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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4.0sccm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20V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。
A LEO large spacecraft powered by a high-voltage solar array power system collects the ambient electrical current in the surrounding space, causing it to be charged to a higher negative potential, causing serious problems with the spacecraft rendezvous and astronaut leaving the bay Therefore, the active control of such spacecraft surface potential can effectively reduce the operational risk of spacecraft and ensure the safety of astronauts. The method of ground simulation is used to control the surface potential of the spacecraft with negative charge by simulating the space environment with the means of electron emission from the hollow cathode plasma contactor. The results show that when the minimum working fluid flow rate is greater than 4.0sccm, the electron current emitted by the hollow cathode can counteract the electron current absorbed by the spacecraft and realize the adaptive control of the spacecraft potential, and the spacecraft surface potential is controlled within 20V. With the increase of xenon flow rate, the clamping voltage will be smaller. This method will effectively avoid the danger of astronauts leaving space and the danger of the spacecraft rendezvous and docking at the time of docking, which is of great significance for the protection of the charged effects of spacecraft in China.