOWNCONTROL		805 FPSS		NOT STORED
#
# DREFR		REFERENCE DRAG				805 FPSS		NOT STORED
#
# DVL		VS1-VL					2 VSAT
#
# E		ECCENTRICITY				4			NOT STORED
#
# F1		DRANGE/D DRAG	(FINAL PHASE)		2700/805		= FX +5
#
# F2		DRANGE/D RDOT	(FINAL PHASE)		2700/2VS NM/FPS		= FX +4
## Page 838
#
# F3		DRANGE/D (L/D)				2700 NM			= FX
#
# FACT1		CONST FOR UPCONTRL			805 FPSS
#
# FACT2		CONST FOR UPCONTRL			1/805 FPSS
#
# FACTOR	USED IN UPCONTRL			1			* MAXIMUM VALUE DENOTES UNSCALED
#								
# GAMMAL	FLIGHT PATH ANGLE AT VL			1 RADIAN		  VARIABLE VALUE WHEN SCALED
#
# GAMMAL1	SIMPLE FORM OF GAMMAL			1 RADIAN		  VARIABLE HAS MAXIMUM VALUE OF ONE.

## Page 839
# VARIABLE	DESCRIPTION				MAXIMUM VALUE		COMPUTER NAME
# --------	-----------				-------	-----		-------- ----
#
# HEADSUP	INDICATOR FOR INITIAL ROLL		1
#
# KA		DRAG TO LIFT UP IF DOWN			805 FPSS		= KAT
#
# KLAT		LATERAL SWITCH GAIN			1			(NOM = .0125)
#
# K2ROLL	INDICATOR FOR ROLL SWITCH		
#
# LAD		MAX L/D (MIN ACTUAL VEHICLE L/D)	1
#
# LADPAD	NOMINAL VEHICLE L/D, SP PAD LOAD	1			(NOM = 0.3)
#
# LATANG	LATERAL RANGE				4 RADIANS
#
# LEQ		EXCESS C.F. OVER GRAV=(VSQ-1)GS		128.8 FPSS
#
# LEWD		UPCONTROL REFERENCE L/D			1
#
# LOD		FINAL PHASE L/D				1			(NOM = 0.18)
#
# LODPAD	FINAL PHASE L/D, SP PAD LOAD		1
#
# L/D		DESIRED LIFT TO DRAG RATIO		1
#		(VERTICAL PLANE)
# 
# L/D1		TEMP STORAGE FOR L/D IN LATERAL		1
#
# L/DCMINR	LAD COS(15DEG)				1			(NOM = 0.2895)
#
# PREDANGL	PREDICTED RANGE	(FINAL PHASE)		2700 NM			= PREDANG
#
# Q2		FINAL PHASE RANGE -23500 Q3		21600 NM
#		Q2 = FCN(LAD)
#
# Q7		MINIMUM DRAG FOR UPCONTROL		805FPSS
#
# RDOT		ALTITUDE RATE				2 VSAT
#
# RDOTREF	REFERENCE RDOT FOR UPCONTROL		2 VSAT
#
# RDTR		REFERENCE RDOT FOR DOWNCONT		2 VSAT			NOT SAVED
#
# ROLLC		ROLL COMMAND				1 REVOLUTION
#
# RTOGO		RANGE TO GO (FINAL PHASE)		2700 NM			= FX +2
#
# SL		SINE OF LATITUDE			1			NOT SAVED
#
# T		TIME					B 28 CENTISEC		= TIME2,TIME1
#
# THETA		DESIRED RANGE (RADIANS)			2 PI RADIANS		= THETAH
#
# THETNM	DESIRED RANGE (NM)			21600 NM		NON EXISTENT
#
# V		VELOCITY MAGNITUDE			2 VSAT
# 
# V1		INITIAL VELOCITY FOR UPCONTROL		2 VSAT
#
# VL		EXIT VELOCITY FOR UPCONTROL		2 VSAT
#
# VREF		REFERENCE VELOCITY FOR UPCONTROL	2 VSAT
#
# VS1		VSAT OR V1, WHICHEVER IS SMALLER	2 VSAT
#		  2     2
# VBARS		VL /VSAT				4
#					   2     2
# VSQ		NORMALISED VEL. SQUARED = V /VSAT	4			= VSQUARE
#
# WT		EARTH RATE TIMES TIME			1 REVOLUTION		NOT SAVED
#										= WIE (DTEAROT)
# X		INTERMEDIATE VARIABLE IN G-LIMITER	2 VSAT	 		NOT SAVED
#
# Y		LATERAL MISS LIMIT			4 RADIANS		NOT SAVED

