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Model reference adaptive attitude control of spacecraft using reaction wheelsA nonlinear model reference adaptive control law for large angle rotational maneuvers of spacecraft using reaction wheels in the presence of uncertainty is presented. The derivation of control law does not require any information on the values of the system parameters and the disturbance torques acting on the spacecraft. The controller includes a dynamic system in the feedback path. The control law is a nonlinear function of the attitude error, the rate of the attitude error, and the compensator state. Simulation results are prsented to show that large angle rotational maneuvers can be performed in spite of the uncertainty in the system.
Document ID
19880027802
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Singh, Sahjendra N.
(Vigyan Research Associates, Inc. Hampton, VA, United States)
Date Acquired
August 13, 2013
Publication Date
January 1, 1986
Subject Category
Spacecraft Design, Testing And Performance
Meeting Information
Meeting: IEEE Conference on Decision and Control
Location: Athens
Country: Greece
Start Date: December 10, 1986
End Date: December 12, 1986
Accession Number
88A15029
Funding Number(s)
CONTRACT_GRANT: NAS1-17919
Distribution Limits
Public
Copyright
Other

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