作　　者： ; ; ;

机构地区： 北京工业大学机械工程与应用电子技术学院

出　　处： 《动力学与控制学报》 2015年第3期230-234,共5页

摘　　要： 折叠翼是可变体飞行器设计最有前景的方案之一.在折叠变形过程中,飞行器的气动特性以及振动特性将会发生变化.为了研究折叠翼可变体飞行器机翼的振动特性,本文设计制作了折叠板结构,介绍了建立复杂结构力学模型的方法,用力学实验得到用于离散折叠板结构的低阶模态,并且考察了系统可能存在的内共振频率. The folding wing is one of the most promising plans for designing a morphing aircraft. The aerodynam- ic and oscillatory characteristics of the aircraft will change as its wings fold. In order to investigate the vibration of the folding wings of a morphing aircraft, a structure with folding plates was designed and made. A method for constructing mechanical models for complicated structures was introduced. Mode shapes of low frequencies were experimentally obtained to discretize the structure with folding plates. And possible internal resonant frequencies of the system were studied.

关 键 词： 折叠翼 频率 模态 实验

领　　域： [兵器科学与技术]