超机动飞机的非线性飞行控制研究  

Nonlinear Flight Control Design for Supermaneuverable Aircraft

作　　者：范子强[1] 方振平[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》2000年第4期404-407,共4页Journal of Beijing University of Aeronautics and Astronautics

基　　金：博士点基金资助项目

摘　　要：介绍了应用非线性动态逆理论进行战斗机过失速机动条件下飞行控制律设计的具体过程 ,首先根据奇异摄动理论将受控状态变量分为快变量和慢变量两个层次 ,快变量为三个角速率 ,慢变量为迎角、侧滑角和速度滚转角 ,然后根据非线性动态逆理论分别对内环和外环进行设计 ,其中外环控制器的输出作为内环控制器的输入指令 .最后对所设计的飞行控制律利用过失速机动仿真来加以验证 。The design of a flight control system for a supermaneuverable aircraft by means of nonlinear dynamic inversion was discussed in detail. First, the dynamics to be controlled are separated into fast and slow variables in terms of singular perturbation theory. The fast variables are the three angular rates and the slow variables are the angle of attack, sideslip angle, and bank angle. Then two dynamic inversion control laws are designed for the fast and slow variables respectively, the outputs of outer loops are used as the inputs of inner loops. The resulting control system is demonstrated using post stall maneuver simulation, the simulation results show that the dynamic inversion control law achieves a high level performance in post stall maneuver conditions.

关 键 词：战斗机 飞行控制系统 仿真 过失速机动 

分 类 号：V271.41[航空宇航科学与技术—飞行器设计] V249.122