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- W2368854780 abstract "Based on dynamic inversion and terminal sliding mode control method,a method of integrated design of the guidance and attitude control for hypersonic flight vehicle is proposed according to the feature that hypersonic vehicle model is highly nonlinear,strong coupling and great uncertainties.The nonlinear decoupling ability of dynamic inversion with the strong robustness of terminal sliding mode control is combined very well in this method.Thus,the nonlinear longitudinal dynamic model of hypersonic flight vehicle can be linearized completely from the Input/Output point of view by feedback linearization.The terminal sliding mode control system can ensure the longitudinal flight stability under the influence of uncertain parameters and outside interference.The simulation results show that the proposed control method is feasible for hypersonic flight vehicle." @default.
- W2368854780 created "2016-06-24" @default.
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- W2368854780 date "2012-01-01" @default.
- W2368854780 modified "2023-09-28" @default.
- W2368854780 title "The Terminal Sliding Mode Control System Design for Hypersonic Flight Vehicle" @default.
- W2368854780 hasPublicationYear "2012" @default.
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