考虑动压限制的高超声速飞行器控制系统设计

Designing Control System of Hypersonic Vehicle with Dynamic Pressure Constraints Considered

针对高超声速飞行器超燃冲压发动机的进气道对飞行动压有比较苛刻的要求,提出一种直接进行动压反馈的高超声速飞行器控制系统设计方法。首先,建立了高超声速飞行器动压反馈控制的动力学模型,并推导了动压控制的状态方程。然后,利用线性二次型最优控制方法,通过引入动压误差进行控制对象增广,从而在动压控制回路中引入积分控制,以消除动压跟踪误差,给出了高超声速飞行器动压控制的控制系统结构。最后,通过仿真验证了动压控制器具有很好的跟踪性能,考虑存在气动、推力不确定性因素,飞行器速度出现偏差时,动压控制系统可以自适应地调整飞行高度以保证对动压指令的跟踪,控制系统具有很好的鲁棒性。

An airbreathing hypersonic vehicle(AHV) generally adopts a scramjet engine as its propulsion, which needs strict conditions of flight dynamic pressure. A new dynamic pressure control system is presented, in which the AHV autopilot directly uses dynamic pressure to track the dynamic pressure command. Firstly, the dynamic pressure model of the AHV is established and the state equations of dynamic pressure control are given. Then, the dynamic pressure control system is implemented using the LQR optimal control theory. The dynamic pressure error is augmented in order to add an integral control to track the dynamic pressure with zero steady error. The structure of the dynamic pressure control system is also obtained. The simulation results show that the dynamic pressure control system has a good performance for guaranteeing the dynamic pressure of the scramjet engine with the disturbance of drag and thrust considered.