航天推进技术研究院主办
[1]谢泽华,周 进,李自然.脉冲等离子体推力器内部流场的数值分析[J].火箭推进,2014,40(01):39-44.
XIE Ze-hua,ZHOU Jin,LI Zi-ran.Numerical analysis of inner flow field of pulsed plasma thruster[J].Journal of Rocket Propulsion,2014,40(01):39-44.
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XIE Ze-hua,ZHOU Jin,LI Zi-ran.Numerical analysis of inner flow field of pulsed plasma thruster[J].Journal of Rocket Propulsion,2014,40(01):39-44.
脉冲等离子体推力器内部流场的数值分析
《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]
卷:
40
期数:
2014年01期
页码:
39-44
栏目:
研究与设计
出版日期:
2014-02-28
- Title:
- Numerical analysis of inner flow field of pulsed plasma thruster
- 分类号:
- V439+.2
- 文献标志码:
- A
- 摘要:
- 应用所建立的广义拉格朗日乘子形式的磁流体力学模型对平行电极型脉冲等离子体推力器的内部流场进行了数值研究。对等离子体流动过程的分析表明，放电初期等离子体在很强的电磁力作用下高速喷出推力器，而到放电后期等离子体受到的气动力比电磁力大得多，等离子体的运动非常缓慢。电磁冲量占推力器元冲量的大部分，增强电磁加速作用可以进一步提高推力器的性能。
- Abstract:
- A magnetohydrodynamics model in the form of the generalized Lagrange multiplier was adopted to simulate the inner flow field of a pulsed plasma thruster with rectangular geometry. Analyses on the flow process of plasma show that the plasma is accelerated to a high velocity to eject from the electrode channel under the strong electromagnetic acceleration in the beginning of the discharge. By contrast with this, the plasma moves downstream slowly in the later period of the discharge when aerodynamic force instead of electromagnetic force dominates the acceleration process. It indicates that the electromagnetic impulse accounts for the majority of the impulse bit of the thruster, and that the performance of this kind of thruster would benefit from the enhancement of electromagnetic acceleration effects.
参考文献/References:
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相似文献/References:
[1]杨乐,李自然,尹乐,等.脉冲等离子体推力器研究综述[J].火箭推进,2006,32(02):32.
Yang Le,Li Ziran,Yin Le,et al.Review of pulsed plasma thruster[J].Journal of Rocket Propulsion,2006,32(01):32.
[2]吴汉基,蒋远大,张志远,等.微小卫星的在轨推进技术[J].火箭推进,2006,32(03):40.
Wu Hanji,Jiang Yuanda,Zhang Zhiyuan,et al.On-board propulsion technologies for micro/minisatellites[J].Journal of Rocket Propulsion,2006,32(01):40.
备注/Memo
收稿日期：2013-09-02；修回日期：2013-11-01 基金项目：国家自然科学基金资助项目（11172327） 作者简介：谢泽华（1984—），男，博士研究生，研究领域为先进火箭推进技术与工程
更新日期/Last Update:
1900-01-01