Source Code
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These source-code files are part of a reconstructed copy of Skylark 048, the
Block II Command Module (CM) Apollo Guidance Computer (AGC) software for the
Skylab-2, Skylab-3, Skylab-4, and Apollo-Soyuz Test Project missions.
They have been created via disassembly of binary dumps of the original core rope
memory modules actually flown on Skylab-2, part numbers 2010802-541, 2010802-551,
2010802-561, 2010802-571, 2010802-581, and 2010802-591. Access to these modules
was provided by the New Mexico Museum of Space History, who we are much indebted to.
The source code for the Apollo 15, 16, and 17 software, Artemis 072, was used as
a starting point. Heavy use was made of TRW 4900.5-244, Programmed Guidance Equations
for Skylark Command Module Earth Orbital Program, dated 14 February 1972. This document
contains pseudocode of essentially all of Skylark, using original program labels which
have been copied for this source reconstruction.
Since only binary dumps (rather than listings) of Skylark are available as source material,
all comments and labels are approximate.
They have been taken from the Programmed Guidance Equations or other AGC programs where
possible, or, in some places, written from scratch to match what we believe would have
been in the original listing.
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035395,000002: ## Copyright: Public domain.
035396,000003: ## Filename: ENTRY_LEXICON.agc
035397,000004: ## Purpose: A section of Skylark revision 048.
035398,000005: ## It is part of the source code for the Apollo Guidance Computer (AGC)
035399,000006: ## for Skylab-2, Skylab-3, Skylab-4, and ASTP. No original listings of
035400,000007: ## this software are available; instead, this file was created via
035401,000008: ## disassembly of dumps of the core rope modules actually flown on
035402,000009: ## Skylab-2. Access to these modules was provided by the New Mexico
035403,000010: ## Museum of Space History.
035404,000011: ## Assembler: yaYUL
035405,000012: ## Contact: Ron Burkey <info@sandroid.org>.
035406,000013: ## Website: www.ibiblio.org/apollo/index.html
035407,000014: ## Mod history: 2023-09-04 MAS Created from Artemis 072.
035408,000015:
035409,000016:
035410,000017: # VARIABLE DESCRIPTION MAXIMUM VALUE * COMPUTER NAME
035411,000018: # -------- ----------- ------- ----- -------- ----
035412,000019: # -
035413,000020: # URT0 INITIAL TARGET VECTOR 2 (UNIT VECTOR) = RTINIT
035414,000021: # -
035415,000022: # UZ UNIT VECTOR NORTH 1 = UNITW
035416,000023: # -
035417,000024: # V VELOCITY VECTOR 2 VSAT = VEL
035418,000025: # -
035419,000026: # R POSITION VECTOR 2 EXP 29 METERS = RN
035420,000027: # -
035421,000028: # VI INERTIAL VELOCITY 128 M/CENTISEC = VN
035422,000029: # -
035423,000030: # RTE VECTOR EAST AT INITIAL TARGET 2 = RTEAST
035424,000031: # -
035425,000032: # UTR NORMAL TO RTE AND UZ 2 = RTNORM
035426,000033: # -
035427,000034: # URT TARGET VECTOR 2 = RT
035428,000035: # -
035429,000036: # UNI UNIT NORMAL TO TRAJECTORY PLANE 2
035430,000037: # -
