高温复合材料在空空导弹上的应用研究  

Application Research of High Temperature Composite on Airborne Missile

作　　者：罗楚养[1] 张朋[2] 李伟东[2] 蔡培培[1] 魏仲委[1] LUO Chuyang ZHANG Peng LI Weidong CAI Peipei WEI Zhongwei(China Airborne Missile Academy, Luoyang 471009, China AVlC Composite Corporation LTD., Key Laboratory of Advanced Composites, Beijing Institute of Aeronautical Materials, Beijing 100095, China)

机构地区：[1]中国空空导弹研究院,河南洛阳471099 [2]中航复合材料有限责任公司先进复合材料重点实验室北京航空材料研究院,北京100095

出　　处：《航空科学技术》2017年第1期19-24,共6页Aeronautical Science & Technology

基　　金：航空科学基金(2013ZA12001;20155212009)~~

摘　　要：针对空空导弹的服役环境及结构设计特点,指出高温与载荷联合作用下的复合材料损伤容限设计、失效准则、刚度退化模型及防热/承载一体化设计等空空导弹复合材料结构设计关键技术,简述了空空导弹用耐高温复合材料的发展现状,并成功研制了耐高温复合材料舵面和连接环这两种典型的空空导弹复合材料结构,突破了空空导弹耐高温复合材料结构防热/承载一体化设计与整体制备等关键技术。According to the service condition and structure characteristics of airborne missile, the key technologies of composite structure used on airborne missile such as the composite damage tolerance design, failure criteria, rigid reduction model and thermal-structural integrated design were proposed. The development status of high temperature composite used on airborne missile was introduced. Two typical composite structures of airborne missile namely high temperature composite rudder and connected ring were designed and manufacture via resin transfer moulding process. The thermal-structural integrated design and manufacturing technologies were broke through.

关 键 词：复合材料 空空导弹 舵面 聚酰亚胺 树脂传递模塑 

分 类 号：V261.94[航空宇航科学与技术—航空宇航制造工程] TB332[一般工业技术—材料科学与工程]