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
2000-01-01
Miscellaneous
No indication
English
Optimal Approach to Halo Orbit Control
AIAA | 2003
|H2 Optimal Halo Orbit Guidance
Online Contents | 1993
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