火箭推进

磁屏蔽能够有效减缓等离子体对霍尔推力器放电室壁面的腐蚀,是延长推力器寿命的有效途径,可以将霍尔推力器的寿命提高至满足长寿命航天任务要求的水平,有巨大的发展潜力。对磁屏蔽技术原理进行了分析,以口径120 mm的霍尔推力器为对象进行了磁场设计和验证实验。提出了一种壁面磁力线向阳极弯曲程度最大且与壁面尽量不相交的磁场构形,是该实验样机壁面磁力线等势程度最高的构形,10 h点火后磁屏蔽构形壁面腐蚀状况与传统构形壁面相比,全部壁面被沉积的黑色物质覆盖,显著减少了离子对放电室壁面的腐蚀。验证了该磁屏蔽磁场构形的显著效果,并对该磁屏蔽霍尔推力器的性能进行了初步研究,阳极流量62 sccm、放电电压300 V下的最优效率为54.23%,对应的羽流状态为“长筒状”。

Magnetic shielding can effectively reduce the erosion of plasma on the wall of Hall thruster discharge chamber.It is an effective way to prolong the life of the thruster, which can improve the life of Hall thruster to meet the requirements of long-life space missions.So it has great potential for development.In this paper, the principle of magnetic shielding technology was analyzed, and the magnetic field design and verification experiments were carried out for a 120 mm Hall thruster.A magnetic field configuration with the maximum bending degree of the near-wall magnetic line to the anode and the maximum disjunction with the wall was proposed, which is the configuration whose near-wall magnetic line is the highest isopotential in the experimental prototype.The erosion of the wall of the magnetic shielding configuration was compared with that of traditional configuration after 10 hours of ignition.The former is covered by deposited carbon powder, which shows that magnetic shielding can significantly reduce the ion erosion on the wall of the discharge chamber.The remarkable effect of the magnetic shielding field configuration was verified.Then the performance of the magnetic shielding Hall thruster was preliminarily studied.The optimum efficiency of the thruster is 54.23% at 62sccm anode flow and 300 V discharge voltage, which corresponds to plume state "long cylinder".

引言
1 磁屏蔽原理
2 磁屏蔽磁场仿真
3 磁屏蔽效果验证及性能分析
4 结论

图1 磁屏蔽与传统霍尔推力器壁面电磁场及放电特性比较<br/>Fig.1 Comparison of electromagnetic field and discharge characteristics near the wall between magnetic shielding and baseline configuration

图1 磁屏蔽与传统霍尔推力器壁面电磁场及放电特性比较
Fig.1 Comparison of electromagnetic field and discharge characteristics near the wall between magnetic shielding and baseline configuration

图2 传统磁场构形仿真结果<br/>Fig.2 Simulation results of baseline magnetic field configuration

图2 传统磁场构形仿真结果
Fig.2 Simulation results of baseline magnetic field configuration

图3 磁力线与出口壁面相交示意图<br/>Fig.3 Diagram of the intersection of the magneticflux line with the exit wall

图3 磁力线与出口壁面相交示意图
Fig.3 Diagram of the intersection of the magneticflux line with the exit wall

图4 磁屏蔽构形仿真结果<br/>Fig.4 Simulation results of magnetic shielding configuration

图4 磁屏蔽构形仿真结果
Fig.4 Simulation results of magnetic shielding configuration

图5 磁屏蔽与传统磁场构形放电室通道中心标准化磁场强度轴向分布<br/>Fig.5 Axial distribution of standardized magnetic field intensity along discharge chamber center of magnetic shielding and baseline configuration

图5 磁屏蔽与传统磁场构形放电室通道中心标准化磁场强度轴向分布
Fig.5 Axial distribution of standardized magnetic field intensity along discharge chamber center of magnetic shielding and baseline configuration

图6 霍尔推力器壁面溅射和碳沉积示意图<br/>Fig.6 Schematic diagram of sputtering and carbon deposition on Hall thruster wall

图6 霍尔推力器壁面溅射和碳沉积示意图
Fig.6 Schematic diagram of sputtering and carbon deposition on Hall thruster wall

图7 点火10 h后磁屏蔽与传统构形下的放电室壁面对比<br/>Fig.7 Comparison between walls of Hall thrusters with magnetic shielding and baseline configuration after 10 hours of operation

图7 点火10 h后磁屏蔽与传统构形下的放电室壁面对比
Fig.7 Comparison between walls of Hall thrusters with magnetic shielding and baseline configuration after 10 hours of operation

图8 略发散羽流<br/>Fig.8 Slightly divergent plumes

图8 略发散羽流
Fig.8 Slightly divergent plumes

图9 长筒状羽流
Fig.9 Long barrel plume

表1 磁屏蔽霍尔推力器300 V下性能随磁场强度的变化<br/>Tab.1 Performance of magnetic shielded Hall thruster at 300 V varies with magnetic field intensity

表1 磁屏蔽霍尔推力器300 V下性能随磁场强度的变化
Tab.1 Performance of magnetic shielded Hall thruster at 300 V varies with magnetic field intensity

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备注

引言

1 磁屏蔽原理

2 磁屏蔽磁场仿真

3 磁屏蔽效果验证及性能分析

4 结论

期刊信息