035431,000038: # DELV INTEGRATED ACCEL. FROM PIPAS 5.85 16384 CM/S
035432,000039: # -
035433,000040: # G GRAVITY VECTOR 128 M/CENTISEC = GDT/2
035434,000041:
035435,000042: # A0 INITIAL DRAG FOR UPCONTRL 805 FPSS FPSS=FT/SEC/SEC
035436,000043: # AHOOKDV TERM IN GAMMAL CALC. = AHOOK DVL 8
035437,000044: # A1 DRAG VALUE IN FACTOR CALCULATION 805 FPSS
035438,000045: # ALP CONST FOR UPCONTRL 1
035439,000046: # ASKEP KEPLER RANGE 21600 NM NM = NAUTICAL MILE
035440,000047: # ASP1 FINAL PHASE RANGE 21600 NM
035441,000048: # ASPUP UP-RANGE 21600 NM
035442,000049: # ASP3 GAMMA CORRECTION 21600 NM
035443,000050: # ASPDWN RANGE DOWN TO PULL-UP 21600 NM
035444,000051: # ASP PREDICTED RANGE 21600 NM NOT STORED
035445,000052: # COSG COSINE(GAMMAL) 2 = COSG/2
035446,000053: # C/D0 RECIPROCAL DRAG, -4/D0 B-8 64/FPSS AGC ONLY
035447,000054: # D TOTAL ACCELERATION 805 FPSS
035448,000055: # D0 CONTROLLED CONSTANT D 805 FPSS
035449,000056: # DHOOK TERM IN GAMMAL COMPUTATION 805 FPSS
035450,000057: # DIFF THETNM-ASP (RANGE DIFFERENCE) 21600 NM
035451,000058: # DIFFOLD PREVIOUS VALUE OF DIFF 21600 NM
035452,000059: # DLEWD CHANGE IN LEWD 1
035453,000060: # DR REFERENCE DRAG FOR DOWNCONTROL 805 FPSS NOT STORED
035454,000061: # DREFR( ) REFERENCE DRAG (FINAL PHASE TABLE) 805 FPSS NOT SAVED
035455,000062: # DVL VS1-VL 2 VSAT
035456,000063: # E ECCENTRICITY 4 NOT STORED
035457,000064: # F1( ) DRANGE/D DRAG (FINAL PHASE TABLE) 2700/805 = FX +5
035458,000065: # F2( ) DRANGE/D RDOT (FINAL PHASE TABLE) 2700/2VS NM/FPS = FX +4 /8
035459,000066: # F3( ) DRANGE/D (L/D) (FINAL PHASE TABLE) 2700 NM = FX
035460,000067: # * MAXIMUM VALUE DENOTES UNSCALED
035461,000068: # VARIABLE VALUE WHEN SCALED
035462,000069: # FIGURE 7.0-2 COMPUTER VARIABLES VARIABLE HAS MAXIMUM VALUE OF ONE.
035463,000070:
035464,000071:
035465,000072: # VARIABLE DESCRIPTION MAXIMUM VALUE COMPUTER NAME
035466,000073: # -------- ----------- ------- ----- -------- ----
035467,000074:
035468,000075: # FACT1 CONST FOR UPCONTRL 2 VSAT
035469,000076: # FACT2 CONST FOR UPCONTRL 1/805 FPSS
035470,000077: # FACTOR USED IN UPCONTRL 1
035471,000078: # GAMMAL FLIGHT PATH ANGLE AT VL 1 RADIAN
035472,000079: # GAMMAL1 SIMPLE FORM OF GAMMAL 1 RADIAN
035473,000080: # HEADSUP INDICATOR FOR INITIAL ROLL 1
035474,000081: # KA DRAG TO LIFT UP IF DOWN 805 FPSS = KAT
035475,000082: # KLAT LATERAL SWITCH GAIN 1 (NOM = .0125)
035476,000083: # K2ROLL INDICATOR FOR ROLL SWITCH
035477,000084: # LAD MAX L/D (MIN ACTUAL VEHICLE L/D) 1
035478,000085: # LADPAD NOMINAL VEHICLE L/D, SP PAD LOAD 1 (NOM = 0.3)
035479,000086: # LATANG LATERAL RANGE 4 RADIANS
035480,000087: # LAT(SPL) GEODETIC LATITUDE OF TARGET 1 REVOLUTION
035481,000088: # LNG(SPL) LONGITUDE OF TARGET 1 REVOLUTION
035482,000089: # LEQ EXCESS C.F. OVER GRAV=(VSQ-1)GS 128.8 FPSS
035483,000090: # LEWD UPCONTROL REFERENCE L/D 1
035484,000091: # LOD FINAL PHASE L/D 1 (NOM = 0.18)
035485,000092: # LODPAD FINAL PHASE L/D, SP PAD LOAD 1
035486,000093: # L/D DESIRED LIFT TO DRAG RATIO 1
035487,000094: # (VERTICAL PLANE)
035488,000095: # L/D1 TEMP STORAGE FOR L/D IN LATERAL 1
035489,000096: # L/DCMINR LAD COS(15DEG) 1 (NOM = 0.2895)
