低速条件下引射火箭实验研究  

An experimental investigation on rocket ejector at low speed

作　　者：刘佩进[1] 何国强[1] 陈剑[1] 黄生洪[1] 王国辉[1] 

机构地区：[1]西北工业大学航天工程学院,西安710072

出　　处：《固体火箭技术》2002年第1期69-72,共4页Journal of Solid Rocket Technology

摘　　要：开展了火箭基组合循环推进在引射阶段的实验系统设计。实验系统包括以支板为特征结构形式的引射火箭试验发动机、自由射流气路系统、燃料喷注系统和压强推力数据采集系统。以固体火箭发动机作为燃气发生器 ,成功的进行了静态海平面零马赫状态下引射模态实验 ,获得了相关实验数据。同时 ,对相应的几何结构做了数值模拟 ,数值计算结果与实验结果基本吻合。Experimental system of rocket based combined cycle(RBCC) ejector modal was designed. The system includes ejection rocket test motor with strut free jet gas supply system, liquid fuel injection system and data acquisition system. Using solid rocket as gas generator, the sea level static ejector modal experiment was conducted successfully, and relevant data was obtained. At the same time, numerical simulation was also used to the relevant geometrical structure and the numerical results agree well with the experimental data.

关 键 词：火箭基组合循环推进 空间运输动力系统 引射 实验 

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]