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Optimal Variable-Structure Control Tracking of Spacecraft ManeuversAn optimal control approach using variable-structure (sliding-mode) tracking for large angle spacecraft maneuvers is presented. The approach expands upon a previously derived regulation result using a quaternion parameterization for the kinematic equations of motion. This parameterization is used since it is free of singularities. The main contribution of this paper is the utilization of a simple term in the control law that produces a maneuver to the reference attitude trajectory in the shortest distance. Also, a multiplicative error quaternion between the desired and actual attitude is used to derive the control law. Sliding-mode switching surfaces are derived using an optimal-control analysis. Control laws are given using either external torque commands or reaction wheel commands. Global asymptotic stability is shown for both cases using a Lyapunov analysis. Simulation results are shown which use the new control strategy to stabilize the motion of the Microwave Anisotropy Probe spacecraft.
Document ID
19990064175
Document Type
Conference Paper
Authors
John L. Crassidis
(Texas A&M University System College Station, Texas, United States)
Srinivas R. Vadali
(Texas A&M University System College Station, Texas, United States)
F. Landis Markley
(Goddard Space Flight Center Greenbelt, Maryland, United States)
Date Acquired
August 19, 2013
Publication Date
May 1, 1999
Publication Information
Publication: 1999 Flight Mechanics Symposium
Publisher: National Aeronautics and Space Administration
Subject Category
Cybernetics
Meeting Information
Meeting: 1999 Flight Mechanics Symposium
Location: Greenbelt, MD
Country: US
Start Date: May 18, 1999
End Date: May 20, 1999
Sponsors: National Aeronautics and Space Administration
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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