火箭推力室喷管内激波对RBCC性能影响分析  

Influences of shock wave in rocket nozzle on RBCC performance

作　　者：路媛媛[1] 张蒙正[1] 严俊峰[1] 

机构地区：[1]西安航天动力研究所,陕西西安710100

出　　处：《火箭推进》2013年第5期46-50,97,共6页Journal of Rocket Propulsion

基　　金：国家863项目(2010AA702308)

摘　　要：针对火箭基组合循环(RBCC)动力系统引射火箭喷管的工作状况,采用准一维方法,假设引射模态火箭推力室喷管内在某些条件下产生的激波为正激波,分析了正激波的存在条件及其对RBCC动力系统性能的影响。结果表明:引射火箭推力室室压越低或飞行器飞行马赫数越高,引射火箭喷管内越易产生正激波;火箭喷管正激波的产生对RBCC动力系统引射性能及比冲特性有一定影响。When the rocket works in some cases, shock wave may appear in rocket nozzle in RBCC engine. The shock wave is supposed to be a normal shock wave in the one-dimensional con- ceptual analysis model. The existence conditions and influences of the normal shock wave on perfor- mance of RBCC dynamical system were analyzed. The results indicate that the lower the total pres- sure is in rocket combustion chamber or the higher the flight Mach number is, the easier the normal shock wave appearances in the nozzle. The generation of the normal shock wave in rocket nozzle has a certain influence on the ejector performance of RBCC dynamical system.

关 键 词：RBCC 引射模态 火箭推力室喷管 正激波 

分 类 号：V434-34[航空宇航科学与技术—航空宇航推进理论与工程]