固体燃料双燃烧室冲压发动机研究  

Study on Solid Propellant Dual Combustor Ramjet

作　　者：徐东来[1] 孙振华[1] 

机构地区：[1]中国空空导弹研究院,河南洛阳471009

出　　处：《弹箭与制导学报》2017年第3期67-70,共4页Journal of Projectiles,Rockets,Missiles and Guidance

摘　　要：双燃烧室冲压发动机是超燃冲压发动机研究的一个重要方向,有很高的应用价值。文中对一种固体燃料双燃烧室冲压发动机进行了性能计算和试验研究,分析了亚燃流道和超燃流道的部件特性和特征参数对发动机总体性能的影响。计算结果表明,在所研究的范围内,超燃流道主要影响发动机性能,亚燃流道主要作用是点火和稳定燃烧。开展了发动机地面试验,亚燃/超燃点火和燃烧组织稳定,验证了固体燃料双燃烧室发动机方案的可行性。As a significant alternative of supersonic ramjet, a kind of solid propellant dual combustor ramjet is investigated in this paper. The performance and characteristic parameters of subsonic duct and supersonic duct effects on the engine overall performance are analyzed through performance calculations and experiment As the calculation results illustrated, the supersonic duct dominates the ramjet perform- ance, while the subsonic duct is more important in ignition and steady combustion. According to the ground experiment, both subsonic and supersonic combustion was stably established, which means this scheme of solid propellant dual combustor ramjet is feasible.

关 键 词：冲压发动机 双燃烧室 超声速燃烧 固体燃料 径向布局 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]