火箭冲压发动机无喷管助推器分析  

Analysis on Nozzleless Booster of Rocket Ramjet Engine

作　　者：曹任刚[1] 郭颜红[1] 

机构地区：[1]中国空空导弹研究院,河南洛阳471009

出　　处：《战术导弹技术》2011年第3期48-53,共6页Tactical Missile Technology

摘　　要：介绍了无喷管固体火箭发动机性能计算的基本架设、控制方程和装药燃速的处理,对影响无喷管助推器性能设计的火箭冲压发动机主要要求、影响进行了分析,围绕装药长度、冲压喷管尺寸、推力要求等设计约束条件对无喷管助推器设计的影响进行了分析与计算,给出定量计算结果和研究结论.同时,介绍了一种提高火箭冲压发动机无喷管助推器性能的新方法、新方案:冲压喷管共用结构方案.The basic structure, control equation performances of nozzleless solid rocket motor are and charge combustion speed processing in calculating presented. According to nozzleless booster design, the relative requirement for rocket.-ramiet engine is analyzed. The constraints on nozzleless booster design are analyzed and calculated, including charge capacity, ramjet nozzle size, thrust etc, to obtain a quantitative result and research conclusion. A shared ramjet-nozzle structure is proposed as a new concept for improving performances of nozzleless booster of rocket-ramjet engine

关 键 词：助推器 无喷管火箭发动机 火箭冲压发动机 

分 类 号：V43[航空宇航科学与技术—航空宇航推进理论与工程]