摘要
研制出高韧性，耐湿热，工艺性好的基体树脂是复合材料扩大到飞机主受力构件应用的关键。５４０５双马来酰亚胺树脂正是基于这一目的而研制的，它以Ｎａｒｍｅｏ５２４５Ｃ作为参比对象，在保证１３０℃使用和良好工艺性的前题下，以突出高韧性为目标。本文研究该树脂浇铸体及碳纤维复合材料的韧性数据，结果表明，５４０５树脂具有良好的韧性，其韧性数据优于５２０８和５２４５，迭层板部分性能达到ＮＡＳＡＲＰ１１４２中规定的指标。
To develop resins matrix which have high damage tolerance, excellent wet hot performance and good processing characteristics is a Key requirement for the application of composites to aircraft primary structure. For this reason, we selected bismaleimide resin systems as an object of study and developed a modified bismaleimide resin (named as 5405) in 1991. Comparative target of 5405 resin is Narmco 5245C, its research objective is to have highest toughness under the cases of 130 ℃ using temperature and good processability. This paper studied toughness properties of 5405 resin casts and carbon fiber composities T300/5405. Following toughness properties were studied to evaluate 5405 resin:(1) tensile properties, impact strength and fracture surface energy of resin casts; (2) transverse tensile, transverse flextural, L T shear properties and interlaminar fracture toughness G ⅠC , G ⅡC of unidirectional fiber composites; (3) multi ply laminate toughness included in NASA RP 1142: Open hole tension (compression) strength, compressive strength after impact, edge delamination tension fracture toughness; (4) impact compression failure curve of typical laminates. The data show that 5405 matrix resin has higher toughness than Narmco 5245C and 5208, and most toughness properties of T300/5405 multi ply laminates are higher than the standard values in NASA RP 1142. As a result, T300/5405 composites could be used in aircraft primary structure.
出处
《高分子材料科学与工程》
EI
CAS
CSCD
北大核心
1997年第2期85-88,共4页
Polymer Materials Science & Engineering
关键词
马来酰亚胺树脂
碳纤维
复合材料
韧性
飞机
bismaleimide resin, carbon fiber composites, toughness properties, aircraft primary structure application
