噪声与振动控制2012，Vol.32Issue(4)：34-36,120,4.DOI:10.3969/j.issn.1006-1335.2012.04.008
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
摘要
Abstract
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Key words
vibration and wave / unmanned helicopter / frame / structural dynamics / finite element modeling / modal testing分类
机械制造引用本文复制引用
谢勤伟,姜年朝,周光明,张逊,王克选,张志清..某无人直升机机身框架动力学计算与试验研究[J].噪声与振动控制,2012,32(4):34-36,120,4.基金项目
国家自然科学基金(10772079) （10772079）
