大型客机进近倾斜姿态H_∞控制研究  

Research on Landing Roll Attitude H_∞ Control for Large Civil Aircrafts

作　　者：李欣[1] 江驹[1] 甄子洋[1] 张平[1] 辛君捷[1] 

机构地区：[1]南京航空航天大学自动化学院,南京210016

出　　处：《电光与控制》2013年第4期34-37,46,共5页Electronics Optics & Control

基　　金：中央高校基本科研业务费专项资金(kfjj20110207);自然基金(71071076);航空基金(2010ZA52002)

摘　　要：实现快速、精准、抗扰动性强的倾斜姿态控制,是大型客机自动着陆控制系统设计的关键技术之一。以Boeing707飞机在常值侧风扰动下的非线性数学模型为基础,通过配平线性化得到线性方程,综合设计了进近着陆阶段的姿态控制律。由于使用PID控制方法的滚转角响应难以兼顾快速性与稳态性能,设计了基于鲁棒H∞理论的倾斜姿态控制律。分别对两种控制方法跟踪滚转角阶跃指令,以及抗侧风扰动的控制效果进行了比较分析。仿真结果表明,状态反馈H∞控制方法能够实现快速、精准、无超调的倾斜姿态控制,且有侧风扰动存在时具有快速的恢复能力、较好的乘坐品质和较大的抗扰动控制余度。Quick, accurate, and anti-disturbance roll attitude control is one of the key technologies of automatic landing control system design for air buses. Based on nonlinear mathematical model of Boeing707 under constant crosswind disturbance, the linear model was obtained by trim and linearization, and the attitude control law for approach and landing was designed. Considering that it＇s difficult to realize rapid and stable response of roll angle with PID control method, we designed a robust H∞ control law. The two methods were analyzed on their capability of tracking roll attitude command and anti-crosswind disturbance. Simulation results indicated state feedback H∞ controller can achieve quick, accurate and no overshoot roll attitude control, and has ability of faster recovery, better riding quality and larger control redundancy of restraining crosswind disturbance.

关 键 词：大型客机 倾斜姿态控制 侧风扰动 鲁棒H∞控制 

分 类 号：V249.1[航空宇航科学与技术—飞行器设计] TP273[自动化与计算机技术—检测技术与自动化装置]