COUPLED EFFECT OF TEMPERATURE AND DEGAS AND/OR MOISTURE DESORPTION ON STRENGTH OF ORGANIC COMPOSITES FOR SPACE STRUCTURAL COMPONENTS, AND DEVELOPPED RESIDUAL STRESSES

温度和脱气和/或水分解吸对空间结构部件有机复合材料强度的耦合影响以及产生的残余应力

基本信息

批准号：
12650070
负责人：
OZAWA Yoshihito
金额：
$ 2.37万
依托单位：
FUKUSHIMA UNIVERSITY
依托单位国家：
日本
项目类别：
Grant-in-Aid for Scientific Research (C)
财政年份：
2000
资助国家：
日本
起止时间：
2000 至 2001
项目状态：
已结题

项目摘要

In order to evaluate the strength and dimensional stability of fiber reinforced organic composites, especially carbon fiber reinforced plastics (CFRP), in the space environment, it is important to clarify the effects of temperature and vacuum condition on the mechanical behavior of CFRP and the microfractures.In this report, the tensile strength and Young's modulus of CFRP cross-ply laminates and short carbon fiber reinforced polyamide (SCFR-PI) composites are considered in the high vacuum condition 10^-4 Pa and the atmospheric condition at various temperatures. From the experimental results, the CFRP at low temperature 93K and 200K has smaller tensile strength than that at 298K in high vacuum condition. The strength of interfacial bonding between carbon fibers and the epoxy resin matrix becomes better in low temperature and high vacuum conditions. It is found that there exist the coupled effect of temperature and vacuum conditions on the tensile strength of CFRP cross-ply laminates and the microfractures.Even though tested at the same temperature 298 K, the SCFR-PI kept in high vacuum condition has higher tensile strength and equivalent Young's modulus than that in the atmospheric condition. The rule of mixture and the shear lag treatment can not be used to evaluate the strength and Young's modulus of SCFR-PI composites in high vacuum condition. The strengthening is attributed to the nonexistence of air around the specimens. In high vacuum condition, the matrix resin is shrank owing to the degas and/or moisture desorption from the matrix and from the interface between the matrix and fibers, and thus yield the residual stresses in the organic composites. The interfacial bonding strength between carbon fibers and the resin matrix becomes much better in high vacuum condition. The methods of characterizing them must be described for evaluation of SCFR-PI composites in space environment.

为了评估纤维增强有机复合材料的强度和尺寸稳定性，尤其是碳纤维增强塑料（CFRP），在太空环境中，重要的是要阐明温度和真空状况对CFRP机械行为的影响和微裂缝的机械行为的影响在这份报告中，在高真空状态10^-4 PA和在各种温度下的大气条件下，考虑了CFRP交叉层压板和短碳纤维增强聚酰胺（SCFR-PI）复合材料的拉伸强度和Young的模量。从实验结果中，低温93K和200K处的CFRP的拉伸强度比在高真空状态下的298K时具有较小的拉伸强度。在低温和高真空条件下，碳纤维和环氧树脂基质之间的界面键合的强度变得更好。发现存在温度和真空条件对CFRP交叉层压板和微裂纹的拉伸强度的耦合作用。尽管在相同的温度下进行了测试，但SCFR-PI保持高真空状态的SCFR-PI具有较高的拉伸性。在大气条件下，力量和等效的杨氏模量比。混合物和剪切滞后处理的规则不能用于评估在高真空条件下SCFR-PI复合材料的强度和Young的模量。加强归因于样品周围空气不存在。在高真空条件下，基质树脂由于基质和基质和纤维之间的界面的DEGA和/或水分解吸而缩减，因此产生了有机复合材料中的残留应力。在高真空状态下，碳纤维和树脂基质之间的界面粘结强度变得更好。必须描述表征它们的方法，以评估太空环境中的SCFR-PI复合材料。