Quasi-1D Analysis Model of Rocket Ejector Mode
- Paper number
IAC-06-C4.5.03
- Author
Mr. Lu Xiang, Northwestern Polytechnical University, China
- Coauthor
Prof. Guoqiang He, Northwestern Polytechnical University, China
- Coauthor
Prof. Pei-Jing Liu, Northwestern Polytechnical University, China
- Year
2006
- Abstract
The Rocket Based Combined Cycle (RBCC), which combines the advantages of both traditional rocket and air-breathing engine, with higher specific impulse (Isp) and thrust to weight ratio (T/W), should be the potential alternative for the next generation reusable launch vehicle. As the first operation mode of RBCC, Rocket Ejector mode has a heavy impact on the performance of full operation range, which should be considered carefully. A performance analysis model of Rocket Ejector mode was established, based on quasi-1D transient flow equations, factors such as skin friction, finite rate chemical reaction and mass injection were taken into account. A time marching MacCormack scheme with prediction-correction methods was adopted for solving the equations, which can obtain by-pass ratio correctly and well consider the ambient pressure. A Operator-Splitting method helped to decouple the stiff between flow equations and chemical reaction source, while a Quasi-Steady-State (QSS) solver for the stiff Ordinary Differential Equations (ODEs) of reaction kinetics was taken. Effect of mixing region between primary and secondary flow on the performance of rocket ejector was studied. Validation with experiments was taken out, which shows that the relative errors are less than 9
- Abstract document