小型旋转固体火箭发动机工作性能研究  

Research on Working Performance of Small Spinning Solid Rocket Motor

作　　者：杨伟苓[1] 王在成[1] 姜春兰[1] 李明[1] 

机构地区：[1]北京理工大学爆炸科学与技术国家重点实验室,北京100081

出　　处：《高压物理学报》2013年第3期379-384,共6页Chinese Journal of High Pressure Physics

摘　　要：通过建立考虑侵蚀燃烧效应的固体火箭发动机内弹道模型,计算发动机内弹道压力时间曲线,将此压力数据作为初始压力输入值,利用FLUENT仿真软件对带有平直段的喷管内的流场进行仿真计算,确定喷管是否实现超音速流场。最后进行小型旋转固体火箭发动机静态和动态性能测试,测试结果表明,发动机转速达到19 000r/min,满足工作需要。The small spinning solid rocket motor was employed to perform as the power of the radial twice throwing system. Interior ballistic model of spinning solid rocket motor, in which eroding burn effect was considered, was established. The calculated pressure-time curve was set as initial pressure value for subsequent simulations. Fluid field of nozzle with straight segment was simulatated by software of Fluent, whether fluid field was supersonic or not can be identified. Finally static and dynamic tests of spinning solid rocket motor were performed. The tested results of spinning solid rocket motor indicate that spinning solid rocket motor works well at 19 000 r/min and meets the working need.

关 键 词：小型旋转固体发动机 内弹道 静态测试 动态测试 

分 类 号：TJ013.1[兵器科学与技术—兵器发射理论与技术]