基于非接触激振的机翼模型模态测试  

Modal Test for Wing Model based on non-Contact Excitation

作　　者：崔盼礼[1] 李晓东[1] 宋巧治 

机构地区：[1]中国飞机强度研究所,陕西西安710065

出　　处：《工程与试验》2016年第3期75-78,共4页Engineering and Test

摘　　要：在轻质试验件模态测试中采用非接触激振,可以有效避免常规模态测试中激振器动圈附加质量和附加刚度对结构动特性的影响,避免锤击法引起的连击、振型不连续和应力集中等现象。本文主要介绍了非接触激振力产生的原理,根据该原理设计了一套非接触激振设施,并在一轻型机翼模型的模态测试中进行了应用。结果表明,基于非接触激振,测试结果更加准确,对于轻质试验件及柔性飞机的模态测试具有一定的工程意义。In modal test,the non-contact exciting force is applied to lightweight structures,which can avoid the influence of added mass and added stiffness. Moreover,it can avoid the phenomenon of stress concentration and discontinuous vibration mode with hammer excitation. The basic principle of non-contact exciting force is introduced in the paper. According to the principle,a new device of implementing non-contact exciting force is developed,and the device is used in a wing model structure. The test results show the advantages of non-contact excitation.

关 键 词：非接触激振 模态测试 涡电流 

分 类 号：V216.24[航空宇航科学与技术—航空宇航推进理论与工程]