某无人直升机机身框架动力学计算与试验研究  

Finite Element Analysis and Test on Dynamic Characteristics of Fuselage Frame of Unmanned Helicopter

作　　者：谢勤伟 姜年朝[1,2] 周光明[2] 张逊 王克选 张志清 

机构地区：[1]总参六十所,南京210016 [2]南京航空航天大学航空宇航学院,南京210016

出　　处：《噪声与振动控制》2012年第4期34-36,120,共4页Noise and Vibration Control

基　　金：国家自然科学基金(10772079)

摘　　要：建立某无人直升机机身框架的动力学有限元模型,计算得到前六阶固有频率和振型,与模态试验结果相比较,误差小于3%,验证了有限元模型的正确性,表明该有限元模型能准确地反映该无人直升机框架的结构动力学特性。有限元计算的机身框架固有频率值避开了旋翼、尾桨、发动机主通过频率值,满足动力学设计要求。这种有限元计算、试验验证以及模型修改相结合的动力学分析方法,能保证框架固有特性计算的精确,也为无人直升机其它结构的动力学建模提供借鉴。The finite element model of structural dynamics of fuselage frame of unmanned helicopter was established and the natural frequencies and mode shapes of its first 6 orders were obtained. Compared with modal test, the maximum error of calculation was less than 3 %. It shows that the finite element model is correct and accurately reflects the structural dynamics character of the fuselage frame of unmanned helicopter. The computational natural frequencies of frame avoided the natural frequencies of main rotor, tail blade and engine and can meet the request of dynamic of unmanned helicopter. The dynamic analysis method based on finite element analyses, which combines verification test and modal modification, can effectively guarantee the accuracy of the fuselage frame of unmanned helicopter. And it also provides the refrence for finite element dynamic modeling about other structure of unmanned helicopter.

关 键 词：振动与波 无人直升机 框架 动力学 有限元建模 模态试验 

分 类 号：TH16[机械工程—机械制造及自动化] V214.12[航空宇航科学与技术—航空宇航推进理论与工程]