极地悬停航天器轨道动力学特性与轨道维持

摘要

针对高纬度地区地球同步轨道卫星存在覆盖盲区的问题,提出了一种长期悬停在极轴上空的极地悬停航天器轨道方案.基于日-地三体模型推导了连续推力控制下的极地悬停航天器轨道动力学模型,并针对悬停高度固定和自由两种模式分析了其推力需求特性和燃料消耗.结合工程实际,对采用电推进和太阳帆混合的极地悬停航天器进行了质量核算和寿命分析.结果表明:考虑电推进自身质量,自由悬停模式较固定悬停模式燃料消耗少,但有效载荷质量减小;太阳帆在当前的帆膜技术下不具有提高有效载荷质量的优势,但未来随着材料的发展太阳帆技术的优势会逐渐显现.文章提出的极地悬停航天器可实现对高纬度地区的连续和实时覆盖.%Pole-sitter spacecraft is proposed to overcome the weakness of geostationary orbits in coverage of polar region.The orbital dynamic characters of pole-sitter spacecraft are derived in three-body problem;thrust characters and fuel consumer are analyzed in both of constant-distance and free-distance hover.Considering the engineering application,the mass budget and mission life are analyzed for both using solar electric propulsion (SEP)and hybrid propulsion combined with solar sails.The results show that when considering the mass of SEP itself,fuel consumer is fewer but the mass of payload is decrease for free-distance hover compared to con-stant-distance hover.The solar sails of current technology cannot increase the mass of payload, but the advantage will appear with the development of technology in the future.The pole-sitter spacecraft proposed in this paper could provide real-time,continuous coverage of the polar region.