Abstract
To improve the accuracy of relative navigation for spacecraft formation flying in eccentric orbits, precise relative motion equation was used and Carrier-phase Difference GPS technology was adopted for relative information measurement. A modified version of Extended Kalman Particle Filter algorithm, called MEKPF, was used for navigation filter design. Simulation results provided later indicate the proposed navigation approach can provide an accuracy and consistent relative navigation output for spacecraft formation flying.
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Wang, X., Zhang, L., Qian, X., Xu, Q., Meng, Y., Su, Z. (2012). A Modified Extend Kalman Particle Filter with Application to Relative Navigation. In: Sun, J., Liu, J., Yang, Y., Fan, S. (eds) China Satellite Navigation Conference (CSNC) 2012 Proceedings. Lecture Notes in Electrical Engineering, vol 160. Springer, Berlin, Heidelberg. https://doi.org/10.1007/978-3-642-29175-3_42
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DOI: https://doi.org/10.1007/978-3-642-29175-3_42
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