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Halo orbit mission correction maneuvers using optimal control

Serban, Radu and Koon, Wang S. and Lo, Martin W. and Marsden, Jerrold E. and Petzold, Linda R. and Ross, Shane D. and Wilson, Roby S. (2002) Halo orbit mission correction maneuvers using optimal control. Automatica, 38 (4). pp. 571-583. ISSN 0005-1098. http://resolver.caltech.edu/CaltechAUTHORS:20100914-095842464

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Abstract

This paper addresses the computation of the required trajectory correction maneuvers for a halo orbit space mission to compensate for the launch velocity errors introduced by inaccuracies of the launch vehicle. By combining dynamical systems theory with optimal control techniques, we are able to provide a compelling portrait of the complex landscape of the trajectory design space. This approach enables automation of the analysis to perform parametric studies that simply were not available to mission designers a few years ago, such as how the magnitude of the errors and the timing of the first trajectory correction maneuver affects the correction ΔV. The impetus for combining dynamical systems theory and optimal control in this problem arises from design issues for the Genesis Discovery Mission being developed for NASA by the Jet Propulsion Laboratory.


Item Type:Article
Related URLs:
URLURL TypeDescription
http://dx.doi.org/10.1016/S0005-1098(01)00279-5 DOIUNSPECIFIED
http://www.cds.caltech.edu/~marsden/bib/2002/04-SeKoLoMaPeRoWi2002/SeKoLoMaPeRoWi2002.pdfAuthorUNSPECIFIED
Additional Information:© 2002 Elsevier. Received 27 April 2000; received in revised form 18 January 2001; accepted 27 June 2001. This work was carried out at the Computational Science and Engineering Group at the University of California, Santa Barbara, the Jet Propulsion Laboratory and the California Institute of Technology. The work was partially supported by the Caltech President’s fund, the NASA Advanced Concepts Research Program, The Genesis Project, NSF grant KDI/ATM-9873133 and AFOSR Microsat contract F49620-99-1-0190.
Funders:
Funding AgencyGrant Number
Caltech President’s fundUNSPECIFIED
NASA Advanced Concepts Research ProgramUNSPECIFIED
Genesis ProjectUNSPECIFIED
NSFKDI/ATM-9873133
Air Force Office of Scientific Research (AFOSR) Microsat F49620-99-1-0190
Subject Keywords:Dynamical systems; Optimal control; Halo orbit transfer; Invariant manifolds; Three-body problem; Space mission design
Record Number:CaltechAUTHORS:20100914-095842464
Persistent URL:http://resolver.caltech.edu/CaltechAUTHORS:20100914-095842464
Usage Policy:No commercial reproduction, distribution, display or performance rights in this work are provided.
ID Code:19937
Collection:CaltechAUTHORS
Deposited By: Ruth Sustaita
Deposited On:15 Sep 2010 17:26
Last Modified:26 Dec 2012 12:25

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