飞机姿态控制系统的精确线性化解耦设计  

Exactly Linearized and Decoupled Design for Airplane Attitude Control System

作　　者：吴庆辉[1] 周洲[1] 郝峰 

机构地区：[1]西北工业大学无人机特种技术国防科技重点实验室,陕西西安710065 [2]现代控制技术研究所第二总体部,陕西西安710065

出　　处：《计算机仿真》2011年第2期55-57,127,共4页Computer Simulation

摘　　要：飞机姿态运动的非线性以及横航向强耦合,增加了控制飞机姿态的难度,不利于飞机快速瞄准目标。为了提高控制姿态性能,直接将飞机姿态角解耦成舵偏角的非线性设计方法,将飞机姿态运动解耦成三个独立的线性系统,并避免气动力矩对舵面进行再次分配,使整个过程更加直观,随后对解耦的单输入单输出系统设计了跟踪控制律,并进行仿真。结果表明,所设计的控制系统姿态角的控制效果较好,并具有很高的控制精度。The nonlinear and strong coupling characters of airplane＇s attitude motion increases the difficulty to control the attitude and disadvantage to aim target.A method was discussed,which directly decoupled attitude angles into the control surface deflections by using nonlinear theory and the attitude channel into three SISO linear systems to avoid distributing the aerodynamic moments to control surface deflections,and made the designing process straight.Then tracking control law was designed for each decoupled SISO system.And analysis of robustness was done to perturbation of mass and uncertainty of aerodynamic moments.The theoretical research and numerical simulation both indicated the excellent performance of the decoupled control system and high control accuracy.

关 键 词：微分几何 精确线性化 解耦 姿态控制 

分 类 号：V249.1[航空宇航科学与技术—飞行器设计]