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Simple computations for near-optimum ascent and abort maneuver targets and deorbit ignition time

Author
Mchenry, R. L.
Published
Jan 1, 1980.
Physical Description
1 electronic document
Online Version

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Unclassified, Unlimited, Publicly available.
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Summary
Closed-form solutions are presented for a two-burn orbit insertion, AOA, and ATO maneuver targets, and for time of ignition of a one-burn deorbit. Based on the assumption that the orbits involved deviate only to the first order about a reference circular orbit, these solutions are nearly fuel-minimum. They are expressed in terms of linear terminal velocity constraint shuttle guidance targets and, thus, are readily applicable to both ground and onboard software use. In addition to potential application to real-time targeting, the equations may be used as a mission design aid in preliminary definition of target loads and definition of abort mode boundaries.
Other Subject(s)
Collection
NASA Technical Reports Server (NTRS) Collection.
Note
Document ID: 19800006926.
Accession ID: 80N15185.
REPT-80-FM-3.
JSC-16318.
NASA-TM-80850.
Terms of Use and Reproduction
No Copyright.
View MARC record | catkey: 15723710