粗纤维压电复合材料(MFC)对旋翼桨叶模型扭转控制的实验及数值研究  

Experimental and Numerical Analysis for Twist Control of Rotor blade model with Macro Fiber Composite(MFC)

作　　者：张红艳[1,2] 白长青[2] 沈亚鹏[2] 

机构地区：[1]长安大学,西安710064 [2]西安交通大学,西安710049

出　　处：《应用力学学报》2009年第3期456-460,共5页Chinese Journal of Applied Mechanics

基　　金：中国博士后基金(20090451382);陕西省自然科学基金(SJ08A19)

摘　　要：对直升机旋翼桨叶进行主动扭转控制是直升机减振主动控制技术中的有效方法之一。本文采用粗纤维压电复合材料(MFC)对旋翼模型进行了扭转控制的实验研究,并建立该结构的有限元模型,将数值结果与实验结果进行了对比分析。实验中,我们采用预扭的悬臂梁模拟旋翼桨叶,在其上表面贴有MFC压电片进行作动。测量得到了不同作动电压下结构的扭转变形,与数值结果进行对比,两者具有很好的一致性。实验及数值结果表明,随着作动电压的增大,结构的扭转角呈线性增加;MFC材料各向异性系数增大,梁的扭转角亦相应增加,采用MFC材料对旋翼进行扭转控制是行之有效的。The active twist control of helicopter rotor blade is efficient one of the active vibration control techniques. The experimental and numerical analysis of twist control of rotor blade model with Macro Fiber Composite (MFC) is performed. The rotor blade is modeled by a pre-twist cantilever, in the test, and the MFC piezoelectric patch is pasted on its upper surface. The twist angles are measured with different actuate voltages, and the experimental results coincide well with the numerical ones, which shows that the twist angle of the pre-twist cantilever is linearly increased with the increasing actuate voltage, and it also increases with the anisotropic property of the MFC. The predicted and measured results are provided to validate the effectiveness of MFC to control the twist angle.

关 键 词：主动控制 压电作动器 MFC材料 直升机 旋翼 

分 类 号：O322[理学—一般力学与力学基础]