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Adaptive spacecraft attitude control utilizing eigenaxis rotationsConventional and adaptive attitude control of spacecraft which use control moment gyros (CMG's) as torque sources are discussed. Control laws predicated on the assumption of a linear system are used since the spacecraft equations of motion are formulated in an 'eigenaxis system' so that they are essentially linear during 'slow' maneuvers even if large angles are involved. The overall control schemes are 'optimal' in several senses. Eigenaxis rotations and a weighted pseudo-inverse CMG steering law are used and, in the adaptive case, a Model Reference Adaptive System (MRAS) controller based on Liapunov's Second Method is adopted. To substantiate the theory, digital simulation results obtained using physical parameters of a Large Space Telescope type spacecraft are presented. These results indicate that an adaptive control law is often desirable.
Document ID
19750034277
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Cochran, J. E., Jr.
Colburn, B. K.
(Auburn University Auburn, Ala., United States)
Speakman, N. O.
(USAF Eglin AFB, Fla., United States)
Date Acquired
August 8, 2013
Publication Date
January 1, 1975
Subject Category
Spacecraft Design, Testing And Performance
Report/Patent Number
AIAA PAPER 75-158
Meeting Information
Meeting: American Institute of Aeronautics and Astronautics, Aerospace Sciences Meeting
Location: Pasadena, CA
Start Date: January 20, 1975
End Date: January 22, 1975
Sponsors: American Institute of Aeronautics and Astronautics
Accession Number
75A18349
Distribution Limits
Public
Copyright
Other

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