柔性飞机阵风载荷减缓飞行控制律设计  

Design of Flight Control Law of Gust Alleviation for Flexible Aircraft

作　　者：刘世前[1] 朱纪洪[2] 胡金春[2] 

机构地区：[1]上海交通大学空天科学技术研究院,上海200030 [2]清华大学计算机系智能技术与系统,北京100084

出　　处：《系统仿真学报》2007年第11期2519-2522,共4页Journal of System Simulation

基　　金：国家航空联合基金(10577012);国家博士后基金(2005038311)。

摘　　要：针对大型柔性飞机纵向飞行运动中气动弹性与飞行品质的耦合控制问题,首先建立柔性飞机动力学模型,运用分布参数系统输出反馈进行纵向短周期运动飞行品质与基本结构模态应力约束下的多指标融合控制设计,在此基础上运用多指标相容控制设计方法进行大型柔性飞机阵风减缓主动控制律设计,最后数值仿真验证设计方法的可行性与有效性。For the coupling control problem between aeroelasticity andflight quality of longitudinal flight control for flexible aircraft, the flight dynamics and structural dynamics model of the aircraft were built up based on a distributed parameter system. Furthermore satisfactory control under constraints of flight quality of longitudinal short-period moment and the wing＇s bending- and torsion-stresses requirement of primary structural modes was designed by output feedback of normal acceleration of the distributed parameter system. Meanwhile gust alleviation control for the flexible aircraft was scheduled by this satisfactory control. A numerical simulation verifies the design approach available and effective, and some conclusions have been proposed.

关 键 词：气动弹性 阵风减缓 弹性模态控制 协方差配置 

分 类 号：V249.1[航空宇航科学与技术—飞行器设计]