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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%。
Abstract: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%.
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Key words:
- blast shock wave /
- impact damage /
- wing /
- modal /
- numerical simulation
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图 3 不同强度冲击波作用后机翼结构变形云图
Figure 3. Deformation cloud diagram of wing structure after shock waves of different intensities
图 4 变形量与TNT当量质量W、距离L的关系
Figure 4. Deformation versus TNT equivalent mass W and distance L
图 5 爆炸点正下方机翼蒙皮节点变形
Figure 5. Deformation of wing skin node directly below explosion point
图 6 冲击波作用在不同位置时机翼结构变形云图
Figure 6. Deformation cloud diagram of wing structure when shock wave acts on different positions
图 9 不同爆炸距离时机翼结构变形云图
Figure 9. Cloud diagram of wing structure deformation at different explosion distances
图 12 无冲击损伤条件下机翼前三阶模态响应
Figure 12. The first third-order modal response of wing without impact damage conditions
图 13 冲击损伤条件下机翼前三阶模态响应
Figure 13. The first third-order modal response of wing under impact damage conditions
图 15 频率相对偏差与爆炸点L/b的关系
Figure 15. Relative frequency deviation versus blow-up point L/b
参数 数值 密度ρ/(g·cm−3) 2.78 弹性模量E/GPa 73.083 泊松比μ 0.33 本构参数n 0.73 本构参数C 0.0083 本构参数m 1.7 本构参数Tm 775.00 本构参数Tr 300.00 本构参数A/MPa 369.00 本构参数B/MPa 648.00 失效参数D1，D2，D3，D4，D5 0.13，0.13，−1.5，0.011，0 
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表 2 无冲击损伤机翼固有频率
Table 2. Natural frequency of wing without impact damage
模态 固有频率/Hz 1 87.15 2 414.36 3 449.89
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