摘要
M40J/环氧树脂复合材料具有高的比强度和高的比模量,热膨胀系数小,尺寸稳定性好,而且在真空条件下质损率低,是目前我国航天应用卫星结构的主要材料,本文对M40J/环氧树脂面板蜂窝夹层结构成型工艺进行了分析研究,同时对两种环氧树脂的几项性能进行了比对。
Carbon fiber M40J/epoxy composites are widely applied in aeropsace field as main material for satellite structure because of the properties with high specific strength and modulus,low coefficient of thermal expansion,good dimensional stability and low mass loss ratio in vacuum.The forming process of carbon fiber M40J/epoxy panel honeycomb sandwich structure is researched and analyzed,and the properties of two different resins are compared.
出处
《航空制造技术》
2009年第S1期75-78,共4页
Aeronautical Manufacturing Technology
关键词
复合材料
蜂窝夹层结构
成型工艺
Composites Honeycomb sandwich structure Forming process
