基于非线性控制分配的飞翼航向控制方法

Yaw Control of a Flying-Wing Aircraft Based on Nonlinear Control Allocation

研究了某无尾飞翼式布局飞行器采用升降副翼实现航向控制的操纵机理,分析了舵面的三轴耦合特性,提出基于非线性可达转矩集的飞行器操纵能力描述。在此基础上,对飞行控制系统进行模块化设计,利用经典控制方法设计出产生整个控制指令的基本控制律,然后利用基于微分进化算法的非线性控制分配器将整个控制指令合理地分配到各个舵面上,实现航向上的稳定与控制,仿真结果证实了该方案的有效性。

According to the characteristics of an aircraft with a tailless fly-wing configuration,the control principles using elevons for yaw control and the coupling effect on a single effecter are researched.The formulation of control capability based on nonlinear attainable moment sets is proposed.A modular design scheme is introduced,firstly a baseline control law is designed by a classic control methodology to generate the total control command for the aircraft motion,then the total control command is distributed properly by a nonlinear control allocator based on the differential evolution algorithm to each effector, the yawing stability and control are satisfied, also the three axis coupling effect is eontrolled, the simulation results show the effectiveness of the proposed scheme.