喉栓式固体火箭发动机喷管性能影响研究  

Analysis for Nozzle Performance of Pintle Controllable Thrust Solid Rocket Motor

作　　者：李娟[1] 李江[1] 

机构地区：[1]西北工业大学航天学院,西安710072

出　　处：《弹箭与制导学报》2007年第3期154-157,160,共5页Journal of Projectiles,Rockets,Missiles and Guidance

摘　　要：对喉栓式固体火箭发动机内流场进行了稳态数值模拟,分析了喉栓头部型面、喉栓尺寸、喉栓位置对发动机性能的影响规律,结果表明发动机效率受喉栓头部型面、尺寸、位置等因素影响显著,所提供的结论可为喉栓式变推力固体火箭发动机的设计、试验及应用提供参考依据。Numerical simulation of the flow field inside pintle controlled solid rocket motor was performed. The effects of pintle contour shapes,pintle size and pintle position on motor performance are investigated. The results show that the influence of these factors on pintle nozzle efficncy are evident. The conclusion would be helpful for pintle controlled solid rocket motor design.experiment and application.

关 键 词：喉栓式固体火箭发动机 喷管效率 数值仿真 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]