## Page 840
# EXTRA COMPUTER ERASABLE LOCATIONS NOT SHOWN ON FLOW CHARTS
# -----------------------------------------------------------
#
# VARIABLE	DESCRIPTION				MAXIMUM VALUE
# --------	-----------				------- -----
#
# GOTOADDR	ADDRESS SELECTED BY SEQUENCER
#
# XPIPBUF	BUFFER TO STORE X PIPA COUNTS
#
# YPIPBUF	BUFFER TO STORE Y PIPA COUNTS
#
# ZPIPBUF	BUFFER TO STORE Z PIPA COUNTS
#
# PIPCTR	COUNTS PASSES THRU PIPA READ ROUTINE
#
# JJ		INDEX IN FINAL PHASE TABLE LOOK-UP
#
# MM		INDEX IN FINAL PHASE TABLE LOOK-UP
#
# GRAD		INTERPOLATION FACTOR IN FINAL PHASE
#
# FX		DRANGE/D L/D = F3			2700 NM
#
# FX +1		AREF					805 FPSS
#
# FX +2		RTOGO					2700 NM
#
# FX +3		RDOTREF					VSAT/4
#
# FX +4		DRANGE/D RDOT = F2			21600/2VS NM/FPS
#
# FX +5		DRANGE/D DRAG = F1			2700/805 NM/FPSS
#
# TEM1B		TEMPORARY LOCATION
#
# TIME/RTO	TIME OF INITIAL TARGET RTINIT		B 28 CENTISEC
#
# DTEAROT	EST TIME BETWEEN RTINIT AND RT		B 28 CENTISEC
# -
# UNITV		UNIT V VECTOR				2
# -
# UNITR		UNIT R VECTOR				2
#  -
# -VREL		NEGATIVE VELOCITY REL TO ATMOSP		2 VSAT

# COMPUTER SWITCHES					INITIAL STATE		CM/FLAGS = STATE +6
# -------- --------					-------------		-------------------
#
# ENTRYDSP	DO ENTRY DISPLAY, IF SET		NON-BRANCH (1)		92D, BIT 13
# GONEPAST	INDICATES OVERSHOOT OF TARGET		NON-BRANCH (0)		95D, BIT 10
# RELVELSW	RELATIVE VELOCITY SWITCH		NON-BRANCH (0)		96D, BIT 9
# EGSW		FINAL PHASE SWITCH			NON-BRANCH (0)		97D, BIT 8
# FIRSTPAS	INITIAL PASS THRU HUNTEST		NON-BRANCH (0)		98D, BIT 7
# HIND		INDICATES ITERATION IN HUNTEST		NON-BRANCH (0)		99D, BIT 6
# INRLSW	INDICATES INIT ROLL ATTITUDE SET	NON-BRANCH (0)		100D, BIT 5
# LATSW		INHIBIT DOWNLIFT SWITCH IF NOT SET	    BRANCH (1)		101D, BIT 4
# .05GSW	INDICATES DRAG EXCEEDS .05 GS		    BRANCH (0)		102D, BIT 3
#
# GONEBY	INDICATES GONE PAST TARGET (SET)	SELF-INITIALZNG	112D, BIT 8

## Page 841
# CONSTANTS AND GAINS							VALUE
# -------------------							-----
#
# C1		FACTOR IN ALP COMPUTATION				1.25
# C16		CONSTD GAIN ON DRAG					.01
# C17		CONSTD GAIN ON RDOT					.001
# C18		BIAS VEL. FOR FINAL PHASE START				500	FPS
# C20		MAX DRAG FOR DOWN-LIFT					175	FPSS
# CHOOK		FACTOR IN AHOOK COMPUTATION				.25
# CH1		FACTOR IN GAMMAL COMPUTATION				1.0
# COS15		COS( 15 DEG )						.965
# DLEWD0	INITIAL VARIATION IN LEWD				-.05
# D2		DRAG TO CHANGE LEWD					175	FPSS
# DT		COMPUTATION CYCLE TIME INTERVAL				2	SEC.
# GMAX		MAXIMUM ACCELERATION					257.6	FPSS	(8 G-S)
# KA1		FACTOR IN KA CALC					1.3	GS
# KA2		FACTOR IN KA CALC					.2 	GS
# KA3		FACTOR IN D0 CALC					90 FPSS
# KA4		FACTOR IN D0 CALC					40 FPSS
# KB1		OPTIMIZED UPCONTROL GAIN				3.4
# KB2		OPTIMIZED UPCONTROL GAIN				.0034
# KDMIN		INCREMENT ON Q7 TO DETECT END OF KEPLER PHASE		.5	FPSS
# KTETA		TIME OF FLIGHT CONSTANT					1000
# KLAT1		FACTOR IN KLAT CALC					1/24
# K44		GAIN USED IN INITIAL ROLL SECTION			19749550 FPS
# LATBIAS	LATERAL SWITCH BIAS TERM				.41252961 NM
# LEWD1		NOMINAL UPCONTROL L/D					.15
# POINT1	FACTOR TO REDUCE UPCONTROL GAIN				.1
# Q2		FINAL PHASE RANGE - 23500 Q3				-1002	NM
# Q3		FINAL PHASE DRANGE/D V					.07	NM/FPS
# Q5		FINAL PHASE DRANGE/D GAMMA				7050	NM/RAD
# Q6		FINAL PHASE INITIAL FLIGHT PATH ANGLE			.0349	RAD
# Q7F		MIN DRAG FOR UPCONTROL					6	FPSS
# Q7MIN		MIN VALUE FOR Q7 IN FACTOR CALCULATION			40	FPSS
# Q19		FACTOR IN GAMMAL1 CALCULATION				.5
# Q21		FACTOR IN Q2 CALCULATION.				1000	NM
# Q22		FACTOR IN Q2 CALCULATION.				-1302	NM
# VFINAL1	VELOCITY TO START FINAL PHASE ON INITIAL ENTRY		27000	FPS
# VFINAL	FACTOR IN INITIAL UP-DOWN CALC				26600	FPS
# VLMIN		MINIMUM VL						18000	FPS
# VMIN		VELOCITY TO SWITCH TO RELATIVE VEL			VSAT/2
# VRCONTRL	RDOT TO START INTO HUNTEST				700	FPS
#		VRCONT=COMPUTER NAME
# 25NM		TOLERANCE TO STOP RANGE ITERATION			25	NM
# VQUIT		VELOCITY TO STOP STEERING				1000	FPS

