推力矢量飞机控制律设计及过失速机动仿真研究  

Research on Flight Control Law Design of Fighter with Vectoring Thrust and Post-Stall Maneuver Simulation

作　　者：张力[1] 王立新[1] 

机构地区：[1]北京航空航天大学航空科学与工程学院,北京100083

出　　处：《飞行力学》2008年第4期1-3,7,共4页Flight Dynamics

摘　　要：利用四元数法建立了带推力矢量的战斗机全量运动方程,依据逆系统理论对推力矢量飞机进行了适用于过失速机动和超敏捷性研究的控制系统设计。根据非线性动态逆的特点将飞机的动态特性分成快慢不同的两组状态变量分别进行设计,并采用伪逆法解决了舵面分配问题。利用该控制系统对"眼镜蛇"飞机机动进行了仿真计算,结果表明该设计方法是可行的。The dynamic equations of fighter with thrust vector using the quaternion method were built. And the control system of fighter with thrust vector was designed for post-stall maneuver and super-agility by the inversion system theory. According to the features of nonlinear flight control law, the fighter＇ s dynamics were divided into two different states which were fast and slow variables. Making use of the counterfeit inversion matrix theory, the allotment of the aerodynamic helm and thrust vector control was solved. The “Cobra” maneuver was simulated by the control system, and the simulation result proves the feasibility and availability of the design method.

关 键 词：过失速机动 推力矢量 非线性动态逆 四元数 

分 类 号：V212.1[航空宇航科学与技术—航空宇航推进理论与工程]