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Control of spinning flexible spacecraft by modal synthesisA procedure is presented for the active control of a spinning flexible spacecraft. Such a system exhibits gyroscopic effects. The design of the controller is based on modal decomposition of the gyroscopic system. This modal decoupling procedure leads to a control mechanism implemented in modular form, which represents a distinct computational advantage over the control of the coupled system. Design procedures are demonstrated for two types of control algorithms, linear and nonlinear. The first represents classical linear feedback approach and the second represents an application of on-off control, both types made feasible by the modal decomposition scheme.
Document ID
19770028032
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Meirovitch, L.
(Virginia Polytechnic Inst. and State Univ. Blacksburg, VA, United States)
Van Landingham, H. F.
(Virginia Polytechnic Inst. and State Univ. Blacksburg, VA, United States)
Oz, H.
(Virginia Polytechnic Institute and State University Blacksburg, Va., United States)
Date Acquired
August 8, 2013
Publication Date
October 1, 1976
Subject Category
Spacecraft Design, Testing And Performance
Report/Patent Number
IAF PAPER 76-022
Meeting Information
Meeting: International Astronautical Congress
Location: Anaheim, CA
Start Date: October 10, 1976
End Date: October 16, 1976
Sponsors: International Astronautical Federation
Accession Number
77A10884
Funding Number(s)
CONTRACT_GRANT: NSG-1109
Distribution Limits
Public
Copyright
Other

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