变弯度机翼后缘多电机分布式控制系统设计与验证

Design and Verification of Multi Motor Distributed Control System for Variable Camber Wing Trailing Edge

飞机变弯度机翼后缘通过机械机构和/或柔性结构变形驱动,根据飞行状态实时连续光滑调节机翼弯度,从而获得最优气动效率,实现减阻、减重、降低燃油消耗等目的。本文针对全尺寸变弯度机翼后缘多节转动模型设计并搭建了测控系统,选用改进的偏差耦合算法,实现了三台电机的协同控制,以角度传感器和光纤变形传感器融合的反馈实现机翼后缘偏转闭环控制;完成了系统软、硬件的设计,并对全尺寸后缘模型驱动系统进行了空载及地面加载试验。结果表明,测控系统可以实时控制电机间的角度偏差在允许的误差范围内,在有无载荷情况下,驱动系统工作无显著差异;在随动加载情况下,驱动控制系统能够使变弯度机翼后缘偏转到设定角度,控制系统超调量小于0.20°,三电机最大角度差小于30°,满足变弯度机翼的协同偏转要求,为下一步变弯度机翼实现三维变形提供了技术储备。

Variable camber wing is deformed and driven by front and rear edge deflection mechanism and/or flexible structure.According to the flight state,the wing curvature can be adjusted continuously and smoothly in real time so as to obtain optimal aerodynamic efficiency,and then achieve the purpose of reducing drag,weight and fuel consumption.In this paper,a measurement and control system is designed and built for the multi segment rotation model of the full-size variable camber wing trailing edge.The improved deviation coupling algorithm is selected to achieve the coordinated control of three motors.The closed-loop control of the wing trailing edge deflection is achieved with the feedback of angle sensor and optical fiber deformation sensor fusion;The hardware and software of the system are designed,and the full size trailing edge model drive system is tested under no-load and ground loading.The results show that the measurement and control system can control the angle deviation between motors within the allowable error range in real time,and there is no significant difference in the operation of the drive system with or without load;Under the condition of follow-up loading,the drive control system can make the trailing edge of the variable camber wing deflected to the set angle,the overshoot of the control system is less than 0.20°,and the maximum angle difference between the three motors is less than 30°,which meets the requirements of the cooperative deflection of the variable camber wing,and provides technical reserves for the next step of achieving three-dimensional differential deformation of the variable camber wing.