## Page 842
# CONVERSION FACTORS AND SCALING CONSTANTS
# ---------- ------- --- ------- ---------
#
# ATK	ANGLE IN RAD TO NM						3437.7468	NM/RAD
# GS	NOMINAL G VALUE FOR SCALING					32.2		FPSS
# HS	ATMOSPHERE SCALE HEIGHT						28500		FT
# J	GRAVITY HARMONIC COEFFICIENT					.00162346	
# KWE	EQUATORIAL EARTH RATE						1546.70168	FPS
# MUE	EARTH GRAVITATIONAL CONSTANT					3.986032233 E14	CUBIC M/ SEC SEC
# RE	EARTH RADIUS							21202900	FT
# REQ	EARTH EQUATORIAL RADIUS						20925738.2	FT
# VSAT	SATELLITE VELOCITY AT RE					25766.1973	FPS
# WIE	EARTH RATE							.0000729211505	RAD/SEC
 
#		(END GSOP AS-278, VOL 1, FIG. 5.6-3 CONSTANTS, GAINS, ETC.)

# DISPLAY QUANTITIES
# ------------------
#
# (SEE SECTION 4 OF THE GSOP FOR SIGN CONVENTIONS.)
#
# VARIABLE	DESCRIPTION				MAXIMUM VALUE
# --------	-----------				------- -----
#
# QMAX		PREDICTED MAXIMUM ENTRY ACCEL		163.84 GS	N 60
# VPRED		PREDICTED VELOCITY AT ALTITUDE		128 M/CENTISEC	N 60
# 		400K FT ABOVE FISCHER RADIUS.
# GAMMAEI	PREDICTED GAMMA AT ALTITUDE		1 REVOLUTION	N 60
#		400K FT ABOVE FISCHER RADIUS.
# D		DRAG ACCELERATION			805 FPSS	N 64
# VMAGI		INERTIAL VELOCITY MAGNITUDE		128 M/CENTISEC	N 64, N 68
# THETAH	DESIRED RANGE ANGLE NM			1 REVOLUTION	N 64, N 67
# LAT		PRESENT LATITUDE			1 REVOLUTION	N 67
# LONG		PRESENT LONGITUDE			1 REVOLUTION	N 67
# RTOGO		RANGE ANGLE TO SPLASH FROM		1 REVOLUTION	N 63
# 		EMSALT FT ABOVE FISCHER RADIUS. (IN NM)	
# VIO		PREDICTED VELOCITY AT ALTITUDE		128 M/CENTISEC	N 63
#		EMSALT FT ABOVE FISCHER RADIUS.
# TTE		TIME OF FREE FALL TO ALT		B 28 CENTISEC	N 63
# 		EMSALT FT ABOVE FISCHER RADIUS.
# ROLLC		ROLL COMMAND				1 REVOLUTION	N 66, N 68, N 69
# LATANG	CROSS-RANGE ERROR (XRNGERR)		4 RADIANS	N 66
# DNRNGERR	DOWN RANGE ERROR			1 REVOLUTION	N 66
#		(PREDANG - THETAH IN NM)
# HDOT		ALTITUDE RATE				128 M/CENTISEC	N 68
# Q7		MINIMUM DRAG FOR UPCONTROL		805 FPSS	N 69
# VL		EXIT VELOCITY FOR UP-CONTROL		2 VSAT		N 69

## Page 843
# BODY ATTITUDE QUANTITIES  (CM/POSE)
# -----------------------------------
#
# VARIABLE	DESCRIPTION				MAXIMUM VALUE
# --------	-----------				------- -----
#  -
# -VREL		NEGATIVE VELOCITY REL TO ATMOS.		2 VSAT
# -
# OLDUYA	USED FOR UYA BELOW 1000 FPS		2
# -
# UXA/2		UNIT VECTOR TRIAD			2
# -
# UYA/2			BASED ON			2
# -
# UZA/2				THE TRAJECTORY.		2
# -
# UBX/2		UNIT VECTOR				2
# -
# UBY/2			BODY TRIAD			2
# -
# UBZ/2				FOR CM.			2