Abstract
This paper takes a six degrees of freedom model of a generic hypersonic vehicle as the research object. The design of flight control system for hypersonic vehicle must deal with strong couplings between variables of nonlinear dynamic model. Using dynamic inversion method, a combined system model of hypersonic vehicle is built. The variables of hypersonic vehicle longitudinal dynamic model are decoupled. Taking into account the parameter uncertainty of dynamic model, this paper designs a flight control system of hypersonic vehicle using the sliding mode control method. The simulation results demonstrate that the hypersonic vehicle flight control system is robust and meets the performance requirements with fight condition.
Published Version
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