首页 | 本学科首页   官方微博 | 高级检索  
     检索      

基于高温树脂传递模塑工艺的碳纤维/聚酰亚胺复合材料连接环制备与验证
引用本文:罗楚养,江晟达,陈梦熊,张朋,夏旭峰,蔡培培.基于高温树脂传递模塑工艺的碳纤维/聚酰亚胺复合材料连接环制备与验证[J].航空学报,2021,42(7):625438-625438.
作者姓名:罗楚养  江晟达  陈梦熊  张朋  夏旭峰  蔡培培
作者单位:东华大学民用航空复合材料协同创新中心,上海 201620;中国空空导弹研究院,洛阳 471009;东华大学民用航空复合材料协同创新中心,上海 201620;航空工业复合材料技术中心先进复合材料重点实验室,北京 101300;中国空空导弹研究院,洛阳 471009
基金项目:航空科学基金(20180112008);青年人才托举工程(2016QNRC001);上海市科技创新行动计划(19DZ1100300)
摘    要:根据连接环的结构特点,结合复合材料的力学特性及成型工艺要求设计了一种隔热/承载一体的碳纤维增强聚酰亚胺复合材料连接环,采用高温树脂传递模塑成型(RTM)整体成型工艺制备了复合材料连接环样件。超声检测结果显示,连接环内部质量良好。常温静强试验结果表明,在150%使用载荷下,连接环能保持良好的结构完整性,其最大应变仅为-491.0 με,满足常温静强度设计要求。520℃严酷热载荷下的静热联合试验结果显示,连接环在118%使用载荷下发生根部连接螺钉断裂失效,连接环本体未出现明显残余变形和损伤,满足热强度设计要求。有限元分析结果显示,常温条件下复合材料连接环的应力危险点出现在孔边,破坏方式主要为孔边的挤压破坏和层间剪切失效,高温条件下复合材料连接环失效位置主要出现在其外侧隔热层及螺栓孔处,对结构承载能力影响较小。

关 键 词:聚酰亚胺复合材料  树脂传递模塑成型(RTM)  高速飞行器热结构  静热联合试验  有限元分析
收稿时间:2021-03-02
修稿时间:2021-04-06

Preparation and evaluation of carbon fiber/polyimide composite attaching collars based on high temperature resin transfer mould process
LUO Chuyang,JIANG Shengda,CHEN Mengxiong,ZHANG Peng,XIA Xufeng,CAI Peipei.Preparation and evaluation of carbon fiber/polyimide composite attaching collars based on high temperature resin transfer mould process[J].Acta Aeronautica et Astronautica Sinica,2021,42(7):625438-625438.
Authors:LUO Chuyang  JIANG Shengda  CHEN Mengxiong  ZHANG Peng  XIA Xufeng  CAI Peipei
Institution:1. Collaborative Innovation Center for Civil Aviation Composites, Donghua University, Shanghai 201620, China;2. China Airborne Missile Academy, Luoyang 471009, China;3. Science and Technology on Advanced Composites Laboratory, AVIC Composite Technology Center, Beijing 101300, China
Abstract:A carbon fiber/polyimide composite attaching collar was designed and manufactured by high temperature Resin Transfer Mould (RTM) process according to the structural characteristics of attaching collars and the mechanical properties and forming process requirements of composite materials. The ultrasonic inspection results showed the good internal quality of the composite attaching collar. The static strength test conducted at room temperature showed that the maximum strain of the composite attaching collar is -491.0 με, indicating that the composite attaching collar maintains structural integrity under 150% ot the design load and meets the static strength design requirements. The thermo-static mechanical coupling test results at the maximum service temperature of 520 ℃ revealed that the attaching collar failed under the limit load of 118% due to the rapture of the screws at the root. The finite element analysis showed that the maximum stress of the composite attaching collar at room temperature occurred at the edge of the holes, and the primary failure mode was crushing and interlaminar shear failure around the holes. In comparison, the primary damage of the composite attaching collar at high temperature appeared at the outer thermal protection layer and the holes, which has minor influence on the structure bearing.
Keywords:polyimide composite  Resin Transfer Molding (RTM)  thermal structure of high-speed aircraft  thermo-static mechanical coupling test  finite element analysis  
本文献已被 万方数据 等数据库收录!
点击此处可从《航空学报》浏览原始摘要信息
点击此处可从《航空学报》下载免费的PDF全文
设为首页 | 免责声明 | 关于勤云 | 加入收藏

Copyright©北京勤云科技发展有限公司  京ICP备09084417号