飞行器控制律设计方法发展综述  

Developing Status of Control Law Design Methods for Flight

作　　者：王美仙[1] 李明[2] 张子军[1] 

机构地区：[1]沈阳飞机设计研究所飞行控制部,辽宁沈阳110035 [2]沈阳飞机设计研究所,辽宁沈阳110035

出　　处：《飞行力学》2007年第2期1-4,共4页Flight Dynamics

摘　　要：综述了飞行器控制律设计方法的研究和应用状况。首先简述了现代控制理论的发展状况,然后给出最优控制法、特征结构配置法等线性设计方法和非线性反馈线性化、非线性H∞优化与μ综合鲁棒控制、滑模变结构控制、反步控制、神经网络控制、自适应控制等非线性设计方法的特点及其在飞行器控制律设计上的限制,最后分析总结了存在的问题及未来的发展方向。Research and application of control law design methods were surveyed. Firstly, this article introduced the developing status of control law design methods for advanced aircraft. Then, several linear design methods that are linear quadratic and eigenvector configuration, and nonlinear design methods that are feedback linearization, robust control of H∞ optimization and μ-synthesis, backstepping control, neural networks control and self- adaptivecontrol, and the limits in application of flight control systems were given. Finally, several key problems of the methods were analyzed and summarized in control law designing for advanced aircraft.

关 键 词：飞行器 控制律设计 线性控制 非线性控制 

分 类 号：V249.1[航空宇航科学与技术—飞行器设计]