035490,000097: # PREDANGL PREDICTED RANGE (FINAL PHASE) 2700 NM = PREDANG
035491,000098: # Q2 FINAL PHASE RANGE 21600 NM
035492,000099: # Q7 MINIMUM DRAG FOR UPCONTROL 805FPSS
035493,000100: # RDOT ALTITUDE RATE 2 VSAT
035494,000101: # RDOTREF REFERENCE RDOT FOR UPCONTROL 2 VSAT
035495,000102: # RDOTREF( ) REFERENCE RDOT (FINAL PHASE TABLE) 2 VSAT = FX +3 /8
035496,000103: # RDTR REFERENCE RDOT FOR DOWNCONT 2 VSAT NOT SAVED
035497,000104: # ROLLC ROLL COMMAND 1 REVOLUTION
035498,000105: # RTOGO( ) RANGE TO GO (FINAL PHASE TABLE) 2700 NM = FX +2
035499,000106: # SL SINE OF LATITUDE 1 NOT SAVED
035500,000107: # T TIME B 28 CENTISEC = PIPTIME-TIME/RTO
035501,000108: # THETA DESIRED RANGE (RADIANS) 2 PI RADIANS = THETAH
035502,000109: # THETNM DESIRED RANGE (NM) 21600 NM NON EXISTENT
035503,000110: # V VELOCITY MAGNITUDE 2 VSAT
035504,000111: # V1 INITIAL VELOCITY FOR UPCONTROL 2 VSAT
035505,000112: # VL EXIT VELOCITY FOR UPCONTROL 2 VSAT
035506,000113: # VMAGI INERTIAL VELOCITY MAGNITUDE,|VI| 128 M/CENTISEC
035507,000114: # VREF REFERENCE VELOCITY FOR UPCONTROL 2 VSAT
035508,000115: # VREF( ) REFERENCE V (FINAL PHASE TABLE) 2 VSAT NOT STORED
035509,000116: # VS1 VSAT OR V1, WHICHEVER IS SMALLER 2 VSAT
035510,000117: # 2 2
035511,000118: # VBARS VL /VSAT 4
035512,000119: # 2 2
035513,000120: # VSQ NORMALISED VEL. SQUARED = V /VSAT 4 = VSQUARE
035514,000121:
035515,000122: # WT EARTH RATE TIMES TIME 1 REVOLUTION NOT SAVED
035516,000123: # = WIE (DTEAROT)
035517,000124: # X INTERMEDIATE VARIABLE IN G-LIMITER 2 VSAT NOT SAVED
035518,000125: # Y LATERAL MISS LIMIT 4 RADIANS NOT SAVED
035519,000126:
035520,000127: # FIGURE 7.0-2A COMPUTER VARIABLES (CONTINUED)
035521,000128:
035522,000129: # EXTRA COMPUTER ERASABLE LOCATIONS NOT SHOWN ON FLOW CHARTS
035523,000130: # -----------------------------------------------------------
035524,000131:
035525,000132: # VARIABLE DESCRIPTION MAXIMUM VALUE
035526,000133: # -------- ----------- ------- -----
035527,000134:
035528,000135: # GOTOADDR ADDRESS SELECTED BY SEQUENCER
035529,000136: # XPIPBUF BUFFER TO STORE X PIPA COUNTS
035530,000137: # YPIPBUF BUFFER TO STORE Y PIPA COUNTS
035531,000138: # ZPIPBUF BUFFER TO STORE Z PIPA COUNTS
035532,000139: # PIPCTR COUNTS PASSES THRU PIPA READ ROUTINE
035533,000140: # JJ INDEX IN FINAL PHASE TABLE LOOK-UP
035534,000141: # MM INDEX IN FINAL PHASE TABLE LOOK-UP
035535,000142: # GRAD INTERPOLATION FACTOR IN FINAL PHASE
035536,000143: # FX DRANGE/D L/D = F3 2700 NM
035537,000144: # FX + 1 AREF 805 FPSS
035538,000145: # FX + 2 RTOGO 2700 NM
035539,000146: # FX + 3 RDOTREF VSAT/4
035540,000147: # FX + 4 DRANGE/D RDOT = F2 21600/2VS NM/FPS
035541,000148: # FX + 5 DRANGE/D DRAG = F1 2700/805 NM/FPSS
035542,000149: # TEM1B TEMPORARY LOCATION
035543,000150: # TIME/RTO TIME OF INITIAL TARGET RTINIT B 28 CENTISEC
035544,000151: # DTEAROT EST TIME BETWEEN RTINIT AND RT B 28 CENTISEC
035545,000152: # -
035546,000153: # UNITV UNIT V VECTOR 2
035547,000154: # -
035548,000155: # UNITR UNIT R VECTOR 2
035549,000156: # -
035550,000157: # -VREL NEGATIVE VELOCITY REL TO ATMOSP 2 VSAT
035551,000158:
