大型低轨道载人航天器电位主动控制
收稿日期: 2015-06-01
修回日期: 2015-10-26
网络出版日期: 2015-10-30
Large manned spacecraft with active potential control at LEO
Received date: 2015-06-01
Revised date: 2015-10-26
Online published: 2015-10-30
采用高电压太阳电池阵供电系统的低轨道(LEO)大型航天器会收集周围空间环境电子电流,使其被充电到较高的负电位,从而对航天器交会对接和航天员出舱产生严重的危害,因此对这种航天器表面电位进行主动控制可有效降低航天器运行风险和保障航天员安全。采用地面模拟试验的方法,利用空心阴极等离子体接触器发射电子的手段,模拟太空环境下对带负电航天器表面电位进行有效控制。研究结果表明,最小工质流率大于4.0 sccm时空心阴极发射的电子电流可以抵消航天器吸收的电子电流,实现航天器电位的自适应控制,将航天器表面电位钳制在20 V之内;且随着氙气流率的增加,钳位电压会更小。这一方法将有效避免航天员出舱活动和航天器交会对接时的放电危险,对中国航天器带电效应防护具有很重要的意义。
蒋锴 , 王先荣 , 秦晓刚 , 杨生胜 , 杨威 , 史亮 , 李得天 . 大型低轨道载人航天器电位主动控制[J]. 航空学报, 2016 , 37(5) : 1563 -1572 . DOI: 10.7527/S1000-6893.2015.0288
At low Earth orbit (LEO), a large spacecraft using high voltage solar arrays will collect electron current that leads to a high negative potential, which will pose threat to astronaut extravehicular activities and spacecraft rendezvous and docking. The active spacecraft potential control can efficiently reduce spacecraft operation risks and safety of astronaut. In this paper, the ground test method to simulate the potential active controlling of negative charged spacecraft in the space environment by emission electron current using hollow cathode plasma contactor is mainly adopted. The results show that the emission electron current of hollow cathode contactor can eliminate collected electron current of spacecraft when the flow rate of Xenon exceeds minimum of 4.0 sccm, which can be the self-regulating control of spacecraft potential and the spacecraft potential is clamped within 20 V. Moreover, with the flow rate of Xenon increasing, the clamping potential is smaller. This potential control method can avoid charged danger not only to astronaut extravehicular activities but spacecraft rendezvous and docking efficiently, which is also significant to the spacecraft charging guard.
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