带有攻角约束的吸气式高超声速飞行器反步法控制

Backstepping control design for air-breathing hypersonicvehicle with angle of attack constraint

吸气式高超声速飞行器机动时攻角需要被约束在一定范围内以满足超燃冲压发动机的正常工作条件。针对飞行器攻角约束控制问题,使用反步法和扩展状态观测器设计了带有攻角约束能力的航迹倾角鲁棒跟踪控制器。在反步法控制器的基础上,通过构建控制模型同阶的补偿系统来限制攻角响应的幅值。当攻角超出限制边界阈值时,补偿系统以攻角和阈值的差为输入产生补偿信号。补偿信号对反步法控制器中每一步控制信号进行修正达到限制飞行器攻角幅值的目的。控制系统中还引入了扰动观测器对模型的不确定项进行估计和补偿,以提高控制系统的鲁棒性能。稳定性分析证明了这种控制器设计方法满足Lyapunov稳定性。数值仿真结果表明,该方法在具有良好的攻角约束作用和鲁棒性能。

The angle of attack of the air-breathing hypersonic vehicle needs to be restricted to constrained within a certain extent to meet the working condition of the scramjet when the vehicle is maneuvering.For the angle of attack constraint control problem,a flight path angle tracking controller,which can limit the angle of attack,is developed by using the backstepping method and extended state observer.Based on the backstepping controller,the amplitude of the angle of attack response is limited by a compensator with the same order.When the angle of attack exceeds the threshold,the compensator generates a compensation signal by the different between the angle of attack and the threshold.The compensation signals modify the each step of control signals of the backstepping controller to limit the angle of attack.The extended state observer is also used to estimate and compensate the uncertain terms of the model,in order to improve the robustness of the control system.Stability analysis proves that the proposed method satisfies Lyapunov stability.The numerical simulation results show that the proposed method has good tracking performance.And the controller is available to limit the angle of attack under the condition of wind angle of attack.