高超声速飞行器鲁棒预测滑模姿态控制方法

A Robust Predictive Sliding Mode Attitude Control Method for Hypersonic Vehicles

针对高超声速飞行器(HSV)在巡航段飞行时模型参数不确定和干扰的问题,提出了HSV鲁棒预测滑模姿态控制方法,由系统实际输出值与参考轨迹的误差设计滑模面,引入预测函数对误差进行预测可得未来时刻的滑模面,再利用改进的滑模趋近律设计快慢回路控制器。该方法能使HSV在参数不确定和有干扰的情况下,保证姿态系统稳定,精确跟踪指令信号,具有较强的鲁棒性,提高了系统的控制性能。最后,通过仿真验证了该方法的有效性。

Aiming at the problems of model parameter uncertainty and interference of Hypersonic Vehicles(HSVs)in cruise phase a robust predictive sliding mode attitude control method is proposed.The sliding mode surface is designed by using the error between the actual output value and the reference trajectory and the prediction function is introduced to predict the error thus the sliding mode surface of the future time can be obtained.The speed-loop controller is designed by using the improved sliding mode approaching law.This method ensures the stability of the attitude system and the accurate tracking of the command signal under the condition of uncertain parameters and interference which has strong robustness and improved control performance.The effectiveness of the method has been verified by simulation.