M40/648碳纤维环氧复合材料热循环效应研究  

Effect of thermal cycle on M40/648 carbon/epoxy composites

作　　者：秦玮[1] 杨艳斌[1] 张永泰[1] 于强[1] 翟睿琼[1] 姜海富[2] 柴丽华[3] 

机构地区：[1]北京卫星环境工程研究所,北京100094 [2]北京卫星环境工程研究所可靠性与环境工程技术重点实验室,北京100094 [3]北京工业大学材料学院,北京100124

出　　处：《航天器环境工程》2018年第1期82-86,共5页Spacecraft Environment Engineering

基　　金：总装预研基金项目(编号:9140A12030314HT05002)

摘　　要：空间热循环作用的耐受性是决定碳环氧复合材料在轨服役寿命的重要因素之一。文章以M40/648碳纤维环氧复合材料为研究对象,开展了热循环(温度区间:-150^+150℃)效应试验研究,分析了试验前后的材料质量损失率、层间剪切性能、微观形貌和表面成分的变化。结果显示:热循环作用后材料的质量损失率在0.04%~0.07%之间;200次热循环使材料层间剪切强度提高,而300次热循环导致材料层间剪切强度下降1.16%;热循环作用对材料断口形貌影响较大,同时造成材料表面碳元素含量降低。The tolerance of the space thermal cycle effect is one of the important factors that affect the service life of carbon/epoxy composite materials. This paper focuses on the effect of the thermal cycle on a kind of carbon/epoxy composite materials M40/648 （which is composed of M40 carbon fiber and 648 epoxy resin）. The temperature range is from -150 ℃ to ＋150 ℃. The mass loss rate, the interlaminar shear strength, the surface morphology and the composition are investigated. It is indicated that the thermal cycle can lead to a mass loss of 0.04%-0.07%. The interlaminar shear strength is increased in the case of 200 temperature cycles. In contrast, with 300 cycles, the interlaminar shear strength is decreased by 1.16%. The composite materials display an obvious change of the fracture morphology along with the decrease of the surface C element content.

关 键 词：复合材料 热循环 质量损失 层间剪切强度 

分 类 号：TH74[机械工程—光学工程] V416.8[机械工程—仪器科学与技术]