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The stability of motion satellites with long flexible appendagesThe dynamics of a gravity-gradient stabilized flexible satellite in the neighborhood of a deformed equilibrium configuration are investigated. First the equilibrium configuration is determined by solving a set of nonlinear differential equations. Then stability of motion about the deformed equilibrium is tested by means of the Liapunov direct method and the natural frequencies of oscillation of the complete structure calculated. The analysis is applicable to the RAE/B satellite.
Document ID
19740014384
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Meirovitch, L. (Virginia Polytechnic Inst. and State Univ. Blacksburg, VA, United States)
Date Acquired
September 3, 2013
Publication Date
March 1, 1974
Subject Category
Space Vehicles
Report/Patent Number
NASA-CR-138153
Report Number: NASA-CR-138153
Accession Number
74N22497
Funding Number(s)
CONTRACT_GRANT: NGR-47-004-098
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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