Abstract
With a concern about the missile attitude control system, this paper attempts to solve the online calculation method of the coefficient of the small deviation equation, on which a LFT-based LPV model of the missile attitude control system is set up.
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Acknowledgments
This work was supported in part by the National Nature Science Foundation of China, No 60975058, Nature Science Foundation of Hubei NO.2010CDB01904, 2010 Aerospace Technology Support Foundation, 2010 Defense Innovation Research Foundation of Huazhong University of Science and Technology.
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Ni, S., Wu, J., Shan, J., Liu, L., Wang, Y., Hu, K. (2012). LPV Modeling of the Missile Attitude Control System Based on Small Deviation Equation. In: Wang, X., Wang, F., Zhong, S. (eds) Electrical, Information Engineering and Mechatronics 2011. Lecture Notes in Electrical Engineering, vol 138. Springer, London. https://doi.org/10.1007/978-1-4471-2467-2_218
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DOI: https://doi.org/10.1007/978-1-4471-2467-2_218
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