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Liapunov stability analysis of spinning flexible spacecraft.The attitude stability of a class of spinning flexible spacecraft in a force-free environment is analyzed. The spacecraft is modeled as a rigid core having attached to it a flexible appendage idealized as a collection of elastically interconnected particles. Liapunov stability theorems are employed with the Hamiltonian of the system, constrained through the angular momentum integral so as to admit complete damping, used as a testing function. The Hamiltonian is written in terms of modal coordinates as interpreted by the hybrid coordinate formulation, thus allowing truncation to a level amenable to literal stability analysis. Testing functions are constructed for a spacecraft with an arbitrary (discretized) appendage, and closed form stability criteria are generated for the first mode of a restricted appendage model lying in a plane which contains the center of mass and is orthogonal to the spin axis. The criteria are (except for idealized cases on the stability boundary line in the parameter space) both necessary and sufficient for stability for any spacecraft characterized by the planar appendage model, such as a spacecraft containing solar panels and/or radial booms.
Document ID
19730041576
Acquisition Source
Legacy CDMS
Document Type
Reprint (Version printed in journal)
Authors
Barbera, F. J.
(North American Rockwell Corp. Downey, Calif., United States)
Likins, P.
(California, University Los Angeles, Calif., United States)
Date Acquired
August 7, 2013
Publication Date
April 1, 1973
Publication Information
Publication: AIAA Journal
Volume: 11
Subject Category
Space Vehicles
Accession Number
73A26378
Funding Number(s)
CONTRACT_GRANT: NAS8-26214
Distribution Limits
Public
Copyright
Other

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