飞机颤振主动抑制控制律优化设计  

OPTIMAL DESIGN ACTIVE FLUTTER SUPPRESSION CONTROL LAW FOR AEROPLANE

作　　者：方力[1] 陈桂彬[1] 

机构地区：[1]北京航空航天大学飞行器设计与应用力学系

出　　处：《北京航空航天大学学报》1996年第3期342-346,共5页Journal of Beijing University of Aeronautics and Astronautics

基　　金：航空基金

摘　　要：对颤振主动抑制控制律的优化设计进行了研究．提出了一种基于“极点配置”思想，考虑低速稳定性的工程性控制律初值设置方法；在优化过程中，除考虑阵风响应等约束外，还考虑了鲁棒性问题．以某型飞机的动力相似模型为实例进行计算．计算结果表明，设计的优化控制律能有效抑制颤振，保证低速稳定性。An optimal design technique of active flutter suppression control laws is studied. An engineering initial value design method,which is based on the idea of fold pole configuration and considers the slow speed stability,was proposed;and the robustness was considered in the optimal process besides gust response constrainted.According to the method mentioned above, an optimal control law was explored to a dynamic model of a type of aeroplane.The calculation results show that it can suppress flutter effectively and guarantee the slow speed stability,and the system satisfies the stability margins requirements.

关 键 词：颤振 主动 约束 控制定律 鲁棒性 飞机 

分 类 号：V215.34[航空宇航科学与技术—航空宇航推进理论与工程]