后缘小翼型智能旋翼桨叶模型设计分析与试验研究

摘要

The design and test of the smart rotor model with active trailing edge flap is performed based on a push-pull double X-frame piezoelectric actuator.The static displacements of piezoelectric stacks and actuators are measured.Unload test is used to verify the performance of the actuator and the load test is conducted to demonstrate whether the actuator can drive the flap with hinge moment in hover.The deflection of the trailing edge flaps are measured by using linear Hall sensors in different actuation frequencies and voltages.Test result agrees with the analysis and shows that the piezoelectric actuators can actuate the flaps and the method is practicable and feasible.%提出了一种基于推挽式双X压电驱动机构的后缘小翼型智能旋翼方案,开展了后缘小翼型智能旋翼模型的设计分析与试验研究.空载试验主要用于验证驱动机构的驱动特性,测试了压电堆和驱动机构的静态输出;为了验证悬停时小翼在铰链力矩作用下驱动机构能否有效驱动后缘小翼,进行了加载试验.试验采用线性霍尔传感嚣对推挽式双X型驱动机构在不同电压和频率驱动下小翼的偏转角度进行了测量.理论分析与试验测试结果基本吻合,压电驱动机构能够有效驱动后缘小翼,该智能旋翼方案是合理和可行的.