大型航天器电位控制系统设计及验证  

Design and Verification of Potential Control for Large Spacecraft

作　　者：梁晓锋 仪德英 高升[1] LIANG Xiaofeng;YI Deying;GAO Sheng(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：《航天器工程》2023年第5期85-90,共6页Spacecraft Engineering

摘　　要：分析了大型航天器在轨交会对接及执行特殊任务等需求,提出了针对不同供电电压等级航天器交会对接、机械臂操作和航天员出舱等任务中的舱体不等电位问题,给出了被动电位控制及主动电位控制的方案。在此基础上提出了具体的设计方案及关键参数的确定,完成了被动电位控制地面验证方案,给出了试验验证结果,完成了主动电位控制在轨实际运行,并给出了实际运行结果情况。可为后续类似航天器的相关设计及地面试验验证提供参考。This paper analyzes the requirements of large spacecraft in rendezvous and docking,as well as the execution of special tasks.It proposes solutions for passive potential control and active potential control to address the problem of unequal potential of spacecraft bodies in mission of rendezvous and docking,robotic arm operation and astronaut extravehicular activity(EVA)with different power supply voltage levels.On this basis,a specific design scheme and the determination of key parameters are proposed,and aground verification scheme for passive potential control is completed,the test verification results are given,the actual operation of active potential control in orbit is completed,and the actual operation results are given.It provides a reference for the subsequent design and ground test verification of similar spacecraft.

关 键 词：大型航天器 电位控制 出舱 交会对接 

分 类 号：V442[航空宇航科学与技术—飞行器设计]