RBCC引射火箭模态二次燃烧实验  

Effect of secondary combustion in rocket ejector

作　　者：刘佩进[1] 何国强[1] 李宇飞[1] 

机构地区：[1]西北工业大学航天工程学院,陕西西安710072

出　　处：《推进技术》2004年第1期75-77,共3页Journal of Propulsion Technology

摘　　要：为了提高RBCC引射火箭模态的推力性能,探索热力壅塞对引射模态推力的影响,开展了二次燃烧实验研究。引射火箭采用二元支板结构,燃气发生器采用多个喷管以加强混合,二次燃料喷嘴为小流量直流自击式喷嘴。通过实验,获得了燃料的质量流率、燃料喷射位置和物理喉道面积对推力的影响。结果表明:合适的燃料流量和喷射位置可以在静态条件下产生推力增强。Secondary combustion was experimentally investigated to improve the thrust of rocket ejector mode of RBCC, and to find the influence of thermal choke on thrust. Rocket ejector with strut characteristic was adopted. Multi primary nozzle was used to enhance mixing and atomized-spray injector was used to obtain better spray. Mass flow rate of added fuel, injecting location and physical throat area on rocket ejector performance were investigated. The experimental results show that with the proper mass flow rate and injecting position of secondary fuel thrust augmentation can be obtained under static condition.

关 键 词：引射火箭 加力燃烧 燃料控制 喷管 推力 

分 类 号：V231.2[航空宇航科学与技术—航空宇航推进理论与工程]