环簇式塞式喷管在固体火箭发动机上应用探讨  

Application of annular clustered plug nozzle to solid rocket motor

作　　者：任军学[1] 刘宇[1] 覃粒子[1] 

机构地区：[1]北京航空航天大学宇航学院,北京100083

出　　处：《固体火箭技术》2005年第3期184-187,共4页Journal of Solid Rocket Technology

基　　金：国家自然科学基金资助项目(批准号:50476002)

摘　　要：对可应用于固体火箭发动机上的3种塞式喷管的结构特点进行了比较,重点讨论环簇式塞式喷管结构性能。基于目前的设计方法,确定了环簇式塞式喷管与钟形喷管的性能比较方法,进行了尺寸及重量分析,并给出了其在战略导弹第一级发动机和高空发动机的应用算例。结果表明,内喷管喉径是影响环簇式塞式喷管尺寸大小的最主要设计参数;在单元数足够多时,环簇式塞式喷管可比相同面积比的钟形喷管的尺寸更小,重量更轻,推力效率更高;明确了环簇式塞式喷管实际应用所需解决的关键问题。The structure characteristics of three types of plug nozzles applied to solid rocket motor were compared, and the structure properties of annular clustered plug nozzle were mainly discussed. Based on the current design method,the property comparison method of annular clustered plug nozzle and bell nozzle was defined ,the size and the weight of the annular clustered plug nozzle were analyzed, and the examples of the annular clustered plug nozzle applied to the first stage motor and the upper stage motor of strategic missile were given. The results show that throat diameter of the inner nozzle is the most important design parameter influencing structure size of the annular clustered plug nozzle. When numbers of the inner nozzle are enough, plug nozzle has less size, less weight and higher thrust efficiency than the bell nozzle under same area ratio. Finally, the key techniques of the annular clustered plug nozzle were indicated.

关 键 词：塞式喷管 固体火箭发动机 性能增益 

分 类 号：V435.23[航空宇航科学与技术—航空宇航推进理论与工程]