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。
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.
作者
张绪
汪厚冰
于振波
胡海威
ZHANG Xu;WANG Hou-bing;YU Zhen-bo;HU Hai-wei(Shanghai Aircraft Design and Research Institute, Shanghai 201210, China;Aircraft Strength Research Institute of China, Xi′an 710065, China)
出处
《玻璃钢／复合材料》
CAS
北大核心
2019年第7期85-91,共7页
Fiber Reinforced Plastics/Composites
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
carbon fiber reinforced plastic (CFRP)
fuselage panel
mechanically fastening
stress analysis
verification test
