近地轨道大型航天器的环境充电

LARGE-SCALE SPACECRAFT CHARGING

许多空间实验和电子计算机预测已经揭示，在极光电子环境中大型航开器的充电电位会高达６０００～７０００Ｖ。对采用大功率太阳阵的航天器而言，其相对于空间等离子体的悬浮电位将因太阳阵工作电压的提高而增加。航天器充电及其悬浮电位提高都导致航天器与空间等离子体间有害的相互作用增加。例如表面材料因遭受离子轰击和电弧放电而老化、剥蚀，由于材料再沉积而使表面污染增加以及航天器电子系统因静电放电而受到严重的干扰和破坏等。因而对载人航天和长寿命空间站而言，解决航天器带电问题不可等闲视之。对极光电子效应、航天器尾流效应、大功率太阳阵及特种工作载荷与环境等离子体的相互作用引起的航天器带电及其控制作了讨论。

Some space experiments and the computer predictions have discovered that the large spacecraft should be charged up to 6000-7000V in high fluxes auroral electron environment.For the spacecraft using of high voltage solar array,its floating potential relative to space plasma ground would rise,result from the voltage level increase. Both the spacecraft charging and the floating potential rising make the spacecraft damaging interaction with space plasma enhance. For instance,the surface material will be destructed and eroded by ion sputting and discharging, the spacecraft surface will be contaminted by redeposition, the electronic system will be interfered or destructed by ESD,and so on. As to the manned flight and the long life space station,it should not be ignored to resolve the problem of spacecraft charging, This paper discusses the effects of the large spacecraft charging in low earth orbit due to the auroral electron, the ram-wake effect,the payload interactions with space plasma environment,and the spacecraft charging control.