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Optimal open-loop and feedback control using single gimbal control moment gyroscopesMethods for control of spacecraft maneuvers through the use of single gimbal control moment gyroscopes are developed. The development employs an integrated model of the spacecraft dynamics with the control moment gyroscope dynamics. Smooth and continuous open-loop control profiles are obtained which minimize a weighted function of maneuver time, magnitude of control effort, and proximity to singular gimbal configurations. Closed-loop state feedback control laws are derived by invoking Lyapunov stability theory. The schemes are presented for implementing the commanded state feedback: gimbal rate control and gimbal acceleration control. The appropriate handling of singular gimbal configurations is also discussed.
Document ID
19950049760
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Hoelscher, Brian R.
(Texas A&M Univ. College Station, TX, US, United States)
Vadali, Srinvas R.
(Texas A&M Univ. College Station, TX, US, United States)
Date Acquired
August 16, 2013
Publication Date
January 1, 1993
Publication Information
Publication: In: Spaceflight mechanics, 1993; AAS(AIAA Spaceflight Mechanics Meeting, 3rd, Pasadena, CA, Feb. 22-24, 1993, Parts 1 & 2 . A95-81344
Publisher: American Astronautical Society (Advances in the Astronautical Sciences, Vol. 82, Pts. 1 & 2)
ISSN: 0065-3438
Subject Category
Spacecraft Design, Testing And Performance
Accession Number
95A81359
Funding Number(s)
CONTRACT_GRANT: NAS1-19373
Distribution Limits
Public
Copyright
Other

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