Numerical simulation of deformed airfoil modal after blast shock wave

被引：0
|
作者：
Xiao L. [1 ]
Zhou L. [1 ]
Li X. [1 ]
机构：
[1] School of Mechanical Engineering, Nanjing University of Science and Technology, Nanjing
来源：
Beijing Hangkong Hangtian Daxue Xuebao/Journal of Beijing University of Aeronautics and Astronautics | 2024年 / 50卷 / 01期
关键词：
blast shock wave; impact damage; modal; numerical simulation; wing;
D O I：
10.13700/j.bh.1001-5965.2022.0244
中图分类号：
学科分类号：
摘要：
The effects of explosive mass, blast azimuth, and blast distance on the degree of damage to typical airfoils were investigated using the finite element method in order to analyze the damaging effect of typical airfoils under the action of blast shock wave and its structural dynamics following damage. The relationship between the deformation and the model of the wing structure was analyzed. The findings indicate that the wing structure damage and the modal frequency will be affected to varying degrees by changes in shock wave strength and action position. The changes in the shock wave intensity and action position will have different degrees of influence on the damage to the wing structure and the modal frequency. As the shock wave intensity increases, the earlier the wing structure deforms, and the deformation becomes larger the corresponding modal frequencies of all orders also drop more quickly, of which the second-order frequency decreases by 15.02% at most. When the explosion point was located directly above the center of the wing, the deformation of the wing was greatest. When the shock wave acts on the center of the wing, with the modal natural frequency of the undamaged wing, the modal frequency of each order showed the largest reduction, ranging from 8.29% to 15.02%. © 2024 Beijing University of Aeronautics and Astronautics (BUAA). All rights reserved.
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页码：341 / 349
页数：8
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