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ITCG Based on Optimal Control and Predictor-Corrector for Hypersonic Vehicles

An impact time control guidance(ITCG) algorithm for hypersonicvehicle in glide phase is proposed in this paper. It introduces the optimal guidance law via quasi-equilibrium gliding condition (QEGC) which can meet the terminal constraints of latitude, longitude, altitude andflight-path-angle. The lateral maneuvering strategy for impact time control is designed, in which the time-to-go is predicted analytically considering time-varying velocity. The magnitude of lateral maneuvering overload is calculated via deviation between the predicted and required impact time. In addition, the maneuvering direction, also called the sign of lateral maneuvering overload is determined with the help of the designed heading error corridor. Finally, the influence of the deviation on the guidance performance is analyzed through the simulation experiments of CAV-H.