NASA NTRS · 20060032714
Halo Orbit Mission Correction Maneuvers Using Optimal Control
Abstract
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.
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Lo, M., Serban, R., Petzold, L., Koon, W., Ross, S., Marsden, J., Wilson, R.. 2000-01-01. Halo Orbit Mission Correction Maneuvers Using Optimal Control. https://ntrs.nasa.gov/citations/20060032714
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