基于被控变量设计的飞机动态逆控制律  

Dynamic-inversion control law for airplane based on design of controlled variables

作　　者：李导[1] 杨伟[1,2] 杨朝旭[2] 孙绍山[2] 

机构地区：[1]西北工业大学航空学院,西安710072 [2]中国航空工业集团公司成都飞机设计研究所,成都610041

出　　处：《四川大学学报（自然科学版）》2014年第1期95-100,共6页Journal of Sichuan University(Natural Science Edition)

基　　金：成都飞机设计研究所创新基金(GCDSC170)

摘　　要：分析了目前有人驾驶飞机控制律设计在结合动态逆控制方法时所存在的问题.参考广泛研究的分层结构的动态逆控制律,并根据机动飞行的要求对进行了有针对性的被控变量设计.通过将用于复合函数求导的雅克比行列式与动态逆相结合,采用非分层结构的Lie导数动态逆运算实现飞机绕速度矢量的滚转机动,仿真结果良好.该方法能够在减少逆运算次数的同时稳定系统状态,简化了目前所广泛研究的动态逆控制结构,并且很好的与目前飞行员指令信号相匹配.The problem exist of control law design for manned combat aircraft base on Dynamic-Inversion method has been analyzed. Dynamic-Inversion control law with nested structure which has been widely studied was refere here, and the Controlled Variables have been introduced to be designed according to the requirment of maneuver. The Jacobian which is used for derivative of compound functions was com- bined with Dynamic-Inversion, inversion control Based on Lie-Derivative without nested structure was employed to achieve a roll maneuver about the Velocity Vector, with a nice simulation result. This ap- proach could stable the system states with less inversion calculation and simplified the structure of Dy- namic-Inverstion control, also it matched the pilot command signal.

关 键 词：动态逆 被控变量设计 Lie导数 快慢回路 雅克比式 

分 类 号：V22[航空宇航科学与技术—飞行器设计]