中国空间科学技术

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高模量碳环氧复合材料混合模式分层断裂研究

赵时熙,王波,陈焕春,林大庆,董艺,肖少伯   

  1. 北京航空航天大学,北京卫星制造厂
  • 发布日期:1998-10-25

MIXED MODE INTERLAMINAR FRACTURE OF HIGH MODULUS CARBON EPOXY COMPOSITES

Zhao Shixi Wang Bo Chen Huanchun (Beijing University of Aeronautics and Astronautics,Beijing 100083) Lin Daqing Dong Yi Xiao Shaobai (Beijing Spacecrafts,Beijing 100080)   

  • Published:1998-10-25
  • Supported by:
    航空科学基金,北京市复合材料技术重点实验室资助项目

摘要： 研究了两种高模量碳纤维环氧复合材料（ＨＭ／４２１１和ＨＭ／ＴＤＥ８６）的Ⅰ型、Ⅱ型和混合型分层断裂行为。在研究中进行了双悬臂梁（ＤＣＢ）试验、端边切口（ＥＮＦ）试验和混合模式弯曲（ＭＭＢ）试验，以确定此两种复合材料的层间断裂韧性和混合模式断裂曲线。这项研究获得的数据和结果对于航天结构应用中的选材和工艺质量保证，以及对确定由这些材料制造的复合材料结构损伤容限分析用的设计许用值，都是很有用处的。

关键词: 层离, 断裂强度, 碳－环氧复合材料, 研究

Abstract: The interlaminar fracture behavior of two high modulus carbon/epoxy composites (HM/4211 and HM/TDE86) has been investigated in mode Ⅰ,mode Ⅱ and mixed mode.The double contilever beam (DCB) test,the end notched flexure (ENF) test and the mixed mode bending (MMB) test were conducted to determine the interlaminar fracture toughness and the failure locus in mixed mode for the two composites.The data and results obtained from this investigation are useful for material selection and quality assurance in space structure application,and furthermore,for establishing design allowable used in damage tolerance analyses of composite structures made of these materials.