摘要
随着复合材料结构在航空航天领域的应用日渐广泛,非主承力结构壁板趋向于采用高比刚度的泡沫夹层结构。采用缝合工艺虽能提高泡沫夹层结构的面外性能和层间性能,但对泡沫夹层结构其它性能的影响并不明晰。通过压缩稳定性试验对泡沫夹层结构的稳定性进行研究,夹层结构分别采用单向带面板和织物面板。研究对象包括未缝合泡沫夹层结构和不同缝合密度的缝合泡沫夹层结构。试验结果表明:缝合会降低泡沫夹层结构的稳定性,缝合密度增加时,泡沫夹层结构稳定性性能降低。
As composite material is getting more and more popular in aviation and aerospace fields, composite sandwich structure with foam core is tend to be adopted in nonprimary structure applications. While stitching across skins and core can reinforce the out-of-plane and interlaminar properties of foam-core composite sandwich structures, the other effects of stitching are not clear. Effect of stitch addition on the stability of foam-core composite sandwich structure is experimentally investigated. The face sheets of test specimens are made of two different materials, namely the unidirectional carbon fiber tape and the carbon fiber fabric. These composite sandwich test specimens, unstitched or stitched with different stitch densities, are studied using the compressive buckling test. It is found that stitching reduces the stability of foam-core composite sandwich structures and the stability of sandwich structure declines when the density of stitching increases.
出处
《应用力学学报》
CAS
CSCD
北大核心
2015年第2期299-303,357,共5页
Chinese Journal of Applied Mechanics
关键词
缝合
复合材料
泡沫夹层
稳定性
stitched,composite,foam core sandwich structure,stability.
作者简介
杨慧，女，1983年生，硕士，上海飞机设计研究院，工程师；研究方向——飞机结构设计。E-mail：yanghui@comac.cc
