Numerical Simulation of a Low-power Hydrazine Arcjet Thruster
文献类型：会议论文
| 作者 | Wang HX ; Geng JY; Chen Xi; Pan WX(潘文霞)
|
| 出版日期 | 2012 |
| 会议名称 | 18TH INTERNATIONAL VACUUM CONGRESS (IVC-18) |
| 会议日期 | AUG 23-27, 2010 |
| 会议地点 | Beijing, PEOPLES R CHINA |
| 通讯作者邮箱 | whx@buaa.edu.cn |
| 关键词 | low-power arcjet plasma flow and heat transfer numerical modeling hydrazine |
| 卷号 | 32 |
| 页码 | 732-742 |
| 通讯作者 | Wang HX (reprint author), Beijing Univ Aeronaut & Astronaut, Sch Astronaut, Beijing 100191, Peoples R China. |
| 中文摘要 | A modeling study is conducted to investigate the plasma flow and heat transfer characteristics of low-power (kW class) arc-heated thrusters (arcjets) with 2:1 hydrogen/nitrogen to simulate decomposed hydrazine as the propellant. The all-speed SIMPLE algorithm is employed to solve the governing equations, which take into account the effects of compressibility, the Lorentz force and Joule heating, as well as the temperature- and pressure-dependence of the gas properties. Typical computed results about the temperature, velocity and Mach number distributions within arcjet thruster are presented for the case with arc current of 9 A and inlet stagnant pressure of 3.3×105 Pa to show the flow and heat transfer characteristics. It is found that the propellant is heated mainly in the near-cathode and constrictor region, with the highest plasma temperature appearing near the cathode tip, and the flow transition from the subsonic to supersonic regime occurs within the constrictor region. The effect of gas viscosity on the plasma flow within arcjet thruster is examined by an additional numerical test using artificially reduced values of gas viscosity. The test results show that the gas viscosity appreciably affects the plasma flow and the performance of the arcjet thruster for the cases with the hydrazine or hydrogen as the propellant. The integrated axial Lorentz force in the thruster nozzle is also calculated and compared with the thrust force of the arcjet thruster. It is found that the integrated axial Lorentz force is much smaller than the thrust force for the low-power arcjet thruster. Modeling results for the NASA 1-kW class arcjet thruster with simulated hydrazine as the propellant are found to be reasonably consistent with available experimental data. |
| 收录类别 | CPCI |
| 合作状况 | 国内 |
| 会议网址 | http://dx.doi.org/10.1016/j.phpro.2012.03.626 |
| 会议录 | Physics Procedia
 |
| 会议录出版者 | ELSEVIER SCIENCE BV |
| 学科主题 | 电磁流体力学和等离子体动力学 |
| 语种 | 英语 |
| ISSN号 | 1875-3892 |
| 源URL | [http://dspace.imech.ac.cn/handle/311007/43292]  |
| 专题 | 力学研究所_高温气体动力学国家重点实验室 |
| 推荐引用方式 GB/T 7714 | Wang HX,Geng JY,Chen Xi,et al. Numerical Simulation of a Low-power Hydrazine Arcjet Thruster[C]. 见:18TH INTERNATIONAL VACUUM CONGRESS (IVC-18). Beijing, PEOPLES R CHINA. AUG 23-27, 2010.http://dx.doi.org/10.1016/j.phpro.2012.03.626. |
入库方式： OAI收割
来源：力学研究所
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