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Kalman filtering for spacecraft attitude estimationSeveral schemes in current use for sequential estimation of spacecraft attitude using Kalman filters are examined. These differ according to their treatment of the attitude error, namely: using the complete four-component quaternion; using a truncated quaternion in which one of the components has been eliminated; or using a quaternion referred to approximate body-fixed axes. These schemes are examined for the case of a spacecraft carrying line-of-sight attitude sensors and three-axis gyros whose measurements are corrupted by noise on both the drift rate and the drift-rate ramp. The analysis of the covariance is carried out in detail. The historical development of Kalman filtering of attitude is reviewed.
Document ID
19820034231
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Lefferts, E. J.
(NASA Goddard Space Flight Center Attitude Dynamics Section, Greenbelt, MD, United States)
Markley, F. L.
(U.S. Navy, Naval Research Laboratory, Washington DC, United States)
Shuster, M. D.
(Business and Technological Systems, Inc. Seabrook, MD, United States)
Date Acquired
August 10, 2013
Publication Date
January 1, 1982
Subject Category
Spacecraft Design, Testing And Performance
Report/Patent Number
AIAA PAPER 82-0070
Meeting Information
Meeting: Aerospace Sciences Meeting
Location: Orlando, FL
Start Date: January 11, 1982
End Date: January 14, 1982
Sponsors: American Institute of Aeronautics and Astronautics
Accession Number
82A17766
Distribution Limits
Public
Copyright
Other

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