035552,000159: # COMPUTER SWITCHES INITIAL STATE CM/FLAGS = STATE +6
035553,000160: # -------- -------- ------------- -------------------
035554,000161:
035555,000162: # ENTRYDSP DO ENTRY DISPLAY, IF SET NON-BRANCH (1) 92D, BIT13
035556,000163: # GONEPAST INDICATES OVERSHOOT OF TARGET BRANCH (1) 95D, BIT10
035557,000164: # RELVELSW RELATIVE VELOCITY SWITCH NON-BRANCH (0) 96D, BIT 9
035558,000165: # EGSW FINAL PHASE SWITCH NON-BRANCH (0) 97D, BIT 8
035559,000166: # NOSWITCH INHIBIT LATERAL SWITCH NON-BRANCH (0) 98D, BIT 7
035560,000167: # HIND INDICATES ITERATION IN HUNTEST NON-BRANCH (0) 99D, BIT 6
035561,000168: # INRLSW INDICATES INIT ROLL ATTITUDE SET NON-BRANCH (0) 100D, BIT 5
035562,000169: # LATSW INHIBIT DOWNLIFT SWITCH IF NOT SET BRANCH (1) 101D, BIT 4
035563,000170: # .05GSW INDICATES DRAG EXCEEDS .05 GS NON-BRANCH (0) 102D, BIT 3
035564,000171:
035565,000172: # GONEBY INDICATES GONE PAST TARGET (SET) SELF-INITIALIZING 112D, BIT 8 IN STATE +7
035566,000173:
035567,000174: # FIGURE 7.0-2B COMPUTER VARIABLES (CONTINUED)
035568,000175:
035569,000176: # BODY ATTITUDE QUANTITIES (CM/POSE)
035570,000177: # -----------------------------------
035571,000178:
035572,000179: # VARIABLE DECRIPTION MAXIMUM VALUE
035573,000180: # -------- ---------- ------- -----
035574,000181: # -
035575,000182: # -VREL NEGATIVE VELOCITY REL TO ATMOS. 2 VSAT
035576,000183: # - -
035577,000184: # OLDUYA USED FOR UYA BELOW 1000 FPS 2
035578,000185:
035579,000186: # -
035580,000187: # UXA/2 UNIT VECTOR TRIAD 2
035581,000188: # -
035582,000189: # UYA/2 BASED ON 2
035583,000190: # -
035584,000191: # UZA/2 THE TRAJECTORY. 2
035585,000192:
035586,000193: # -
035587,000194: # UBX/2 UNIT VECTOR 2
035588,000195: # -
035589,000196: # UBY/2 BODY TRIAD 2
035590,000197: # -
035591,000198: # UBZ/2 FOR CM. 2
035592,000199:
035593,000200: # FIGURE 7.0-2C COMPUTER VARIABLES (CONTINUED)
035594,000201:
035595,000202: # DISPLAY QUANTITIES (FOR USAGE,SEE SECTION 4: P 61 THROUGH P 67)
035596,000203: # ------------------
035597,000204:
035598,000205: # THIS TABLE PROVIDES THE READER WITH DISPLAY QUANTITY INFORMATION. THE VARIABLE NAMES REFLECT
035599,000206: # SECTION 5 USAGE. EXCEPTING IMBEDDED BLANKS, THE SECTION 4 NAMES ARE PARENTHESIZED,IF DIFFERENT.
035600,000207: # SIGN CONVENTIONS ARE FOUND IN SECTION 4. IF THE DISPLAY VARIABLE NAME DIFFERS FROM SECTION 5 USAGE,
035601,000208: # SAY BECAUSE OF SCALE FACTOR, THE ALTERNATE SECTION 5 NAME IS ENCLOSED IN ANGULAR BRACKETS: < >.
035602,000209: # DISPLAY QUANTITY INFORMATION APPEARING ELSEWHERE IN SECTION 5 OTHER THAN IN 5 7 MAY BE FOUND THUS:
035603,000210: # N 60 & N 63 (ALL) FIGURE 6.10-4 IN 5.6.10.3
035604,000211: # N 22 (ALL) FIGURE 6.10-11 IN 5.6.10.6
035605,000212: # N67 (LAT, LONG) FIGURE 5.3-1 IN 5.5.3
035606,000213:
035607,000214: # VARIABLE DESCRIPTION MAXIMUM VALUE DISPLAY NOUNS
035608,000215: # -------- ----------- ------- ----- ------- -----
035609,000216:
035610,000217: # GMAX PREDICTED MAXIMUM ENTRY ACCEL 163.84 GS N 60
035611,000218: # VPRED PREDICTED VELOCITY AT ALTITUDE 128 M/CENTISEC N 60
035612,000219: # 400K FT ABOVE FISCHER RADIUS.
