Abstract
The reconfigurability of satellite control systems is a fundamental index to the capability of spacecraft stability after the faults occur in the process of satellite operating in-orbit. This paper addresses the problem of reconfigurability evaluation for faulty control systems. Firstly, The reconfiguration indicator based on system stability is presented by regarding the faults that occur in the system as model uncertainties. And then the method for normalized coprime factorization is introduced to describe the maximal reconfigurability boundary, which causes the control system instability when the fault exceeds the allowable range of the given controller and model. Finally, the efficacy of the proposed method is tested through an numerical simulation on the Hubble telescope.
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Xu, H., Wang, D., Li, W. (2016). A Reconfigurability Evaluation Method for Satellite Control System. In: Jia, Y., Du, J., Li, H., Zhang, W. (eds) Proceedings of the 2015 Chinese Intelligent Systems Conference. Lecture Notes in Electrical Engineering. Springer, Berlin, Heidelberg. https://doi.org/10.1007/978-3-662-48386-2_61
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DOI: https://doi.org/10.1007/978-3-662-48386-2_61
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