飞翼布局无人机控制律设计

以某飞翼布局无人机为设计对象,进行内、外回路的控制律设计.在Matlab/Simulink仿真环境下,建立飞翼布局无人机线性小扰动模型,分析纵向、横航向模态特性,根据本体特性缺陷针对性地设计控制律内回路反馈支路及增益,经反馈补偿后的飞行品质满足GJB 185-1986相关要求.在内回路控制律的基础上设计外回路PI控制器实现飞机姿态控制,各控制回路的系统稳定裕度计算结果满足GJB 2191-1994要求.建立飞翼布局无人机六自由度非线性仿真模型,仿真验证结果表明所设计的内、外回路控制律能够精确控制飞机姿态且精度满足GJB 2191-1994要求,同时系统鲁棒性良好.

Design of Flight Control Law for a Flying-Wing UAV

The control law of the inner and outer loops for flying-wing UAV is designed.In the Matlab/Simulink simulation environment,a linear small disturbance model of the flying-wing UAV was established,the longitudinal and transverse modal characteristics were analyzed,and the feedback loop and gain of the inner loop of the control law were designed according to the defects of the body characteristics.The flight quality after feedback compensation meets the relevant requirements of GJB 185-1986.The outer loop PI controller was designed on the basis of the inner loop control law to achieve the aircraft attitude control,and the calculation result of the system stability margin of each control loop meets the requirements of GJB 2191-1994.A six-degree-of-freedom nonlinear simulation model of flying-wing UAV was established.The simulation verification results show that the designed inner and outer loop control laws can accurately control the aircraft attitude and the accuracy meets the requirements of GJB 2191-1994,and the system has good robustness.