大型固体火箭发动机研制的关键技术  

Critical techniques in development of large-size solid rocket motors

作　　者：阮崇智[1] 

机构地区：[1]中国航天科技集团公司四院,西安710025

出　　处：《固体火箭技术》2005年第1期23-28,共6页Journal of Solid Rocket Technology

摘　　要：介绍了大型固体发动机推进技术的现状和发展趋势。研讨了发动机设计总体布局与各部件匹配及协调、优化设计、推进剂性能、装药燃烧室的界面脱粘、喷管热结构设计与材料、全轴摆动柔性接头喷管和鉴定阶段发动机性能逆运算等技术问题,并总结了多年的研制经验。The present status and progress trend of propulsion technique for large-size solid rocket motors was introduced and some technique questions of the large-size motor design were discussed, such as matching of system arrangement and various parts, design optimization, properties of propellant, interface debonding, thermal-structure design and material of nozzle, flexible bearing-gimbaled nozzle and inverse calculation of motor performances during the qualification phase. The experience of research and development in recent years was summarized.

关 键 词：固体火箭发动机 关键技术 固体发动机 发动机设计 推进剂性能 发动机性能 发展趋势 推进技术 总体布局 优化设计 界面脱粘 结构设计 柔性接头 研制经验 燃烧室 逆运算 喷管 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程] V435.12