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Page 618

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http://www.ibiblio.org/apollo/ScansForConversion/Luminary099/0618.jpg

R0011 (L32) remove extra hyphen
R0014 (L37) remove word "TIME" not in scan
R0015 (L38) remove extra hyphen
R0021 (L46) (un)correct typo in scan: "FLIGHT" → "FLIGNT"
R0043 (L79) remove comma not in scan
Comment out empty lines within comment blocks, for consistency
This commit is contained in:
Nathan Scott 2020-10-19 17:11:22 +11:00
parent 91c2a8d8f9
commit 173e615208
1 changed files with 16 additions and 16 deletions
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32
Luminary099/P32-P35_P72-P75.agc
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@ -29,54 +29,54 @@
# Page 618
# COELLIPTIC SEQUENCE INITIATION (CSI) PROGRAMS (P32 AND P72)
#
# MOD NO -1 LOG SECTION -- P32-P35, P72-P75
# MOD NO -1 LOG SECTION - P32-P35, P72-P75
# MOD BY WHITE.P DATE 1JUNE67
#
# PURPOSE
# (1) TO CALCULATE PARAMETERS ASSOCIATED WITH THE TIME FOLLOWING
# CONCENTRIC FLIGHT PLAN MANEUVERS -- THE CO-ELLIPTIC SEQUENCE
#
# (1) TO CALCULATE PARAMETERS ASSOCIATED WITH THE FOLLOWING
# CONCENTRIC FLIGHT PLAN MANEUVERS - THE CO-ELLIPTIC SEQUENCE
# INITIATION (CSI) MANEUVER AND THE CONSTANT DELTA ALTITUDE
# (CDH) MANEUVER.
#
# (2) TO CALCULATE THESE PARAMETERS BASED UPON MANEUVER DATA
# APPROVED AND KEYED INTO THE DSKY BY THE ASTRONAUT.
#
# (3) TO DISPLAY TO THE ASTRONAUT AND THE GROUND DEPENDENT VARIABLES
# ASSOCIATED WITH THE CONCENTRIC FLIGHT PLAN MANEUVERS FOR
# ASSOCIATED WITH THE CONCENTRIC FLIGNT PLAN MANEUVERS FOR
# APPROVAL BY THE ASTRONAUT/GROUND.
#
# (4) TO STORE THE CSI TARGET PARAMETERS FOR USE BY THE DESIRED
# THRUSTING PROGRAM.
#
# ASSUMPTIONS
#
# (1) AT A SELECTED TPI TIME THE LINE OF SIGHT BETWEEN THE ACTIVE
# AND PASSIVE VEHICLES IS SELECTED TO BE A PRESCRIBED ANGLE (E)
# FROM THE HORIZONTAL PLANE DEFINED BY THE ACTIVE VEHICLE
# POSITION.
#
# (2) THE TIME BETWEEN CSI IGNITION AND CDH IGNITION MUST BE
# COMPUTED TO BE GREATER THAN 10 MINUTES FOR SUCCESSFUL
# COMPLETION OF THE PROGRAM.
#
# (3) THE TIME BETWEEN CDH IGNITION AND TPI IGNITION MUST BE
# COMPUTED TO BE GREATER THAN 10 MINUTES FOR SUCCESSFUL
# COMPLETION OF THE PROGRAM.
#
# (4) CDH DELTA V IS SELECTED TO MINIMIZE THE VARIATION OF THE
# ALTITUDE DIFFERENCE BETWEEN THE ORBITS.
#
# (5) CSI BURN IS DEFINED SUCH THAT THE IMPULSIVE DELTA V IS IN THE
# HORIZONTAL PLANE DEFINED BY THE ACTIVE VEHICLE POSITION AT CSI
# IGNITION.
#
# (6) THE PERICENTER ALTITUDE OF THE ORBIT FOLLOWING CSI AND CDH
# MUST BE GREATER THAN 35,000 FT (LUNAR ORBIT) OR 85 NM (EARTH
# ORBIT) FOR SUCCESSFUL COMPLETION OF THIS PROGRAM.
#
# (7) THE CSI AND CDH MANEUVERS ARE ORIGINALLY ASSUMED TO BE
# PARALLEL TO THE PLANE OF THE CSM ORBIT. HOWEVER, CREW
# PARALLEL TO THE PLANE OF THE CSM ORBIT. HOWEVER CREW
# Page 619
# MODIFICATION OF DELTA V (LV) COMPONENTS MAY RESULT IN AN
# OUT-OF-PLANE CSI MANEUVER