基于反馈线性化的直接侧向力与襟翼复合控制

Compound control with flaps and reaction jets based on feedback linearization

针对高超声速飞行器再入过程中气动舵面烧蚀与失效的问题,选用具有良好热防护性能的尾装襟翼作为气动执行机构,但欠驱动的气动控制将使飞行器存在不稳定内动态,从而使飞行器成为非最小相位系统。为抑制不稳定内动态对系统稳定性的危害并提高襟翼飞行器在临近空间高超声速飞行的控制品质,在飞行器的俯仰与偏航通道中各引入一对姿控发动机,构成襟翼与直接侧向力复合控制系统。建立了襟翼飞行器复合控制系统数学模型,并基于该模型分析了过载输出时系统内动态的有界稳定条件。针对内动态稳定的复合控制系统,运用输入-输出反馈线性化方法设计了控制器,并分析了襟翼和姿控发动机之间的配合机理。进行了快时变背景下的对比仿真,仿真结果表明,该复合控制系统有比纯襟翼控制作用下更好的动态品质,并对气动参数快时变具有一定的鲁棒性。

To solve the problem of ablation and failure of the aerodynamic control surface during the reentry process of hypersonic vehicle, the tail-mounted flaps with impressive thermal protection performance are selected as the aerodynamics actuator, but the underactuated aerodynamics control makes the vehicle become a non-minimum phase system with unstable internal dynamics. In order to restrain the harm to system stability caused by unstable internal dynamics and improve the control quality of hypersonic vehicles in near space, by introducing reaction jets into pitch and yaw channels, a compound control system of the flap and direct lateral force is established. In this paper, the mathematical model of the compound control vehicle is established, and the bounded stability conditions of system internal dynamics with overload output are analyzed based on this model. A controller is designed by input-output feedback linearization method for the compound control system with stable internal dynamics, also the cooperation mechanism between flaps and reaction jets is analyzed. The comparative simulations are carried out under the parameter fast time-varying background, The results show that the dynamic performance of the compound control system is better than that of the flaps control system, and it has enough robustness to deal with the fast time-varying aerodynamic parameters.