高超声速飞行器的抗饱和切换控制

Anti-Windup Switched Control of Hypersonic Vehicle

针对高超声速飞行器动力学模型强非线性及飞行过程中系统参数变化剧烈的问题,提出一种根据飞行包线分区并分别建立独立的子系统的切换系统建模方式和抗饱和切换控制方法。通过缩小子系统模型对应的飞行空域,降低系统线性化以及参数变化带来的影响,使得线性控制理论能够应用于高超声速飞行器的控制器设计当中。考虑到飞行过程中可能会遇到的执行器饱和问题,本文在切换系统模型的基础上,为高超声速飞行器设计了抗饱和切换控制器。仿真算例验证了提出的切换系统模型的优越性及抗饱和控制器的有效性。

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.