中国空间科学技术

中国空间科学技术 ›› 2018, Vol. 38 ›› Issue (5): 7-16.doi: 10.16708/j.cnki.1000.758X.2018.0051

• 研究探讨 • 上一篇    下一篇

霍尔推力器羽流对太阳翼的溅射影响规律

于博1,2,3，王宣1,3，余水淋1,3，康小录1,3，*   

  1. 1上海空间推进研究所，上海201112
    2电子科技大学 电子学院，成都611731
    3上海空间发动机工程技术研究中心，上海201112
  • 收稿日期:2018-02-27 修回日期:2018-04-16 出版日期:2018-10-25 发布日期:2018-08-29
  • 作者简介:于博（1986-），男，硕士研究生，441695759@qq.com，研究方向为电推进数值计算

An investigation of the sputtering influence on the solar panel by Hall thruster plume

YU Bo1,2,3, WANG Xuan1,3, YU Shuilin1,3, KANG Xiaolu1,3,*   

  1. 1Shanghai Institute of Space Propulsion, Shanghai 201112, China
    2School of Physical Electronics, Universicy of Electronic Science and Technology of China,Chengdu 611731, China
    3Shanghai Engineering Research Center of the Space Engine, Shanghai 201112, China
  • Received:2018-02-27 Revised:2018-04-16 Published:2018-10-25 Online:2018-08-29

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摘要： 霍尔推力器羽流对太阳翼的溅射作用是影响翼板工作性能、卫星供能稳定性的重要因素。为深入研究霍尔推力器羽流在不同布置工况下对太阳翼的溅射影响规律，采用单元粒子/直接蒙特卡洛碰撞模型（PIC/DSMC）求解羽流等离子体的输运过程，其中对离子的扩散作用采用基于菲克定律的求解模型，并以Yamamura溅射模型来求解等离子体对太阳翼表面的溅射产额。为验证修正扩散模型后的算法精度，在真空舱内开展羽流诊断试验，以试验与计算结果的对比来修正扩散经验参数以及验证计算精度。试验结果表明，在扩散系数kd=126×10-36N·m4时，该模型计算误差在87%左右。在此基础上，对不同的推力器方位角、推力器与翼板距离工况，开展羽流对太阳翼的溅射产额计算。计算结果给出太阳翼表面溅射分布随方位角、距离增加的依变规律，并进行了相关透光率影响程度的讨论，可对推力器的星上布置提供参考依据。

关键词: 霍尔推力器, 羽流, 溅射, 太阳翼, 数值计算

Abstract: The sputtering effect of the Hall thruster plume has a large influence on operating performance and power support stability of the solar panel. In order to study the sputtering mechanism of plume bombarding on the solar panel under different installation conditions of Hall thruster, a hybrid model based on Particle in Cell/Directional Simulation of Montecarlo Collisions was employed ,and the ion diffusion model was corrected to solve the plume field. Meanwhile, the Yamamura sputtering model was used to calculate the sputtering yield on the solar panel caused by the plume bombardment. A diagnose test of plume in the vacuum chamber was conducted to verify and correct the feasibility and accuracy of the calculation model, and the diffusion coefficient was corrected to make calculation agree with the test. According to the comparison between the test and calculation results, the error of the calculation model is about 87% with kd=126×10-36N·m4. Based on those, the corrected model was used to calculate the sputtering yield on the solar panel with different onorbit conditions of thruster installation angle and thrusterpanel distance. The calculation results provide the changing rules of the surface sputtering mass distribution on the panel under different conditions, and the light transmittance influenced by sputtering was also predicted. This paper can provide a reference of Hall thruster installation strategy on the satellite.

Key words: Hall thruster, plume, sputtering, solar panel, numerical simulation