Numerical simulation of combustion chamber and nozzle flow in classical hybrid rocket motors

被引：0

作者：

Tian, Hui ^{[1
]}

Cai, Guo-Biao ^{[1
]}

Wang, Hui-Yu ^{[1
]}

Zhang, Zhen-Peng ^{[1
]}

机构：

[1] College of Astronautics, Beijing University of Aeronautics and Astronautics, Beijing 100083, China

来源：

Yuhang Xuebao/Journal of Astronautics | 2006年 / 27卷 / 02期

关键词：

Chemical reactions - Combustion chambers - Mathematical models - Navier Stokes equations - Nozzles - Numerical methods - Temperature distribution;

D O I：

暂无

中图分类号：

学科分类号：

摘要：

In a typical hybrid, the fuel is a solid and the oxidizer is a liquid. A combustion and flow characteristic is the key problem in a hybrid rocket motor. Making research on computation of a combustion chamber and nozzle flow of a hybrid rocket motor is necessary. Numerical solutions of full Navier-Stokes equations with chemical reaction flow were obtained for of the LOX/HT-PB hybrid rocket motor. Lower-Upper decomposition scheme and MUSCL-type and VanLeer approach were used. One step chemistry model and two steps chemistry model were adopted. The combustion chamber and the nozzle flow under oxidizer velocity and combustion pressure were calculated. The better chemistry model was chosen by the result, which will be useful for the hybrid rocket motor design.

引用

页码：281 / 285