LIPS-200离子推力器热特性模拟分析研究 |
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引用本文: | 孙明明,张天平,陈娟娟,龙建飞. LIPS-200离子推力器热特性模拟分析研究[J]. 强激光与粒子束, 2014, 26(8): 084002. DOI: 10.11884/HPLPB201426.084002 |
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作者姓名: | 孙明明 张天平 陈娟娟 龙建飞 |
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作者单位: | 1.兰州空间技术物理研究所 真空低温技术与物理国家级重点实验室, 兰州 730000 |
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摘 要: | 为了对20cm口径LIPS-200环形会切磁场离子推力器的热设计研究提出优化建议,利用LIPS-200离子推力器内部放电能量沉积数学模型计算结果开展推力器的稳态和瞬态热分析,并进行热平衡试验加以验证。结果显示:当推力器处于稳态工作时,其内部磁钢的温度分布是影响推力器热设计的关键因素,而通过提高推力器内外部件的表面发射率,可以使内部关键部件温度降低50~60℃,相关热平衡试验验证结果与仿真分析结果基本吻合。
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关 键 词: | 离子推力器 热分析 温度分布 热设计优化 |
收稿时间: | 2014-03-13 |
Thermal analysis of LIPS-200 ion thruster |
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Affiliation: | 1.National Key Laboratory of Vacuum and Cryogenic Technology on Physics,Lanzhou Institute of Physics,Lanzhou 730000,China |
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Abstract: | In order to provide optimization suggestions for the thermal design study on the 20 cm diameter LIPS-200 ion thruster with ring-cusp magnetic field, steady-state and transient thermal analysis are performed utilizing the calculation results with the internal discharge energy deposition mathematical model of the LIPS-200 ion thruster. Thermal balance experiments are conducted to validate these results. The results indicate that the internal magnet is the key factor influencing the thermal design of the thruster as the thruster is in steady operation, while increasing the surface emissivity of the internal and external components of the thruster can reduce the temperature of the internal components effectively, roughly by the order of 50~60 ℃. The thermal balance experiment results is in agreement with the theoretical analysis results. |
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Keywords: | ion thruster thermal analysis temperature distribution thermal design optimization |
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