基于应变响应贡献度的细长体翼面结构振动试验方法  

Vibration Test Method of Slender Wing Structure Using Strain Response Contribution

作　　者：王龙[1] 张治君[1] 何石[1] WANG Long;ZHANG Zhi-jun;HE Shi(Aircraft Strength Research Institute,Xi an 710065,China)

机构地区：[1]中国飞机强度研究所,西安710065

出　　处：《科学技术与工程》2018年第18期1-6,共6页Science Technology and Engineering

摘　　要：针对典型细长体翼面结构的特点,采用单振动台激振、柔性夹具及多点平均响应控制的方法进行振动疲劳试验:通过对试件进行振动载荷虚拟加载,确定目标模态;设计柔性夹具对其进行柔性支持,使试件在柔性夹具支持下共振频率、振型与目标模态一致;通过虚拟加载的方法,研究试件翼面加速度响应,选取加速度响应较大的两个点和较小的两个点进行四点平均,控制振动台的载荷加载。试验结果表明:通过本文方法设计的柔性夹具在振动试验中使试件复现了目标模态;通过虚拟加载方法在试件翼面确定了四个控制点进行平均控制,精确控制了试验载荷加载。In order to carry out the vibration test of one typical slender wing structure,a single shaker was used for loading the vibration loads,a flexible fixture was also designed to support the structure,which can simulate the supporting stiffness,besides,the average acceleration response of the multiple points was used as the signal of loading control system.Through the virtual vibration loading in the software,the modes in which the relatively large strain responses occur were chosen as the target modes.In the other hand,the flexible fixture was optimized to achieve the design goal,that the first few modes of structure fixed on flexible fixture was similar to the target modes.Through the studying of acceleration response of structure s wing surface when the vibration load was virtually loaded,two points with larger acceleration response and two points with smaller acceleration response were selected as the control points.At last,the test completes successfully,and the test result shows that the flexible fixture achieves the design goal,the vibration loads is also accurately loaded.

关 键 词：细长体翼面结构 柔性夹具 虚拟加载 多点平均 响应控制 

分 类 号：O324[理学—一般力学与力学基础] V216.21[理学—力学]