035613,000220: # GAMMAEI PREDICTED GAMMA AT ALTITUDE 1 REVOLUTION N 60
035614,000221: # 400K FT ABOVE FISCHER RADIUS.
035615,000222: # RTGO RANGE ANGLE TO SPLASH (RTOGO) 1 REVOLUTION N 63
035616,000223: # FROM EMSALT FT ABOVE FISCHER
035617,000224: # RADIUS. (IN NM)
035618,000225: # VIO PREDICTED VELOCITY AT ALTITUDE 128 M/CENTISEC N 63
035619,000226: # EMSALT FT ABOVE FISCHER RADIUS.
035620,000227: # TTE TIME OF FREE FALL (TFE) TO B 28 CENTISEC N 63
035621,000228: # ALTITUDE EMSALT FT ABOVE FISCHER
035622,000229: # RADIUS.
035623,000230: # OGA OUTER GIMBAL ANGLE (OG ROLL) 1 REVOLUTION N 22
035624,000231: # IGA INNER GIMBAL ANGLE (IG PITCH) 1 REVOLUTION N 22
035625,000232: # MGA MIDDLE GIMBAL ANGLE (MG YAW) 1 REVOLUTION N 22
035626,000233: # ALL ABOVE ANGLES FOR HYPERSONIC TRIM
035627,000234: # D DRAG ACCELERATION (G) 805 FPSS N 64, N 74
035628,000235: # VMAGI INERTIAL VELOCITY MAGNITUDE (VI) 128 M/CENTISEC N 64, N 68, N 74
035629,000236: # ROLLC ROLL COMMAND (BETA) 1 REVOLUTION N 66, N 68, N 69, N 74
035630,000237: # XRNGERR CROSS-RANGE ERROR <LATANG IN NM> 1 REVOLUTION N 66
035631,000238: # DNRNGERR DOWN RANGE ERROR ** 1 REVOLUTION N 66
035632,000239: # <PREDANG - THETAH IN NM>
035633,000240: # ** <DNRNGERR DISPLAYS 9999.9 IF GONEPAST =1 IN P 67>
035634,000241: # HDOT ALTITUDE RATE <RDOT> 128 M/CENTISEC N 68
035635,000242: # Q7 EXIT DRAG LEVEL (DL) 805 FPSS N 69
035636,000243: # VL EXIT VELOCITY FOR UP-CONTROL 2 VSAT N 69
035637,000244: # RTOGO DESIRED RANGE ANGLE <THETAH> 1 REVOLUTION N 67, N 64
035638,000245: # <-THETAH IF GONEBY =0, THETAH IF GONEBY =1>
035639,000246: # LAT GEODETIC LATITUDE OF VEHICLE 1 REVOLUTION N 67
035640,000247: # LONG LONGITUDE OF VEHICLE 1 REVOLUTION N 67
035641,000248:
035642,000249: # THE FOLLOWING IS A DATA INPUT NOUN (REFER TO SECTION 4,P 61 & P 62)
035643,000250: # HEADSUP INDICATOR FOR INITIAL ROLL 1 REVOLUTION N 61
035644,000251: # LAT(SPL) GEODETIC LATITUDE OF TARGET 1 REVOLUTION N 61
035645,000252: # (IMPACT LAT)
035646,000253: # LNG(SPL) LONGITUDE OF TARGET (IMPACT LONG) 1 REVOLUTION N 61
035647,000254:
035648,000255: # FIGURE 7.0-2D COMPUTER VARIABLES (CONTINUED)
035649,000256:
035650,000257:
035651,000258: # CONSTANTS AND GAINS VALUE
035652,000259: # ------------------- -----
035653,000260:
035654,000261: # C1 FACTOR IN ALP COMPUTATION 1.25
035655,000262: # C16 CONSTD GAIN ON DRAG 0.01
035656,000263: # C17 CONSTD GAIN ON RDOT 0.002
035657,000264: # C18 BIAS VEL. FOR FINAL PHASE START 500 FPS
035658,000265: # C20 MAX DRAG FOR DOWN-LIFT 210 FPSS
035659,000266: # C21 DRAG FOR NO LATERAL SWITCH 140 FPSS
035660,000267: # CHOOK FACTOR IN AHOOK COMPUTATION 0.25
035661,000268: # CH1 FACTOR IN GAMMAL COMPUTATION 1.0
035662,000269: # COS15 COS( 15 DEG) 0.965
035663,000270: # DLEWD0 INITIAL VARIATION IN LEWD -0.05
035664,000271: # DT COMPUTATION CYCLE TIME INTERVAL 2 SEC.
