玻璃钢/复合材料 ›› 2017, Vol. 0 ›› Issue (7): 74-76.

• 应用研究 • 上一篇    下一篇

夹层结构预埋玻璃纤维板拉脱强度研究

娄程飞, 张金奎, 张 伟   

  1. 中航工业特种飞行器研究所,荆门448035
  • 收稿日期:2017-01-10 出版日期:2017-07-28 发布日期:2017-07-28
  • 作者简介:娄程飞(1985-),男, 主要从事飞机结构强度设计方面的研究,longteng6688@126.com。

STUDY ON PULL-OFF LOAD OF SANDWICH STRUCTURE EMBEDDED GLASS FIBRE BOARD

LOU Cheng-fei, ZHANG Jin-kui, ZHANG Wei   

  1. Avic Special Vehicle Research Institute, Jingmen Hubei 448035, China
  • Received:2017-01-10 Online:2017-07-28 Published:2017-07-28

摘要: 夹层结构在飞机复合材料结构中大量使用,其连接处力学性能影响飞机结构的完整性。采用玻璃纤维板G10-t0.25"预埋于碳纤维材料面板纸窝芯的夹层结构中,针对20 mm、30 mm、40 mm等不同预埋件直径,开展拉脱试验。试验结果表明:较典型金属后埋件结构,拉脱载荷有较大提高,随着预埋件直径的增加,拉脱载荷不断增加;当预埋件直径大于30 mm后,预埋件直径的增加对拉脱载荷的提高影响不大。

关键词: 复合材料, 夹层结构, 预埋件, 玻璃纤维板, 拉脱强度

Abstract: Sandwich structure is widely used in aircraft composite structures, and the mechanical properties of sandwich structures affect the integrity of aircraft structures. The test was carried out using glass fiber board G10-t0.25" embedded in carbon fiber material paper litter of core sandwich panel structure embedded parts, which have different diameters of 20 mm, 30 mm, and 40 mm. The results show that, compared with the typical metal post-embedded structure, the pull-off load is greatly improved. With the increase of embedded part diameter, the load of pull-off increases. However, the load of pull-off does not show significant change when the embedded part diameter is larger than 30 mm.

Key words: composites, sandwich structure, embedded part, glass fibre board, pull-off load

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