来流马赫数对引射火箭引射量的影响研究  

Effects of incoming Mach number on secondary mass flow rate

作　　者：李强[1] 刘佩进[1] 李江[1] 何国强[1] 

机构地区：[1]西北工业大学航天学院,西安710072

出　　处：《固体火箭技术》2009年第3期254-257,共4页Journal of Solid Rocket Technology

摘　　要：研究引射火箭引射量随来流马赫数的变化关系，对引射量由火箭引射主导向冲压主导之间转换点的选取以及一次火箭的质量管理具有重要意义。采用数值分析和实验研究，探索了引射火箭引射量随来流马赫数的变化关系。结果表明，针对所采用的引射火箭发动机构型，引射量随来流马赫数变化的拐点约为Ma：1．3～1．5，当来流马赫数Ma〈1．3时，引射量由火箭引射主导，随来流马赫数的增加，引射量变化较缓慢；当来流马赫数Ma〉1．5时，引射量由冲压主导，随来流马赫数的增加，引射量迅速增加。The critical point from rocket eject mode to ramjet mode is critial to the theoretical and experimental investigation of rocket eject motor and the mass management of eject rocket. Numerical simulation and experimental study were both conducted to investigate the dependence of secondary air mass flow rate on the flight Mach number. The results show that for the eject rocket stud- ied,the critical point is about Ma = 1.3 - 1.5. The secondary mass flow rate increases gradually along with the increase of incoming Macb number when the Mach number is smalller than 1.3 ; while the the secondary mass flow rate increases rapidly with the increase of incoming Mach number when it is greater than 1.5.

关 键 词：引射火箭 来流马赫数 引射量 

分 类 号：V435.1[航空宇航科学与技术—航空宇航推进理论与工程]