爆炸冲击波作用后变形机翼模态数值模拟  

Numerical simulation of deformed airfoil modal after blast shock wave

作　　者：肖良丰 周兰伟 李向东[1] XIAO Liangfeng;ZHOU Lanwei;LI Xiangdong(School of Mechanical Engineering,Nanjing University of Science and Technology,Nanjing 210094,China)

机构地区：[1]南京理工大学机械工程学院,南京210094

出　　处：《北京航空航天大学学报》2024年第1期341-349,共9页Journal of Beijing University of Aeronautics and Astronautics

摘　　要：为研究典型机翼在爆炸冲击波作用下的毁伤效应及其损伤后的结构动力学特性,基于有限元方法,研究了爆炸当量、爆炸方位及爆炸距离等对典型机翼损伤程度的影响,并分析了机翼结构变形程度与模态的关系。研究结果表明:冲击波强度和作用位置的变化对机翼结构的损伤及模态频率会产生不同程度的影响;随着冲击波强度的增加,机翼结构越早产生变形,对应的各阶模态频率下降越大,其中,二阶频率最大减少了15.02%;爆炸点位于机翼中心正上方时,机翼的变形最大;与无损伤机翼模态固有频率相比,爆炸冲击波作用在机翼中心位置时,各阶模态频率减小幅度最大,减少幅度为8.29%~15.02%。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%.

关 键 词：爆炸冲击波 冲击损伤 机翼 模态 数值仿真 

分 类 号：V214.11[航空宇航科学与技术—航空宇航推进理论与工程] TP391.9[自动化与计算机技术—计算机应用技术]