| N2O/HTPB固液火箭发动机喷管两相流计算 |
| |
| 引用本文： | 田辉,蔡国飙,孙再庸. N2O/HTPB固液火箭发动机喷管两相流计算[J]. 航空动力学报, 2008, 23(6): 1146-1150 |
| |
| 作者姓名： | 田辉 蔡国飙 孙再庸 |
| |
| 作者单位： | 1.北京航空航天大学 宇航学院, 北京 100083 |
| |
| 摘 要： | 利用二维轴对称N-S方程对选用氧化亚氮/丁羟基燃料推进剂的固液混合火箭发动机的喷管两相流进行了计算.计算采用MacCormack时间推进预报校正二步格式,采用了Baldwin-Lomax代数湍流模型和两相平衡流模型.计算了三种氧燃比下4个不同喷管的喷管流场参数,并计算了喷管性能,通过比较两相流和气相流的计算结果,分析了不同氧燃比和喷管形状对喷管性能的影响,认为固液火箭发动机的性能主要受氧燃比的影响,为固液混合火箭发动机的设计提供了依据.
|
| 关 键 词： | 固液混合火箭发动机 喷管 两相流 氧化亚氮 丁羟基燃料 |
| 收稿时间： | 2007-11-22 |
| 修稿时间： | 2008-04-11 |
Computation of nozzle two-phase flow in a N2O/HTPB hybrid rocket motor |
| |
| TIAN Hui,CAI Guo-biao and SUN Zai-yong. Computation of nozzle two-phase flow in a N2O/HTPB hybrid rocket motor[J]. Journal of Aerospace Power, 2008, 23(6): 1146-1150 |
| |
| Authors: | TIAN Hui CAI Guo-biao SUN Zai-yong |
| |
| Affiliation: | 1.School of Astronautlcs, Beijing University of Aeronautics and Astronautics, Beijing 100083, China2.The 41st Research Institute, The 6th Academy of China Aerospace Science and Industry Corporation, Hohhot 010010, China |
| |
| Abstract: | Numerical solutions of full Navier-Stokes equations were obtained for a nozzle two-phase flow of the nitrous oxide(N2O)/hydroxyl-terminated polybutadiene(HTPB) based fuels hybrid rocket motor.MacCormack decomposition scheme and B-L algebraic turbulence model and two-phase equilibrium flow model were used.The nozzle flow and performance under three oxidizer-to-fuel ratios and four nozzle types were calculated.Effect of oxidizer-to-fuel ratio and nozzle type on nozzle performance was analyzed from the two-phase and gas phase results.Vacuum specific impulse is bound up with oxidizer-to-fuel ratio.This paper will be useful for the hybrid rocket motor design. |
| |
| Keywords: | hybrid rocket motor nozzle two-phase flow N2O HTPB-based fuels |
| 本文献已被 CNKI 万方数据 等数据库收录！ |
| 点击此处可从《航空动力学报》浏览原始摘要信息 |
|
点击此处可从《航空动力学报》下载全文 |
