固体火箭发动机尾焰注水流场实验研究  

The Experimental Study on Flow Field of Solid Rocket Motor Plume Injected by Water

作　　者：姜毅[1] 周帆[1] 张学文[1] 

机构地区：[1]北京理工大学宇航学院,北京100081

出　　处：《弹箭与制导学报》2011年第3期151-153,156,共4页Journal of Projectiles,Rockets,Missiles and Guidance

摘　　要：为了减弱发动机燃气射流对发射装置的冲击和烧蚀作用,对固体火箭发动机尾焰的注水流场开展了实验研究。通过高速摄影和红外热像仪两种非接触式测量设备对无注水和注水两种状态下的流场进行了对比拍摄。对两种状态下的流型和温度场分布进行了对比分析和研究,得出了通过注水方式可以减少核心区长度和面积从而达到降低热冲击烧蚀效应的结论。In order to weaken the impact and ablation effect on the launcher by motor jet, an experimental study was developed on flow field of solid rocket motor plume injected by water. The films of flow fields were photographed and compared fewer than two conditions of no-water-injected and water-injected by two non-contact measuring devices of high-speed photography and infrared thermograph. The flow pattern and temperature distribution under two conditions were compared, analyzed and researched. It is concluded that the heat impact and ablation effect can be weakened, and the length and area of potential core has been reduced by water injection.

关 键 词：固体火箭发动机 燃气射流 注水 流型 温度场分布 

分 类 号：V433.9[航空宇航科学与技术—航空宇航推进理论与工程]