基于反馈线性化和变结构控制的飞行器姿态控制系统设计  

Design for aerocraft attitude control system based on feedback-linearization and variable-structure-control

作　　者：韩艳铧[1] 周凤岐[1] 周军[1] 

机构地区：[1]西北工业大学航天学院,西安710072

出　　处：《宇航学报》2004年第6期637-641,668,共6页Journal of Astronautics

摘　　要：在大姿态角的情况下,飞行器姿态运动的非线性因素和耦合因素不容忽略,使得传统的基于小扰动假设的近似线性化处理方法面临难以克服的困难。本文首先运用反馈线性化方法,将飞行器姿态通道线性化解耦成三个单输入单输出系统,然后运用分散滑动模态变结构控制理论对每个通道分别设计变结构控制器,以期使系统获得对参数摄动和外部扰动的鲁棒性。理论研究和数值仿真表明,所设计的控制系统可以适用于飞行器大姿态角飞行的情况,并对系统参数摄动和外部扰动具有较强的鲁棒性。There exist strong nonlinearity and coupling while the aerocrafts attitude angle is large. So the traditional approximative linearization method based on small disturbance faces difficulties. In this paper, the attitude channel of aerocraft was decoupled into three SISO linear systems by means of feedback-linearization. Then variable-structure-controller was designed based on the theory of decentralized sliding mode control with respect to each attitude channel, so as to obtain robustness to perturbation and disturbance. Theoretical research and numerical simulation indicate that the control system designed in this paper works properly even if in the case of large attitudes of aerocraft. At the same time, the control system is robust to perturbation and disturbance. It is necessary to point out that matching conditions are always satisfied in the case of the SISO system which state variables are phase variables, so the invariance of the sliding mode to uncertainties holds at all time.

关 键 词：飞行器 姿态控制 非线性 反馈线性化 变结构控制 滑动模态 

分 类 号：V448.22[航空宇航科学与技术—飞行器设计]