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An application of modern control theory to an elastic spacecraftResults are presented to illustrate the application of established procedures of linear, quadratic, Gaussian optimal estimation and control to a spacecraft with dynamically significant elastic appendages. Interpretations are provided in both time domain and frequency domain, and conclusions are drawn for a wide class of problems of flexible spacecraft attitude control.
Document ID
19760021229
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Larson, V. (Jet Propulsion Lab., California Inst. of Tech. Pasadena, CA, United States)
Likins, P. W. (Univ. of Calif. Los Angeles, United States)
Date Acquired
August 8, 2013
Publication Date
January 1, 1976
Publication Information
Publication: ESA Dyn. and Control of Non-rigid Space Vehicles
Subject Category
Spacecraft Design, Testing And Performance
Accession Number
76N28317
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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