非线性动态逆方法在飞行控制律设计中的应用  

Application of Nonlinear Dynamic Inversion to Design of Flight Control Laws

作　　者：邓婷婷[1] 杨朝旭[2] 孙绍山[2] 章卫国[1] 

机构地区：[1]西北工业大学自动化学院,西安710129 [2]成都飞机设计研究所,成都610091

出　　处：《计算机测量与控制》2013年第5期1236-1239,共4页Computer Measurement &Control

摘　　要：随着现代空战环境对战斗机的性能要求日益提高,传统的飞行控制方法已经难以满足这些要求。进行了非线性动态逆飞行控制律的设计研究及其应用。按照时标分离原理将飞机状态变量进行分组,针对各子系统的响应特点,采用层叠结构的动态逆控制器,设计了飞机四组状态变量的控制律。通过水平和垂直导引的算例进行仿真验证,结果表明飞机能较好的跟踪预定航迹,跟踪误差较小。With the increasing requirements of fighter day by day, the traditional flight control methods have the difficults in meeting these requirements. The nonlinear dynamic inversion flight control law and its application are researched. According to the time--scale separation principle, the state variables will be grouped. Because of the different characteristics of each subsystem, the control laws of the four groups of state variables can be designed respectively. Through the simulations of horizontal and vertical guidance examples, the results show that the plane can effectively track along the desired route.

关 键 词：动态逆 时标分离 飞行控制 航迹跟踪 

分 类 号：V249.1[航空宇航科学与技术—飞行器设计]