飞机中央翼上壁板斜切单接头复合材料长桁端头压缩性能研究

玻璃钢/复合材料 ›› 2018, Vol. 0 ›› Issue (4): 27-31.

飞机中央翼上壁板斜切单接头复合材料长桁端头压缩性能研究

张明星

中国商飞上海飞机设计研究院,上海201210

收稿日期:2017-12-26 出版日期:2018-04-20 发布日期:2018-04-20
作者简介:张明星(1982-),男,博士,高级工程师,主要从事航空碳纤维增强复合材料方面的研究,schoolstar1982@163.com。

COMPRESSIVE PROPERTIES STUDIES ON ANGLE CUTTING AND SINGLE JOINT COMPOSITE STRINGER END OF AIRCRAFT CENTER WING

ZHANG Ming-xing

Shanghai Aircraft Design and Research Institute, Shanghai 201210, China

Received:2017-12-26 Online:2018-04-20 Published:2018-04-20

摘要/Abstract

摘要： 为研究飞机中央翼上壁板斜切单接头复合材料长桁端头的压缩性能,制作了中央翼斜切单接头长桁端头试验件,通过对试验件进行轴向压缩测试,建立了中央翼上壁板斜切单接头复合材料长桁端头区域的有限元模型,进行了试验前有限元分析计算,通过试验测得了整个试验件的载荷-应变曲线。试验结果表明,试验件发生非线性变形,然后随着载荷的增加,连接肋缘条、蒙皮、长桁的螺栓被剪断,紧固件连接失效,试验件被破坏。长桁蒙皮区域最大的应变出现在肋缘条和蒙皮连接的第一排钉附近,同时试验测得破坏载荷与有限元计算的结果总体一致,证明了有限元模型的合理性。

关键词: 中央翼, 上壁板, 压缩, 剪切, 非线性, 有限元分析

Abstract: Angle cutting and single joint stringer end samples of center wing were made and subjected to compression test. Load-strain curves under axial compression load were obtained. The results show that non-linear deformation appeared and under the increasing load, bolts connecting rib flange, skin and stringer were sheared and failed on connection. The largest strain appears on the the first row fastners on the rib flange and skin.

Key words: center wing, upper panel, compression, shear, non-linear, FEA

中图分类号:

TB332

张明星. 飞机中央翼上壁板斜切单接头复合材料长桁端头压缩性能研究[J]. 玻璃钢/复合材料, 2018, 0(4): 27-31.

ZHANG Ming-xing. COMPRESSIVE PROPERTIES STUDIES ON ANGLE CUTTING AND SINGLE JOINT COMPOSITE STRINGER END OF AIRCRAFT CENTER WING[J]. Fiber Reinforced Plastics/Composites, 2018, 0(4): 27-31.

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