ryan/Apollo-11
1
0
Fork 0
Code Issues Pull Requests Actions Packages Projects Releases Wiki Activity

proof(luminary099): page 1160

Browse Source
This commit is contained in:
Taís Massaro 2021-10-29 16:59:03 +00:00 committed by GitHub
parent 2735bd52af
commit fd2c5ae56f
1 changed files with 19 additions and 17 deletions
Show Stats Download Patch File Download Diff File Expand all files Collapse all files

36
Luminary099/CONIC_SUBROUTINES.agc
View File

@ -58,45 +58,47 @@
# Page 1160
# PROGRAM DESCRIPTION - KEPLER SUBROUTINE DATE - 11 OCTOBER 1967
# MOD NO. -1 LOG SECTION - CONIC SUBROUTINES
# MOD NO. -1 LOG SECTION - CONIC SUBROUTINES
# MOD BY KRAUSE ASSEMBLY - COLOSSUS 103 AND SUNDANCE 222
# MOD NO. - 2 (AUGUST 1968) BY ROBERTSON: TO PERMIT BACKDATING BY MORE THAN ONE ORBITAL PERIOD.
# MOD NO. - 3 (DEC 1968) BY ROBERTSON: SUPPRESSION OF X-MODULO-ING
# MOD NO. - 4 (JAN 1969) BY ROBERTSON: CLEAR OVFIND AT KEPLER ENTRY
#
# MOD NO. - 3 (DEC 1968) BY ROBERTSON: SUPPRESSION OF X-MODULO-ING
#
# MOD NO. - 4 (JAN 1969) BY ROBERTSON: CLEAR OVFIND AT KEPLER ENTRY
#
# FUNCTIONAL DESCRIPTION -
# THIS SUBROUTINE, GIVEN AN INITIAL STATE VECTOR AND THE DESIRED TRANSFER TIME THROUGH WHICH THE STATE IS TO
# BE UPDATED ALONG A CONIC TRAJECTORY, COMPUTES THE NEW, UPDATED STATE VECTOR. THE TRAJECTORY MAY BE ANY CONIC
# SECTION - CIRCULAR, ELLIPTIC, PARABOLIC, HYPERPOLIC, OR RECTILINEAR WITH RESPECT TO THE EARTH OR THE MOON. THE
# SECTION - CIRCULAR, ELLIPTIC, PARABOLIC, HYPERBOLIC, OR RECTILINEAR WITH RESPECT TO THE EARTH OR THE MOON. THE
# USE OF THE SUBROUTINE CAN BE EXTENDED USING OTHER PRIMARY BODIES BY SIMPLE ADDITIONS TO THE MUTABLE WITHOUT
# INTRODUCING ANY CODING CHANGES, ACCEPTING THE INHERENT SCALE FACTOR CHANGES IN POSITION AND VELOCITY. AN ITERATION
# TECHNIQUE IS UTILIZED IN THE COMPUTATION.
#
# INTRODUCING ANY CODING CHANGES, ACCEPTING THE INHERENT SCALE FACTOR CHANGES IN POSITION AND VELOCITY. AN ITERA-
# TION TECHNIQUE IS UTILIZED IN THE COMPUTATION.
# IF A NEGATIVE TIME-OF-FLIGHT IS INPUT, THE PROGRAM WILL SOLVE FOR THE STATE WHICH WOULD BE PRODUCED BY
# EXTRAPOLATING THE POSITION BACKWARD IN TIME.
#
# IF THE ABSOLUTE VALUE OF THE DESIRED TRANSFER TIME EXCEEDS THE ORBITAL PERIOD, THE SUBROUTINE, THROUGH A
# MODULAR TECHNIQUE, WILL COMPUTE THE STATE CORRESPONDING TO THE DESIRED TIME (WHETHER POSITIVE OR NEGATIVE).
#
# THE RESTRICTIONS ARE -
# 1. (PREVIOUS RESTRICTION ON THE NEGATIVE DESIRED TRANSFER TIME IS NOW DELETED.)
# 2. THE PARAMETERS IN THE PROBLEM CANNOT EXCEED THEIR SCALING LIMITS AS SPECIFIED IN THE GSOP. IF
# ANY OF THESE LIMITS ARE EXCEEDED, THE RESULTING SOLUTION WILL BE MEANINGLESS.
# 2. THE PARAMETERS IN THE PROBLEM CANNOT EXCEED THEIR SCALING LIMITS AS SPECIFIED IN THE GSOP. IF
# ANY OF THESE LIMITS ARE EXCEEDED, THE RESULTING SOLUTION WILL BE MEANINGLESS.
#
# THE NUMBER OF ITERATIONS AND, THEREFORE, THE COMPUTATION SPEED IS DEPENDENT ON THE ACCURACY OF THE
# GUESS, XKFPNEW. THE AGC COMPUTATION TIME IS APPROXIMATELY .061 SECONDS FOR INITIALIZATION, .065 SECONDS FOR THE
# GUESS, XKEPNEW. THE AGC COMPUTATION TIME IS APPROXIMATELY .061 SECONDS FOR INITIALIZATION, .065 SECONDS FOR THE
# FINAL COMPUTATIONS, PLUS .083 SECONDS FOR EACH ITERATION.
#
#
# REFERENCES -
# R-479, MISSION PROGRAMMING DEFINITION MEMO NO. 10, LUNAR LANDING MISSION GSOP, SECTION 5.5, SGA
# MEMO 67-4.
# MEMO 67-4.
#
#
# INPUT - ERASABLE INITIALIZATION REQUIRED
# * SCALE FACTOR *
# VARIABLE *IN POWERS OF 2 * DESCRIPTION AND REMARKS
# -------- *-------------- * -----------------------
# RRECT * +29 FOR EARTH * DP INITIAL POSITION VECTOR IN METERS
# * +27 FOR MOON *
# * SCALE FACTOR *
# VARIABLE *IN POWERS OF 2* DESCRIPTION AND REMARKS
# -------- *--------------* -----------------------
# RRECT * +29 FOR EARTH* DP INITIAL POSITION VECTOR IN METERS
# * +27 FOR MOON *
# Page 1161
# VRECT * +7 FOR EARTH * DP INITIAL VELOCITY VECTOR IN METERS/CENTISECOND
# * +5 FOR MOON *