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Halo Orbit Mission Correction Maneuvers Using Optimal ControlThis 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.
Document ID
20060032714
Acquisition Source
Jet Propulsion Laboratory
Document Type
Reprint (Version printed in journal)
External Source(s)
Authors
Lo, M.
Serban, R.
Petzold, L.
Koon, W.
Ross, S.
Marsden, J.
Wilson, R.
Date Acquired
August 23, 2013
Publication Date
January 1, 2000
Publication Information
Publication: Automatica
Subject Category
Astrodynamics
Distribution Limits
Public
Copyright
Other
Keywords
Halo Orbit trajectory error correction optimal control

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