035665,000272: # GMAX MAXIMUM ACCELERATION 257.6 FPSS (8 G-S)
035666,000273: # KA1 FACTOR IN KA CALC 1.3 GS
035667,000274: # KA2 FACTOR IN KA CALC 0.2 GS
035668,000275: # KA3 FACTOR IN D0 CALC 90 FPSS
035669,000276: # KA4 FACTOR IN D0 CALC 40 FPSS
035670,000277: # KB1 OPTIMIZED UPCONTROL GAIN 2.5
035671,000278: # KB2 OPTIMIZED UPCONTROL GAIN 0.0025
035672,000279: # KDMIN INCREMENT ON Q7F TO DETECT END OF KEPLER PHASE 0.5 FPSS
035673,000280: # KTETA TIME OF FLIGHT CONSTANT 1000
035674,000281: # KLAT1 FACTOR IN KLAT CALC 1/24
035675,000282: # K44 GAIN USED IN INITIAL ROLL SECTION 19749550 FPS
035676,000283: # LATBIAS LATERAL SWITCH BIAS TERM 0.41252961 NM
035677,000284: # LEWD1 NOMINAL UPCONTROL L/D 0.15
035678,000285: # POINT1 FACTOR TO REDUCE UPCONTROL GAIN 0.1
035679,000286: # Q3 FINAL PHASE DRANGE/D V 0.07 NM/FPS
035680,000287: # Q5 FINAL PHASE DRANGE/ D GAMMA 7050 NM/RAD
035681,000288: # Q6 FINAL PHASE INITIAL FLIGHT PATH ANGLE 0.0349 RAD
035682,000289: # Q7F MIN DRAG FOR UPCONTROL 6 FPSS
035683,000290: # Q7MIN MIN VALUE FOR Q7 IN FACTOR CALCULATION 805 FPSS (DISABLE FACTOR)
035684,000291: # Q19 FACTOR IN GAMMAL1 CALCULATION 0.5
035685,000292: # Q21 FACTOR IN Q2 CALCULATION. 3500 NM
035686,000293: # Q22 FACTOR IN Q2 CALCULATION. -1992 NM
035687,000294: # VFINAL1 VELOCITY TO START FINAL PHASE ON INITIAL ENTRY 27000 FPS
035688,000295: # VFINAL FACTOR IN INITIAL UP-DOWN CALC 26600 FPS
035689,000296: # VLMIN MINIMUM VL 18000 FPS
035690,000297: # VMIN VELOCITY TO SWITCH TO RELATIVE VEL VSAT/2
035691,000298: # VRCONTRL RDOT TO START INTO HUNTEST 700 FPS
035692,000299: # VRCONT = COMPUTER NAME
035693,000300: # 25NM TOLERANCE TO STOP RANGE ITERATION 25 NM
035694,000301: # VQUIT VELOCITY TO STOP STEERING 1000 FPS
035695,000302:
035696,000303: # CONVERSION FACTORS AND SCALING CONSTANTS
035697,000304: # ---------- ------- --- ------- ---------
035698,000305:
035699,000306: # ATK ANGLE IN RAD TO NM 3437.7468 NM/RAD
035700,000307: # GS NOMINAL G VALUE FOR SCALING 32.2 FPSS
035701,000308: # HS ATMOSPHERE SCALE HEIGHT 28500 FT
035702,000309: # J GRAVITY HARMONIC COEFFICIENT 0.00162346
035703,000310: # KWE EQUATORIAL EARTH RATE 1546.70168 FPS
035704,000311: # MUE EARTH GRAVITATIONAL CONSTANT 3.986032233 E 14 CUBIC M/ SEC SEC
035705,000312: # RE EARTH RADIUS 21202900 FT
035706,000313: # REQ EARTH EQUATORIAL RADIUS 20925738.2 FT
035707,000314: # VSAT SATELLITE VELOCITY AT RE 25766.1973 FPS
035708,000315: # WIE EARTH RATE 0.0000729211505 RAD/SEC
035709,000316:
035710,000317: # FIGURE 7.0-3 CONSTANTS, GAINS AND CONVERSION FACTORS
End of include-file ENTRY_LEXICON.agc. Parent file is MAIN.agc