某型飞机机翼前缘抗鸟撞结构设计与试验验证

任冀宾; 王斌; 王振; 刘军; 索涛; 李玉龙

doi:10.11883/bzycj-2017-0407

某型飞机机翼前缘抗鸟撞结构设计与试验验证

doi: 10.11883/bzycj-2017-0407

任冀宾^{1, 2,},
王斌²,
王振¹,
刘军¹,
索涛^1, ,,
李玉龙¹

1.
西北工业大学航空学院航空结构工程系, 陕西西安 710072
2.
航空工业第一飞机设计研究院, 陕西西安 710089

基金项目:

国家自然科学基金项目 11527803

国家自然科学基金项目 11522220

国家自然科学基金项目 11772268

国家自然科学基金项目 11372256

详细信息

作者简介:
任冀宾(1978-), 男, 硕士, 研究员, walker21@126.com

通讯作者:
索涛(1979-), 男, 博士, 教授, suotao@nwpu.edu.cn

中图分类号: O383;V214.6
计量
- 文章访问数: 6434
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- 被引次数: 0
出版历程
- 收稿日期: 2017-11-10
- 修回日期: 2018-03-27
- 刊出日期: 2019-02-05

Design and experimental verification of a wing leading edge structure

REN Jibin^{1, 2
,},
WANG Bin²,
WANG Zhen¹,
LIU Jun¹,
SUO Tao^{1
, ,},
LI Yulong¹

1.
Department of Aeronautical Structural Engineering, School of Aeronautics, Northwestern Polytechnical University, Xi'an 710072, Shaanxi, China
2.
AVIC The First Airplane Institute, Xi'an 710089, Shaanxi, China

摘要

摘要: 针对某型飞机机翼前缘抗鸟撞性能不满足适航要求的问题，采用"数值仿真-试验验证-再仿真"的研究思路，对该结构进行了抗鸟撞优化设计。首先，通过有限元数值仿真，分别对具有三角板结构和前墙结构的两种新型前缘结构抗鸟撞能力进行了分析。仿真结果表明：具有前墙结构的机翼前缘抗鸟撞能力优于原始结构和带三角板结构的机翼前缘；在鸟撞过程中，这种具有前墙结构的机翼前缘通过利用破损蒙皮继续变形吸能的方式提高了结构的抗鸟撞性能。基于此，对带前墙结构的机翼前缘进行了抗鸟撞试验，一方面验证了数值模拟方法的准确性，另一方面验证了前墙结构的抗鸟撞效果。最后，采用数值仿真方法对带前墙结构的机翼前缘结构进行了参数分析，得到了前缘蒙皮厚度和前墙厚度与结构抗鸟撞性能的关系，并基于结构承载和抗鸟撞能力的综合要求，确定了最终结构参数。分析表明，优化后的机翼前缘结构不仅满足抗鸟撞要求，而且实现结构减重30%。
- 机翼前缘 /
- 抗鸟撞设计 /
- 前墙结构 /
- 试验验证
Abstract: In order to improve the anti-bird strike performance of a wing leading edge to meet the airworthiness requirements, the simulation-test-simulation methodology was adopted for the optimization of the leading edge. Firstly, the anti-bird strike responses of two kinds of the new leading edges, with the triangular plate structure and the front wall structure, respectively, were investigated via finite element simulation. The simulation results show the anti-bird strike performance of the leading edge with the front wall structure is better than those of the leading edges with the original structure and the triangular plate structure. During the bird strike process, the front wall structure can utilize the damaged skin's deformation to absorb energy, thus leading to the improvement of the anti-bird strike performance of the leading edge. The experiment was then carried out to verify not only the accuracy of the numerical simulation method but also the ability of the front wall structure against bird strike. Then, the validated model was used to analyze the influence of the leading edge structural parameters. With the weight reduction of 30%, the optimized wing leading edge structure with the front wall achieved a good performance of anti-bird strike.
- wing leading edge /
- anti-bird strike design /
- front wall structure /
- experimental verification

HTML全文

图 1 鸟体SPH模型

Figure 1. The SPH model of the bird

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图 2 机翼前缘结构示意图

Figure 2. Schematic structure of the wing edge

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图 3 三角板结构

Figure 3. Schemactic structure of the angular plate

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图 4 三角板结构鸟撞后的形貌

Figure 4. The angular plate after bird strike

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图 5 鸟体姿态的变化

Figure 5. Change of the bird posture

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图 6 前墙结构

Figure 6. Schematic structure of the front wall

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图 7 前墙结构鸟撞后的形貌

Figure 7. The front wall after bird strike

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图 8 3种结构蒙皮能量的变化对比

Figure 8. Comparison of the skin's energy changes of the three structures

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图 9 带前墙结构中蒙皮和前墙能量的变化

Figure 9. Energy changes of the skin and front wall in the front-wall structure

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图 10 机翼前缘试验件

Figure 10. The test article of the wing edge structure

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图 11 试验装置

Figure 11. Experimental apparatus

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图 12 试验撞击过程与模拟结果对比

Figure 12. Comparison of the striking process between experiment and simulation

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图 13 试验测试应变与模拟结果对比

Figure 13. Comparison of strain between experiment and simulation

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图 14 试验件鸟撞后形貌图与模拟结果对比

Figure 14. Comparison of the structure after bird strike between experiment and simulation

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图 15 前墙最大位移和蒙皮吸能随蒙皮厚度的变化

Figure 15. Changes of the maximum displacement of the front wall and the energy absorbed by the skin with the thickness of the skin

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图 16 前墙厚度对其最大位移和吸收能量的影响

Figure 16. Influences of the thickness of the front-wall on the maximum diaplacement of the front-wall and the energy absorbed by the front-wall

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