Abstract: The problems of switched system model and anti-windup control of hypersonic vehicle are investigated. In order to solve the nonlinearity associated with the dynamic model of hypersonic vehicle as well as the parameter variation during flight, a flight envelope partition based switched system modeling approach is proposed. By shrinking the flight airspace corresponding to the subsystem mode, the impact introduced by model linearization is reduced along with the parameter variation, such that the linear control theory can be applied to the control problem of hypersonic vehicle. Considering the actuator saturation problem encountered during flight, this paper designs an anti-windup switched controller based on the proposed switched system model. A simulation example is demonstrated to verify the advantage of the proposed switched system model as well as the effectiveness of the anti-windup controller.

Key words: Hypersonic vehicle, Switched control, Anti-windup control, Persistent dwell-time(PDT)