飞行器变结构姿态控制的研究

Research on Variable Structure Attitude Control of Aircraft

本文针对飞行器姿态控制中存在的子系统之间的动态耦合问题，给出了一种自适应变结构控制律。并对于变结构控制中存在的模态颤振问题提出了一种具体解决方法。理论分析和仿真研究表明此控制律具有姿态跟踪精度高，实时计算量小，便于工程实现等优点。

This paper presents a kind of adaptive variable structure control law for the dynamic coupling problems existing between subsystems of the aircraft attitude control and discusses a method to solve the sliding mode vibration problem in the variable structure control system.Theoretical analysis and the simulation results show that this method has the advantages of good attitude tracking accuracy,less real time calculations and easy realization.