飞机典型结构模态测试优化激励方法的试验研究  

Experimental Research on Optimal Excitation Method for Modal Test of Typical Aircraft Structures

作　　者：付月 李坤 任建楠[1] 赵程 FU Yue;LI Kun;REN Jiannan;ZHAO Cheng(Shenyang Aircraft Corporation,Shenyang 110850,Liaoning,China;Liaoning Province Key Laboratory of Digital Twin for Aircraft Structural Strength,Shenyang 110850,Liaoning,China)

机构地区：[1]沈阳飞机工业(集团)有限公司,辽宁沈阳110850 [2]辽宁省飞行器结构强度数字孪生重点实验室,辽宁沈阳110850

出　　处：《工程与试验》2024年第4期32-33,49,共3页Engineering and Test

摘　　要：针对飞机典型结构,开展模态测试试验。飞机典型结构模型相对较小,试验过程中不同位置激振力产生的响应存在相互耦合,导致很难获取结构某些振型的纯模态。为避免上述情况发生,试验过程中采用3种不同的激励方法。通过改变激励点位置、激励方向和激振器与结构之间的连接方式,获取不同激励方法下的结构模态测试结果。比较测试结果可以得出,选择不同的激励方法,能够获取不同的纯模态振型,此结论对于进行试验方案的设计和完善具有一定的参考和指导意义。Modal tests are carried out for the typical aircraft structures.The model of typical aircraft structures is relatively small,and the responses generated by excitation force at different positions during the test are coupled with each other,which makes it difficult to obtain the pure modal of some structural vibration modes.In order to avoid the above situation,three different excitation methods are used during the test.The structural modal test results of different excitation methods are obtained by changing the position of excitation points,excitation direction and the connection mode between the exciter and the structure.Comparing the test results,a conclusion can be obtained that different excitation methods can obtain different pure modal shapes.This conclusion has certain reference and guiding significance for the design and improvement of the test scheme.

关 键 词：模态测试 激励方法 纯模态 试验研究 

分 类 号：V216.2[航空宇航科学与技术—航空宇航推进理论与工程]