Abstract
A scheme for integrated guidance/autopilot design for missiles based on terminal sliding-mode control is proposed. Firstly, the terminal sliding mode control is introduced, based on which and the backstepping idea the guidance/control law is designed when an integrated guidance/autopilot model of the yaw plane is formulated. Secondly, an estimating method is given for the unavailable information of the maneuvering target, and an auxiliary control based on a sliding mode estimator is used to offset the estimation error. Finally, a simulation of some missile against high maneuvering targets on the yaw plane was made to verify the effectiveness and rightness of the scheme, and the simulation results have shown that high accuracy of hitting target can be got when the scheme is adopted.
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© 2005 Springer-Verlag Berlin Heidelberg
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Yu, J., Tang, D., Gu, Wj., Xu, Q. (2005). The Application of TSM Control to Integrated Guidance/Autopilot Design for Missiles. In: Huang, DS., Zhang, XP., Huang, GB. (eds) Advances in Intelligent Computing. ICIC 2005. Lecture Notes in Computer Science, vol 3645. Springer, Berlin, Heidelberg. https://doi.org/10.1007/11538356_34
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DOI: https://doi.org/10.1007/11538356_34
Publisher Name: Springer, Berlin, Heidelberg
Print ISBN: 978-3-540-28227-3
Online ISBN: 978-3-540-31907-8
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