mirrors
/
Apollo-11
mirror of https://github.com/chrislgarry/Apollo-11.git
1
0
Fork 0
Code Issues Packages Projects Releases Wiki Activity

Proof AUTOMATIC_MANEUVERS (#194) (#335) 

* Proof FIXED_FIXED_CONSTANT_POOL (#207)

* Proof AUTOMATIC_MANEUVERS (#194)
pull/342/head
Glenn Dwiyatcita 2018-05-25 21:30:28 +02:00 committed by James Harris
parent ffcfaf5d51
commit eaec0f796b
1 changed files with 19 additions and 14 deletions
Show Stats Download Patch File Download Diff File Expand all files Collapse all files

33
Comanche055/AUTOMATIC_MANEUVERS.agc
View File

@ -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 S/C INTO THE
# COMPUTE THE CHANGE IN RATE CORRESPONDING TO THE ATTITUDE ERROR NECESSARY TO DRIVE THE 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