基于非线性动态逆的大迎角飞行控制律设计  

High AOA Flight Control Law Design Based on Nonlinear Dynamic Inversion Method

作　　者：樊战旗[1] 刘林[1] 

机构地区：[1]西北工业大学自动化学院,陕西西安710072

出　　处：《计算机仿真》2012年第9期113-116,共4页Computer Simulation

基　　金：航空科学基金(20110718003)

摘　　要：研究飞机大迎角飞行优化控制问题。为了用非线性动态逆方法进行大迎角飞行控制律设计,首先建立具有大迎角条件下强非线性、非定常迟滞、不对称的力与力矩等气动特性的六自由度非线性飞机模型。然后将非线性动态逆方法与奇异摄动理论相结合,并将飞机状态划分为快慢回路,分别应用非线性动态逆方法进行了飞行控制律设计。最后,通过控制分配将计算得到的三轴力矩指令转化为相应的舵面与推力矢量偏转指令,并进行了仿真验证。仿真结果表明,设计的飞行控制律具有优良的大迎角控制效果。The nonlinear dynamic inversion method was used to design the high AOA flight control law. A 6-DOF nonlinear aircraft model with high AOA dynamic characters was built in this paper. The states of the aircraft were di-vided into two loops ： fast loop and slow loop. For each loop, the nonlinear dynamic inversion method was used to de-sign the control law. The moment command based on the nonlinear dynamic inversion method was translate into the elevator, aileron, rudder and thrust vector commands. The simulation results show that the high AOA controller has good control performance.

关 键 词：非线性动态逆 大迎角 推力矢量 飞行控制 

分 类 号：V249.1[航空宇航科学与技术—飞行器设计]