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Minimum fuel spacecraft reorientationFuel optimal solutions for the reorientation of an inertially symmetric rigid spacecraft with independent 3-axes controls are investigated. All possible optimal control strategies are identified. These include bangbang solutions, finite order singular arcs and infinite order singular arcs. Higher order necessary conditions for optimality of finite order singular arcs are presented. Numerical examples of fuel optimal solutions with fixed maneuver time are presented involving all of the theoretically possible control logics.
Document ID
19930064454
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Seywald, H. (NASA Langley Research Center Hampton, VA, United States)
Kumar, R. R. (NASA Langley Research Center Hampton, VA, United States)
Deshpande, S. M. (NASA Langley Research Center Hampton, VA, United States)
Heck, M. L. (Analytical Mechanics Associates, Inc.; NASA, Langley Research Center Hampton, VA, United States)
Date Acquired
August 16, 2013
Publication Date
January 1, 1992
Publication Information
Publication: In: Spaceflight mechanics 1992; Proceedings of the 2nd AAS(AIAA Meeting, Colorado Springs, CO, Feb. 24-26, 1992. Pt. 1 (A93-48426 20-12)
Publisher: Univelt, Inc.
Subject Category
Spacecraft Design, Testing And Performance
Report/Patent Number
AAS PAPER 92-140
Accession Number
93A48451
Distribution Limits
Public
Copyright
Other

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IDRelationTitle19930064429Collected WorksSpaceflight mechanics 1992; Proceedings of the 2nd AAS/AIAA Meeting, Colorado Springs, CO, Feb. 24-26, 1992. Pts. 1 & 2
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