塞式喷管在固体火箭发动机上的应用研究  

Application study of plug nozzles for solid rocket motors

作　　者：王长辉[1] 刘宇[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1期36-39,56,共5页Journal of Solid Rocket Technology

基　　金：国家 863资助项目(863 2 3 4 10)。

摘　　要：针对固体火箭发动机要求,比较了 3种可能的环排塞式喷管结构形式,认为环排瓦状塞式喷管是目前最可行的方案。以高空工作的固体发动机喷管为例,设计了一个 8单元环排瓦状塞式喷管和与其对比用的钟形喷管,在相同尺寸限制条件下,塞式喷管的面积比大大高于钟形喷管。通过数值模拟的方法对设计的环排瓦状塞式喷管的流场和性能进行了研究,分析了不同反压下塞锥流场特点和塞锥表面的压强分布。计算结果表明,塞式喷管在设计点效率为 97. 41%时,其真空效率为78. 63%。这比对比用钟形喷管的一维理想真空效率高出近2. 0%。Three types of annular plug nozzles applied to solid rocket motors were compared and annular tile-shaped plug nozzle was considered to be practicable. Taking solid rocket motor nozzles working at high altitude as an example, an 8-unit annular plug nozzle and a bell-shaped nozzle were design. Under the same dimensional condition, the area ratio of plug nozzle is much larger than that of bell-shaped nozzle. Flow field and performance of tile-shaped plug nozzle were investigated by using numerical simulation method and flow field characteristics and pressure distribution along plug cone surface were analyzed. The results show that vacuum efficiency of annular plug nozzles is 78.63% when its efficiency of design point is 97.41%. Its vacuum efficiency is almost 2.0% higher than one dimensional desired vacuum efficiency of bell-shaped nozzle.

关 键 词：固体火箭发动机 塞式喷管 应用 发动机喷管 结构形式 数值模拟 压强分布 计算结果 设计 面积比 点效率 流场 真空 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程] V430