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A linear quadratic tracker for Control Moment Gyro based attitude control of the Space StationThe paper discusses a design for an attitude control system for the Space Station which produces fast response, with minimal overshoot and cross-coupling with the use of Control Moment Gyros (CMG). The rigid body equations of motion are linearized and discretized and a Linear Quadratic Regulator (LQR) design and analysis study is performed. The resulting design is then modified such that integral and differential terms are added to the state equations to enhance response characteristics. Methods for reduction of computation time through channelization are discussed as well as the reduction of initial torque requirements.
Document ID
19860055869
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Kaidy, J. T.
(Houston, University Clear Lake; Rockwell International Corp., Houston, TX, United States)
Date Acquired
August 12, 2013
Publication Date
January 1, 1986
Subject Category
Spacecraft Design, Testing And Performance
Report/Patent Number
AIAA PAPER 86-1194
Accession Number
86A40607
Funding Number(s)
CONTRACT_GRANT: NAS9-16715
CONTRACT_GRANT: NAS9-18000
Distribution Limits
Public
Copyright
Other

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