复合材料机身壁板机械连接的强度分析与验证

玻璃钢/复合材料 ›› 2019, Vol. 0 ›› Issue (7): 85-91.

复合材料机身壁板机械连接的强度分析与验证

张绪¹, 汪厚冰², 于振波¹, 胡海威¹

1.上海飞机设计研究院,上海201210;
2.中国飞机强度研究所,西安710065

收稿日期:2018-09-25 出版日期:2019-07-25 发布日期:2019-07-28
作者简介:张绪(1986-),男,硕士,高级工程师,主要从事民用飞机复合材料结构强度设计方面的研究,345552710@qq.com。

STRESS ANALYSIS AND VERIFICATION TEST OF COMPOSITE FUSELAGE PANEL MECHANICALLY FASTENING

ZHANG Xu¹, WANG Hou-bing², YU Zhen-bo¹, HU Hai-wei¹

1.Shanghai Aircraft Design and Research Institute, Shanghai 201210, China;
2.Aircraft Strength Research Institute of China, Xi′an 710065, China

Received:2018-09-25 Online:2019-07-25 Published:2019-07-28

摘要/Abstract

摘要： 为了验证复合材料机身壁板机械连接设计及分析方法的合理性,设计了复合材料壁板纵向对缝连接零组件试验,并分别利用工程经验公式和有限元建模方法对试验件进行了强度分析。试验结果表明,复合材料壁板机械连接设计满足限制载荷和极限载荷设计要求,理论应变分布与试验应变分布一致,机械连接处紧固件传载比例与工程经验方法吻合,实际破坏载荷高于理论分析所预测的破坏载荷,表明强度分析方法合理且保守。

关键词: 碳纤维复合材料, 机身壁板, 机械连接, 强度分析, 试验验证

Abstract: A static test was designed to verify the composite fuselage panels mechanically-fastening design and analysis method. Stress analysis was carried out by experience formula and finite element modeling respectively. As shown by the test results, the mechanically fastening design can sustain the limited load and ultimate load. The theoretical strain complies with the test strain. Load ratio carried by the fasteners calculated by test data is in line with the experience data. The damage load level in the test was higher than the predicted level given by theoretical analysis, demonstrating that the selected method is rational and conservative.

Key words: carbon fiber reinforced plastic (CFRP), fuselage panel, mechanically fastening, stress analysis, verification test

中图分类号:

TB332

张绪, 汪厚冰, 于振波, 胡海威. 复合材料机身壁板机械连接的强度分析与验证[J]. 玻璃钢/复合材料, 2019, 0(7): 85-91.

ZHANG Xu, WANG Hou-bing, YU Zhen-bo, HU Hai-wei. STRESS ANALYSIS AND VERIFICATION TEST OF COMPOSITE FUSELAGE PANEL MECHANICALLY FASTENING[J]. Fiber Reinforced Plastics/Composites, 2019, 0(7): 85-91.

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