Rigid Body Rate Inference from Attitude Variation

THIS Note deals with the extraction of the angular velocity in a gyroless spacecraft (SC) for which the attitude is represented by ;a quaternion that is obtained as a measurement of autonomous star trackers (AST) [1]. When the attitude is known, one can differentiate it and use the kinematics equati...

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Bibliographic Details
Published in:Journal of guidance, control, and dynamics control, and dynamics, 2007-01, Vol.30 (1), p.275-281
Main Authors: Bar-Itzhack, Itzhack Y, Harman, Richard R, Thienel, Julie K
Format: Article
Language:English
Subjects:
Accuracy
Aerospace engineering
Algorithms
Exact sciences and technology
Fundamental areas of phenomenology (including applications)
Investigations
Kalman filters
Kinematics
Noise
Physics
Rigid structures
Solid dynamics (ballistics, collision, multibody system, stabilization...)
Solid mechanics
Velocity
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Summary:THIS Note deals with the extraction of the angular velocity in a gyroless spacecraft (SC) for which the attitude is represented by ;a quaternion that is obtained as a measurement of autonomous star trackers (AST) [1]. When the attitude is known, one can differentiate it and use the kinematics equation that connects the derivative of the attitude with the satellite angular rate to compute the latter [2,3]. However, because the attitude is obtained from sensor measurements, it introduces considerable noise. Another approach employs a Kalman filter (KF) using the SC rotational kinematics equation [4,5]. However, the use of a KF requires the computation of a covariance matrix. Not only is this process cumbersome, sometimes it may also pose an accuracy problem. This accuracy problem led to the use of the more computationally intensive covariance measurement-update
ISSN:0731-5090
1533-3884
DOI:10.2514/1.23955