固体火箭发动机预固化技术及其应用(英文)  

Pre-cure Technique and Its Applications for Solid Rocket Motors

作　　者：苏昌银[1] 张爱科[1] 

机构地区：[1]中国航天科技集团公司四院7416厂,西安710000

出　　处：《固体火箭技术》2004年第4期298-303,共6页Journal of Solid Rocket Technology

摘　　要：依据HTPB复合推进剂界面特性 ,提出改变固化反应温度与时间来调节交联程度 ,使系统的官能团逐步进行化学反应 ,形成化学键和氢键 ,改善了生成物的力学性能。论述了预固化技术和粘接模型。将其应用于固体发动机推进剂 衬层界面粘接、发动机装药成型和推进剂药柱修补技术 ,经地面热试车和飞行考核 ,以及试件的十年储存试验考核 ,性能可靠 。Based on interface properties of HTPB (hydroxy terminated polybutadiene propellant) propellant, the cross linking level is regulated through the temperature and time of cure reaction. The chemical reaction takes place gradually in remainder functional groups of the system to form chemical bonds and hydrogen bond, so as to improve the mechanical properties of the resultant. Pre-cure technique and bonding model are described in the paper. They can be used in propellant-liner bonding, propellant loading and integral repairing of the propellant grain of the solid rocket motor (SRM). These test results have been qualified by the successful static firing tests, flight tests of motors and storage tests of specimens for ten years. The performance of the motor meets the design requirements with good reproducibility.

关 键 词：固体火箭发动机 固体发动机 复合推进剂 推进剂药柱 热试车 HTPB 飞行 固化技术 固化反应 成型 

分 类 号：V512[航空宇航科学与技术—航空宇航推进理论与工程] V435