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This paper aims to present the development and performance evaluation of an attitude and rate estimation algorithm using an extended Kalman filter structure based on a body-referenced representation of the state.
The algorithm requires only geomagnetic field data and can be used as a low-cost alternative or as a back-up estimator in the case of attitude sensor failures. The satellite rate is estimated as a part of the filter state and thus no gyroscope is necessary. The assessment of the algorithm performance is realized through a Monte Carlo simulation using a low-Earth orbit, nadir-pointing satellite.
Given some attitude and rate error requirements, the range of admissible initial errors on the filter state and the effect of un-modelled disturbance torque are determined, along with the achievable attitude and rate accuracies.
Because the simulation set-up is clearly stated, the results of this evaluation can be used as a benchmark for other estimation algorithms.
The necessary assumptions and approximations used to derive the filter equations are explicitly pointed out for the benefit of the readers. Well-defined filter initial conditions are used in an extensive series of tests resulting into a unique set of findings.
Evaluation of a spacecraft attitude and rate estimation algorithm
Aircraft Engineering and Aerospace Technology ; 82 , 3 ; 184-193
2010-05-18
10 pages
Aufsatz (Zeitschrift)
Elektronische Ressource
Englisch
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