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Optimal control of quaternion propagation errors in spacecraft navigationOptimal control techniques are used to drive the numerical error (truncation, roundoff, commutation) in computing the quaternion vector to zero. The normalization of the quaternion is carried out by appropriate choice of a performance index, which can be optimized. The error equations are derived from Friedland's (1978) theoretical development, and a matrix Riccati equation results for the computation of the gain matrix. Simulation results show that a high precision of the order of 10 to the -12th can be obtained using this technique in meeting the q(T)q=1 constraint. The performance of the estimator in the presence of the feedback control that maintains the normalization, is studied.
Document ID
19860054312
Acquisition Source
Legacy CDMS
Document Type
Reprint (Version printed in journal)
Authors
Vathsal, S.
(NASA Goddard Space Flight Center Greenbelt, MD, United States)
Date Acquired
August 12, 2013
Publication Date
June 1, 1986
Publication Information
Publication: Journal of Guidance, Control, and Dynamics
Volume: 9
ISSN: 0731-5090
Subject Category
Spacecraft Design, Testing And Performance
Accession Number
86A39050
Distribution Limits
Public
Copyright
Other

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