Thermal Analysis of Lanthanum Hexaboride Hollow Cathode with Radiative Carbon Heater IEPC-2015-455 / ISTS-2015
Thermal Analysis of Lanthanum Hexaboride Hollow Cathode with Radiative Carbon Heater IEPC-2015-455 / ISTS-2015
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使用辐射碳加热器进行六硼化镧空心阴极的热分析 IEPC-2015-455 / ISTS-2015
DOI：
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发表时间：
2015
期刊：
影响因子：
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通讯作者：
I. Funaki
中科院分区：
文献类型：
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作者：
Y. Oshio;K. Kubota;Y. Ohkawa;Shinatora Cho;Hiroki Watanabe;I. Funaki
为了设计大功率电推进用的大电流空心阴极，对六硼化镧空心阴极进行了热分析。研制了一台50 A级空心阴极试验机，该试验机采用碳辐射加热器，与传统的碳辐射加热器相比，具有更好的抗热变形和抗腐蚀性能。使用辐射高温计测量假嵌件的温度，其总计超过1700 °C。基于实验结果，热分析模型被调整以再现结果。实验和数值计算结果表明，在455 W时，刀片的温度可达1500 °C。这表明，辐射加热器有足够的潜力，大电流空心阴极，但加热效率低于传统的直接加热加热器。对热平衡的讨论也为辐射加热器的性能改进提供了建议。Nomadium Do = Richardson-Dushman方程的温度修正系数J =电流k =玻尔兹曼常数L =插入长度T =温度1空间和宇航科学研究所研究员，ohshio.yuuya@ jaxa.jp。2航空技术研究所研究员，kkubota@chofu.jaxa.jp。3推进组副高级研究工程师，okawa. yasushi@jaxa.jp. 4航空工业研究所研究员，cho@chofu.jaxa.jp 5系统设计系助理教授，hwatanabe@tmu.ac.jp 6宇宙航行科学研究所副教授，funaki@isas.jaxa.jp。
The thermal analysis of a Lanthanum Hexaboride hollow cathode is conducted in order to design a high current hollow cathode for the high power electric propulsion. A 50 A class hollow cathode tester with a radiative carbon heater is manufactured, which is expected to have better robustness against thermal deformation or erosion than the conventional heaters. The temperature of a dummy insert is measured using the radiation pyrometer, which amounts to over 1700 °C. Based on the experimental results, the thermal analysis model is tuned to reproduce the results. The experimental and numerical results indicate that the temperature of the insert reaches 1500 °C at 455W. This suggests that the radiative heater has enough potential for the high current hollow cathode, whereas the heating efficiency is lower than conventional direct heating heater. The discussion on the heat balance also offers suggestion for the performance improvement of the radiative heater. Nomenclature Do = temperature-modified coefficient to the Richardson–Dushman equation J = current k = Boltzman’s constant L = insert length T = temperature 1 Research associate, Institute of Space and Astronautical Science, ohshio.yuuya@jaxa.jp. 2 Researcher, Institute of Aeronautical Technology, kkubota@chofu.jaxa.jp. 3 Associate Senior Research Engineer, Propulsion Group, okawa.yasushi@jaxa.jp. 4 Researcher, Institute of Aeronautical Technology, cho@chofu.jaxa.jp 5 Assistant professor, Department of System Design, hwatanabe@tmu.ac.jp. 6 Associate Professor, Institute of Space and Astronautical Science, funaki@isas.jaxa.jp.