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Spacecraft Large Attitude Estimation Using a Navigation Sensor

Published online by Cambridge University Press:  01 December 2009

Ranjan Vepa
Ranjan Vepa*
Affiliation:
(Queen Mary, University of London)
*
(Email: [email protected])
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Abstract

In this paper we assume that we have measurements of a first difference of a typical satellite navigation carrier phase differential, which is a homogeneous quadratic function of the components of the attitude quaternion. We illustrate the determination of large or sustained attitudes using a dedicated unscented Kalman filter. The unscented Kalman filter structure was chosen for the dedicated filter because of its derivative free nature and other advantages. When a Gaussian distributed vector random variable is transformed to an equivalent quaternion it does not continue to be Gaussian distributed. For this reason, a new predictor-corrector form of the unscented Kalman filter is proposed to maintain the normalization of the unscented mean quaternion estimate in the presence of additive disturbances. The results from our realistic simulations indicate that the large attitude of a spacecraft can be estimated to within 0·1% accuracy over large time frames. The filter is particularly useful for autonomous operations of spacecraft as well as in other applications where the process model is bilinear or second order in the states.

Keywords

Unscented Kalman FilterSpacecraft attitude
Type
Research Article
Information
The Journal of Navigation , Volume 63 , Issue 1 , January 2010 , pp. 89 - 104
Copyright
Copyright © The Royal Institute of Navigation 2009

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