高超声速飞行器的滑模预测控制方法  

Sliding Mode Predictive Control for Hypersonic Vehicle

作　　者：高海燕[1] 蔡远利[1] 

机构地区：[1]西安交通大学电子与信息工程学院,西安710049

出　　处：《西安交通大学学报》2014年第1期67-72,共6页Journal of Xi'an Jiaotong University

基　　金：国家自然科学基金资助项目(60972146;60602025)

摘　　要：针对高超声速飞行器非线性、强耦合、快时变、不确定性等特点,结合滑模控制鲁棒性强和预测控制可以显式处理约束条件的优点,提出了一种滑模预测控制器设计方法。首先,在平衡点将高超声速飞行器的纵向模型进行小扰动线性化,得到用于控制器设计的预测模型;然后,基于小扰动模型利用极点配置设计渐近稳定的滑模面,对滑模面进行预测并在性能指标中优化,通过矩阵变换将优化问题转化为二次规划问题,避免了常规滑模控制的高频切换,有效地克服了抖振现象。仿真试验表明:当存在参数不确定时,滑模预测控制能有效地克服干扰信号,实现速度和高度的精确跟踪,保证输入和状态均在约束范围之内;稳态时系统误差趋近于滑动面并且一直处在这个滑模面上,不存在抖振现象。Considering the nonlinearity, strong coupling, fast time-varying and uncertainty of hypersonic vehicle, a sliding mode predictive control strategy is proposed, in which the strong robustness of sliding mode control is combined with the ability of predictive control for handling the constraints. The longitudinal dynamics of hypersonic vehicle is linearized at the equilibrium to get the predictive model. Then pole placement is adopted to design asymptotically stable sliding mode surface following the small perturbation linearized model, and the sliding mode surface is predicted and optimized in the performance index. The optimization problem becomes a quadratic programming problem by matrix transformation, thus the frequent switching on the sliding mode surface is avoided and the chattering is suppressed. Simulations show that the altitude and velocity are tracked accurately even with parameter uncertainties, and the control and state are all in the limited scope. The steady-state tracking errors approach the sliding mode surface, and keep staying on the sliding mode surface without chattering.

关 键 词：高超声速飞行器 滑模变结构控制 滑模预测控制 鲁棒性 

分 类 号：TJ765.2[兵器科学与技术—武器系统与运用工程]