摘要
采用RFI工艺分别成型了648和5228A环氧树脂基复合材料层合板,其增强材料为碳纤维无屈曲织物,铺层方式为[(0,90)/(±45)]s;测试了两组层合板的拉伸性能、弯曲性能和层间剪切性能并做了比较分析;对破坏形式和机理进行了探讨。结果表明:5228A相对于648环氧树脂膜有较宽的低黏度区域,较长的凝胶时间;5228A与648层合板相比,拉伸强度高106%,拉伸模量、泊松比接近;弯曲强度高58%,弯曲模量高16%;层间剪切强度高62%。
Epoxy 648 and epoxy 5228A matrix laminates were formed by RFI process, which were reinforced by carbon fiber non-crimp fabric （NCF） and ply orientation was [ （0,90）/（ 45 ） ] s. Mechanical properties of two laminates, such as tensile properties, flexural properties, interlaminar shear properties, were tested and compared. The failure mode and mechanism were discussed. The results show that epoxy film 5228A has a wider range of low viscosity, longer gelation time, compared with epoxy film 648. Epoxy 5228A matrix laminate has 106% higher tensile strength, 58% higher flexural strength, 16% higher flexural modulus, and 62% higher ILSS than that of epoxy 648 matrix laminate. The tensile modulus and poisson＇ s ratio of them are similar.
出处
《宇航材料工艺》
CAS
CSCD
北大核心
2008年第2期69-71,共3页
Aerospace Materials & Technology
