基于碳纳米管透明导电膜的航天器表面充电防护试验研究  

Experimental study of spacecraft surface charging protection based on carbon nanotube transparent conductive film

作　　者：李衍存[1] 向宏文[1] 张志平 秦珊珊[1] 蔡震波[1] LI Yancun;XIANG Hongwen;ZHANG Zhiping;QIN Shanshan;CAI Zhenbo(Beijing Institute of Spacecraft System Engineering,Beijing 100094,China)

机构地区：[1]北京空间飞行器总体设计部,北京100094

出　　处：《航天器环境工程》2021年第3期375-380,共6页Spacecraft Environment Engineering

摘　　要：ITO膜常用于卫星表面电位控制,但其易碎、折叠后电阻增大,导致卫星表面存在充电隐患。为解决此问题,试验研究碳纳米管透明导电膜的电阻经过折叠后的变化,并采用低能电子辐照的手段获得碳纳米管膜的充电特性。试验结果显示:碳纳米管膜的体电阻率、充电电位与ITO膜接近,但在相同折叠次数下,碳纳米管膜电阻的变化远小于ITO膜,因此碳纳米管膜在航天器表面充电防护工程应用方面比ITO膜更有优势。The ITO film is often used to control the satellite charging.But it will lead to a hidden trouble of the satellite surface charging when the ITO film is cracked due to its fragility.To deal with this problem,the carbon nanotube transparent conductive film is folded to change its resistance,and it is irradiated by the low energy electron to measure the charging characteristic.It is shown that the carbon nanotube film has the similar volume resistivity and the charging voltage as the ITO film,but with much smaller resistance variations compared with the ITO film for the same fold number.So it is possible to replace the ITO film with the carbon nanotube film,just in the context of satellite charging control.

关 键 词：碳纳米管 透明导电膜 折叠 表面充电 

分 类 号：V257[一般工业技术—材料科学与工程] V416.5[航空宇航科学与技术—航空宇航制造工程]