某飞机机翼颤振模型模态测试及分析  

Mode tests and analysis of a wing flutter model

作　　者：秦锦 赵冬强[1] 龚亮[1] 王培勇 Qin Jin;Zhao Dongqiang;Gong Liang;Wang Peiyong(The First Aircraft Institute,710089,Xi’an,China)

机构地区：[1]第一飞机设计研究院,西安710089

出　　处：《应用力学学报》2020年第5期1882-1886,I0003,共6页Chinese Journal of Applied Mechanics

摘　　要：以某飞机机翼颤振缩比模型为研究对象,通过纯模态测试得到试验件前九阶模态参数。建立机翼梁架有限元模型并进行计算,得到各阶模态振型及频率。将各阶模态的计算结果与试验结果进行对比,频率的计算结果与纯模态试验值的误差均在5%以内,主要模态的振型计算结果与试验结果也基本一致,验证了有限元计算模型的准确性。在此基础上可以进行下一步的颤振分析,且试验结果可以作为机翼颤振模型风洞试验的参考依据。The normal mode tests of a wing flutter scale reduction model were implemented and modal parameters of its first nine modes were measured. The finite element model of the specimen is established and natural frequencies and modal shapes of each mode are obtained. Compared with the calculation results of each mode’s frequency, the maximum error of the test results is less than 5%, and the calculation results of each mode’s shape agree well with the test results. The accuracy of the finite element model is verified, based on that the flutter analysis could be further carried out, and the results of normal mode test provide a reference for wind tunnel test of the wing flutter model.

关 键 词：纯模态测试 模态分析 频率 振型 

分 类 号：O321[理学—一般力学与力学基础]