基于动态逆-滑模的高速飞行器控制器设计  

Dynamic inversion-sliding mode for breathing hypersonic vehicle controller design

作　　者：李飞[1] 李新国[1] 

机构地区：[1]西北工业大学航天飞行动力学技术国家重点实验室,陕西西安710072

出　　处：《飞行力学》2016年第2期64-67,共4页Flight Dynamics

摘　　要：吸气式高超声速飞行器巡航状态下飞行环境复杂,建模时存在非线性以及参数摄动。基于小扰动假设的传统经典控制理论难以适应当前任务对鲁棒性的要求,对此提出了一种非线性动态逆-滑模控制律改进方法。通过对吸气式高超声速飞行器模型精确反馈线性化得到解耦形式的线性方程,为速度和高度设计出动态逆控制律来抵消非线性特性,在动态逆的基础上采用滑模变结构来补偿参数摄动带来的误差。仿真结果表明,所设计的控制方法具有良好的动态性能及鲁棒性。Air-breathing hypersonic vehicle cruising flight environment is complex,non-linearity and parameter perturbation exists in modeling. Based on the assumption that it is difficult for small disturbance traditional classical control theory to adapt to the current task robustness requirements,this paper presents a nonlinear dynamic inversion-sliding mode control law improvement. Through the air-breathing hypersonic vehicle model to get precise feedback linearization decoupled linear equations,the dynamic inverse control law is designed for the speed and height to offset the non-linear characteristics. On the basis of dynamic inversion,the sliding mode variable structure is adopted to compensate parameter error caused by perturbation. The simulation results show that the control method is designed with good dynamic performance and robustness.

关 键 词：非线性动态逆 滑动模态变结构控制系统 反馈线性化 

分 类 号：V448.2[航空宇航科学与技术—飞行器设计]