This paper addresses the computation of the required trajectory correction maneuvers (TCM) for a halo orbit space mission to compensate for the launch velocity errors introduced by inaccuracies of the launch vehicle.
Halo Orbit Mission Correction Maneuvers Using Optimal Control
01.01.2000
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Englisch
Optimal Approach to Halo Orbit Control
AIAA | 2003
|Halo Orbit Formulation for the ISEE-3 Mission
AIAA | 1980
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