首页|A global model for evaluating discharge characteristics and performance of hollow cathodes

A global model for evaluating discharge characteristics and performance of hollow cathodes

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Hollow cathode,with the highest plasma density,current density,and temperature,becomes one of the most important components in the electro-thruster system.As the electric-propulsion thruster performance is directly related to the ionization rate,reliability,and lifetime of the hollow cathode,this paper develops a global model to study the effects of discharge current,gas flow rate,and gas species on the discharge characteristics in the insert and orifice regions of the hollow cathode.The emitter wall temperatures of hollow cathodes predicted by the global model are compared with experimental results from NSTAR thruster neutralization cathodes,confirming the model's validity.The influence of hollow cathode emitter material and structure sizes on the plasma parameters in the internal regions was also evaluated.The simulation results show that there is an optimal matching relationship between the discharge current and gas flow rate to guarantee the maximum ionization rate.The optimal working region for the hollow cathode has been deter-mined under different energetic,regime and structural parameters.The global model established in this paper can quickly determine the key structure and operating parameters of hollow cathode at the design stage,and provide the theoretical basis for hollow cathode design and development.

Hollow cathodeGlobal modelElectric propulsionDischarge characteristicsOptimal matching relationship

Feng TIAN、Long MIAO、Qimeng XIA、Zhiwen WU、Ningfei WANG、Xiao HOU

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School of Aerospace Engineering,Beijing Institute of Technology,Beijing 100081,China

Chongqing Innovation Center,Beijing Institute of Technology,Chongqing 404100,China

National Natural Science Foundation of ChinaNational Natural Science Foundation of ChinaNational Natural Science Foundation of ChinaNational Key R&D Program of ChinaNational Key R&D Program of ChinaNational Key R&D Program of ChinaChina Postdoctoral Science FoundationChina Postdoctoral Science FoundationAdvanced Space Propulsion Laboratory of BICEBeijing Engineering Research Center of Efficient and Green Aerospace Propulsion Technology,China

U22B20120NSFC52202460NSFC521771282020YFC22011002021YFC22028042022YFB34035042021M6903922021TQ0036LabASP-2021-04

2024

10.1016/j.cja.2024.03.004

中国航空学报(英文版)
中国航空学会

中国航空学报(英文版)

CSTPCDEI
影响因子：0.847
ISSN：1000-9361
年,卷(期)：2024.37(9)
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