Time-Optimal Reorientation of a Spacecraft using a Direct Optimization Method Based on Inverse Dynamics
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Authors
Boyarko, George A.
Romano, Marcello
Yakimenko, Oleg A.
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Date of Issue
2010
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Abstract
This paper proposes a rapid attitude trajectory
generation method for satellite reorientation that satisfies the
spatial and temporal constraints imposed by the problem of
docking with a tumbling object. 12The problem is first
formulated and solved using known academic software
readily used for generating optimal guidance trajectories
off-line. Then, the problem is reformulated using a
polynomial structure that lends itself to satisfying special
mathematical constraints imposed by using a unit
quaternion for orientation description. The speed profile of
the maneuver is varied in order to arrive at a quasi-optimal
solution that is both feasible and exactly matches the
endpoint conditions specified in the problem. The reduction
in the number of varied parameters due to the predetermined
structure of the trajectory leads to a faster computational
speed as well as having a trajectory that satisfies the end
constraints at each iteration. The paper ends with a
discussion of solutions obtained for several cases.
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Article
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Mechanical and Aerospace Engineering (MAE)
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This publication is a work of the U.S. Government as defined in Title 17, United States Code, Section 101. Copyright protection is not available for this work in the United States.