5 A发射电流空心阴极热特性模拟分析
2024,46(5):159-167
代鹏
兰州空间技术物理研究所 真空技术与物理重点试验室, 甘肃 兰州 730000，daip2009@163.com,smmhappy@163.com
孙明明
兰州空间技术物理研究所 真空技术与物理重点试验室, 甘肃 兰州 730000，daip2009@163.com,smmhappy@163.com
耿海
兰州空间技术物理研究所 真空技术与物理重点试验室, 甘肃 兰州 730000
谷增杰
兰州空间技术物理研究所 真空技术与物理重点试验室, 甘肃 兰州 730000
王东升
兰州空间技术物理研究所 真空技术与物理重点试验室, 甘肃 兰州 730000
兰州空间技术物理研究所 真空技术与物理重点试验室, 甘肃 兰州 730000，daip2009@163.com,smmhappy@163.com
孙明明
兰州空间技术物理研究所 真空技术与物理重点试验室, 甘肃 兰州 730000，daip2009@163.com,smmhappy@163.com
耿海
兰州空间技术物理研究所 真空技术与物理重点试验室, 甘肃 兰州 730000
谷增杰
兰州空间技术物理研究所 真空技术与物理重点试验室, 甘肃 兰州 730000
王东升
兰州空间技术物理研究所 真空技术与物理重点试验室, 甘肃 兰州 730000
摘要：
采用有限元分析方法,建立了国产5 A空心阴极的热仿真模型,并进行了模型校验和典型工况下的温度场分析。结果显示:模型能够较好地反映空心阴极内部的能量传动过程,温度的仿真结果与试验比对误差小于5%；加热电流是造成空心阴极温度差异的主要原因；环境温度主要影响着空心阴极的外部部件温度,并且在太阳辐照影响时的高温环境更有利于推力器的启动；空心阴极加热且处于自持放电状态时,发射体温度在环境温度0 ℃和94 ℃下分别达到2 122 ℃和2 126 ℃,已接近发射体材料的耐温极限,因此空心阴极必须避免此极端使用工况。
采用有限元分析方法,建立了国产5 A空心阴极的热仿真模型,并进行了模型校验和典型工况下的温度场分析。结果显示:模型能够较好地反映空心阴极内部的能量传动过程,温度的仿真结果与试验比对误差小于5%；加热电流是造成空心阴极温度差异的主要原因；环境温度主要影响着空心阴极的外部部件温度,并且在太阳辐照影响时的高温环境更有利于推力器的启动；空心阴极加热且处于自持放电状态时,发射体温度在环境温度0 ℃和94 ℃下分别达到2 122 ℃和2 126 ℃,已接近发射体材料的耐温极限,因此空心阴极必须避免此极端使用工况。
基金项目：
国家自然科学基金资助项目(61901202)；甘肃省科技计划资助项目(21JR7RA744)
国家自然科学基金资助项目(61901202)；甘肃省科技计划资助项目(21JR7RA744)
Simulation analysis on the thermal characteristics of 5 A emission current hollow cathode
DAI Peng
National Key Laboratory of Science and Technology on Vacuum Technology & Physics, Lanzhou Institute of Physics, Lanzhou 730000, China,daip2009@163.com,smmhappy@163.com
SUN Mingming
National Key Laboratory of Science and Technology on Vacuum Technology & Physics, Lanzhou Institute of Physics, Lanzhou 730000, China,daip2009@163.com,smmhappy@163.com
GENG Hai
National Key Laboratory of Science and Technology on Vacuum Technology & Physics, Lanzhou Institute of Physics, Lanzhou 730000, China
GU Zengjie
National Key Laboratory of Science and Technology on Vacuum Technology & Physics, Lanzhou Institute of Physics, Lanzhou 730000, China
WANG Dongsheng
National Key Laboratory of Science and Technology on Vacuum Technology & Physics, Lanzhou Institute of Physics, Lanzhou 730000, China
National Key Laboratory of Science and Technology on Vacuum Technology & Physics, Lanzhou Institute of Physics, Lanzhou 730000, China,daip2009@163.com,smmhappy@163.com
SUN Mingming
National Key Laboratory of Science and Technology on Vacuum Technology & Physics, Lanzhou Institute of Physics, Lanzhou 730000, China,daip2009@163.com,smmhappy@163.com
GENG Hai
National Key Laboratory of Science and Technology on Vacuum Technology & Physics, Lanzhou Institute of Physics, Lanzhou 730000, China
GU Zengjie
National Key Laboratory of Science and Technology on Vacuum Technology & Physics, Lanzhou Institute of Physics, Lanzhou 730000, China
WANG Dongsheng
National Key Laboratory of Science and Technology on Vacuum Technology & Physics, Lanzhou Institute of Physics, Lanzhou 730000, China
Abstract：
A thermal simulation model of 5 A emission current hollow cathode was established by using finite element method, and the model verification and temperature analysis under typical working condition were investigated. The results show that the model can better reflect the energy transmission process inside the hollow cathode. The comparison error between the simulation results and the test results is less than 5%. The temperature difference of hollow cathode is mainly caused by heating current. The ambient temperature mainly affect the external components of hollow cathode, and the high ambient temperature under the influence of solar irradiation is more conducive to the start-up of the thruster. When the hollow cathode is heated and in self-sustaining discharge state, the temperature of the emitter reaches 2 122 ℃ and 2 126 ℃ at the ambient temperatures of 0 ℃ and 94 ℃, respectively, which is close to the temperature resistance limit of the emitter. Therefore, the hollow cathode must avoid the extreme condition.
A thermal simulation model of 5 A emission current hollow cathode was established by using finite element method, and the model verification and temperature analysis under typical working condition were investigated. The results show that the model can better reflect the energy transmission process inside the hollow cathode. The comparison error between the simulation results and the test results is less than 5%. The temperature difference of hollow cathode is mainly caused by heating current. The ambient temperature mainly affect the external components of hollow cathode, and the high ambient temperature under the influence of solar irradiation is more conducive to the start-up of the thruster. When the hollow cathode is heated and in self-sustaining discharge state, the temperature of the emitter reaches 2 122 ℃ and 2 126 ℃ at the ambient temperatures of 0 ℃ and 94 ℃, respectively, which is close to the temperature resistance limit of the emitter. Therefore, the hollow cathode must avoid the extreme condition.
收稿日期：
2022-05-26
2022-05-26
