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针对在倾斜转弯时高超声速飞行器自动驾驶仪设计中系统参数不确定和干扰严重、各通道之间存在强烈耦合的问题,提出了一种全局积分滑模变结构解耦控制方法。该方法基于滑动模态对匹配的参数不确定和外界干扰的不变性原理,采用了一种全局积分型的滑模面,使系统在初始阶段就处于滑模态,同时通过滑模函数反馈削弱参数摄动及干扰产生的滑模误差,实现了各输出之间的全程解耦和鲁棒稳定。仿真结果证实了所提方法具有良好的跟踪性能和鲁棒性,能满足高超声速飞行器倾斜转弯协调控制的要求。
Aiming at the problem of uncertain system parameters and severe interference in hypersonic vehicle autopilot design and strong coupling between the various channels in tilting corner, a global integrated sliding mode variable structure decoupling control method is proposed. Based on the principle of invariance of sliding modal pair matching and invariance of external disturbance, a globally integrated sliding mode surface is adopted to make the system in sliding mode in the initial stage and to be weakened by the feedback of the sliding mode function Parameter perturbation and interference sliding mode error, to achieve the full decoupling between the output and robust stability. The simulation results show that the proposed method has good tracking performance and robustness, and can meet the requirements of coordinated control of hypersonic vehicle tilt bends.