Filipski M.N., Varatharajoo R.
Department of Aerospace Engineering, Universiti Putra Malaysia, Serdang, Malaysia
Abstract:
Purpose - 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. Design/methodology/approach - 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. Findings - 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. Practical implications - Because the simulation set-up is clearly stated, the results of this evaluation can be used as a benchmark for other estimation algorithms. Originality/value - 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. © Emerald Group Publishing Limited.
Author Keywords:
Estimation; Magnetic fields; Monte Carlo simulation; Spacecraft
Year:
2010
Source title:
Aircraft Engineering and Aerospace Technology
Volume:
82
Issue:
3
Page :
184-193
Link:
Scorpus Link
Document Type:
Article
Source:
Scopus
Authors with affiliations:
-
Filipski, M.N., Department of Aerospace Engineering, Universiti Putra Malaysia, Serdang, Malaysia
-
Varatharajoo, R., Department of Aerospace Engineering, Universiti Putra Malaysia, Serdang, Malaysia
Download Abstract:
geo21.pdf