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Predicted torque equilibrium attitude utilization for Space Station attitude controlAn approximate knowledge of the torque equilibrium attitude (TEA) is shown to improve the performance of a control moment gyroscope (CMG) momentum management/attitude control law for Space Station Freedom. The linearized equations of motion are used in conjunction with a state transformation to obtain a control law which uses full state feedback and the predicted TEA to minimize both attitude excursions and CMG peak and secular momentum. The TEA can be computationally determined either by observing the steady state attitude of a 'controlled' spacecraft using arbitrary initial attitude, or by simulating a fixed attitude spacecraft flying in desired orbit subject to realistic environmental disturbance models.
Document ID
19900060525
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Kumar, Renjith R.
(Analytical Mechanics Associates, Inc. Hampton, VA, United States)
Heck, Michael L.
(Analytical Mechanics Associates, Inc. Hampton, VA, United States)
Robertson, Brent P.
(McDonnell Douglas Space Systems Co. Seabrook, MD, United States)
Date Acquired
August 14, 2013
Publication Date
January 1, 1990
Subject Category
Spacecraft Design, Testing And Performance
Report/Patent Number
AIAA PAPER 90-3318
Meeting Information
Meeting: AIAA Guidance, Navigation and Control Conference
Location: Portland, OR
Country: United States
Start Date: August 20, 1990
End Date: August 22, 1990
Accession Number
90A47580
Funding Number(s)
CONTRACT_GRANT: NAS1-18246
Distribution Limits
Public
Copyright
Other

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