爆炸载荷下飞机典型加筋结构毁伤特性

程帅; 刘文祥; 童念雪; 殷文骏; 师莹菊; 张德志

doi:10.11883/bzycj-2020-0077

爆炸载荷下飞机典型加筋结构毁伤特性

doi: 10.11883/bzycj-2020-0077

西北核技术研究所强动载与效应重点实验室，陕西西安 710024

详细信息

作者简介:
程　帅（1988－　），男，博士研究生，助理研究员，chengshuai@nint.ac.cn

通讯作者:
张德志（1973－　），男，博士，研究员，zhangdezhi@nint.ac.cn

中图分类号: O383.3
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- 被引次数: 0
出版历程
- 收稿日期: 2020-03-23
- 修回日期: 2020-09-17
- 刊出日期: 2021-01-05

Damage mechanism of typical stiffened aircraft structures under explosive loading

Laboratory of Intense Dynamic Loading and Effect, Northwest Institute of Nuclear Technology, Xi’an 710024, Shaanxi, China

摘要

摘要: 为了探讨爆炸载荷下飞机典型加筋结构的响应规律，开展了爆炸实验，获得了飞机典型结构表面的反射超压历程，加筋结构的应变、位移等结构响应数据。并结合实验结果建立了高置信度的有限元模型，研究了所选结构的变形分布规律和塑性毁伤特性。结果表明，对于本文中选取的飞机加筋结构，塑性变形除了会开始于常见的加强筋中点外，还会开始于加强筋与加强筋联结处、加强筋与外框联结处。这主要是受加筋板的双向拉伸变形和应力集中的影响。进一步总结了随冲击波正压时间增长，能够引发加筋结构塑性变形的有效冲量和反射超压峰值阈值。研究结果对飞机气动外形、抗爆能力设计具有重要意义。
- 飞机 /
- 加筋结构 /
- 塑性变形 /
- 触地爆炸 /
- 毁伤 /
- 爆炸载荷
Abstract: Explosion experiments were performed to explore the response law of typical stiffened skin structures of aircrafts under explosive loading. And in the experiments, the following data on the structural responses were obtained as the reflected overpressure history at the surface of the typical aircraft structure, the strain and displacement of the stiffened structure. By combining the experimental data, a finite element model at a high-confidence level was proposed to analyze the deformation distribution and plastical damage characteristics of the structure investigated in this paper. Results show that for the stiffened structure investigated in this paper, the plastical deformation can start commonly at the midpoints of stiffeners, stiffener-to-stiffener and stiffener-to-outer frame joints in addition. It is mainly due to biaxial tensile deformation and stress concentration in stiffeners. Furthermore, the effective impulse and the peak threshold of reflected overpressure which can cause plastic deformation of reinforced structures with the increase of positive pressure action time were summarized. The research results are of great significance in the aerodynamic design of an aircraft.
- aircraft /
- stiffened structure /
- plastic deformation /
- contact surface explosion /
- damage /
- explosive loading

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图 1 某飞机典型加筋蒙皮试件

Figure 1. A typical reinforced skin specimen of an aircraft

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图 2 实验现场布局及夹具

Figure 2. Experimental layout and fixtures

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图 3 加筋蒙皮试件夹具和压紧结构

Figure 3. Reinforced skin specimen fixture and compression structure

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图 4 实验和数值模拟得到的压力载荷历程

Figure 4. Pressure history curves obtained by experiment and numerical simulation

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图 5 钢板中心形成的炸坑

Figure 5. The crater formed at the center of the steel plate

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图 6 考虑夹具的有限元模型

Figure 6. A finite element model considering the response of fixtures

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图 7 应变实验数据与模拟结果的比较

Figure 7. Comparison of experimental data and simulated results for strain

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图 8 位移实验数据与数值模拟结果的比较

Figure 8. Comparison of experimental data and simulated results for displacement

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图 9 实验件等效应变云图模拟结果

Figure 9. Simulated effective strain contour in the specimen

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图 10 不同反射压力峰值下，最大变形随正压作用时间的变化

Figure 10. The maximum deformation varied with positive pressure action time at different reflected pressure peaks

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图 11 不同反射压力峰值下，最大变形随有效冲量的变化

Figure 11. The maximum deformation varied with effective impulse at different reflected pressure peaks

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表 1 试件各结构件的厚度

Table 1. Thicknesses of different structural parts of the specimen

结构部位厚度/mm

蒙皮 1.5
外框 1.2
横向加强筋 1.2
纵向加强筋 1.5

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参考文献(17)

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