航空材料学报2012，Vol.32Issue(5)：97-102,6.DOI:10.3969/j.issn.1005-5053.2012.5.017
新型纤维金属混合层板结构的疲劳裂纹扩展与分层行为
Fatigue Crack Propagation and Delamination Behavior of Advanced Fiber Metal Hybrid Laminate
摘要
Abstract
To study damage tolerance behavior of one kind of advanced hybrid laminate, this article accomplished fatigue crack propagation test under R = 0. 1 or - 1 for two kinds of saw-cut length and two kinds of lay-up, compared and analyzed α-N data, obtained the delamination shape between each layers by etching the aluminium sheet. The result indicates that this advanced hybrid laminate obviously displays a better fatigue crack propagation property than aluminium sheet under R = 0. 1. The laminate with adhesive film around the prepreg performs a better fatigue crack propagation property than the laminate without adhesive film around the prepreg. The specimen with shorter saw-cut length shows a better fatigue crack propagation property than the specimen with longer saw-cut length for the bridging mechanism. Crack in central aluminium sheet is shorter than the others. The delamination shape between inner aluminium sheet and prepreg presents a triangle.关键词
新型混合层板/疲劳裂纹扩展/分层Key words
advanced hybrid laminate/ fatigue crack propagation/ delamination分类
航空航天引用本文复制引用
黄啸,刘建中..新型纤维金属混合层板结构的疲劳裂纹扩展与分层行为[J].航空材料学报,2012,32(5):97-102,6.
