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首页> 外文期刊>Journal of guidance, control, and dynamics >Solar Sail Heliocentric Earth-Following Orbits
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Solar Sail Heliocentric Earth-Following Orbits

机译：太阳帆太阳向心绕地轨道

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This Note has introduced the concept of solar sail heliocentric Earth-following orbits. By exploiting the force due to solar radiation pressure on a solar sail, the line of apsides of a heliocentric orbit is rotated such that the aphelion is always directed along the sun-Earth line. This orbit control has been achieved with a simple apsides steering law. By further assuming that the semimajor axis and eccentricity remain constant along the orbit, an analytic expression for the required sail performance has been derived. Removing this assumption allows for slightly better performing heliocentric Earth-following orbits for small sail lightness numbers. Compared with an inertially fixed Keplerian orbit, the heliocentric Earth-following orbits increase the time spent within a predefined cone around the sun-Earth line by an average factor of 1.17 for a sail performance equal to that of NASA's Sunjammer mission (i.e., maximum sail lightness number of 0.0455). For an optimal solar sail steering law, which is directed more radially than the apsides steering law, this factor increases further to an average factor of 1.31. Further improvements in the performance can be achieved when considering a larger sail lightness number of 0.1, which should be achievable in the future by building upon the technology developed for Sunjammer. This lightness number can increase the percentage observation time compared with a Keplerian orbit by a factor of 1.79. Applications of the heliocentric Earth-following orbits have been identified as space weather forecasting and NEOs surveillance, which both require continuous observations taken along the sun-Earth line. This can be achieved by a phased constellation of solar sail satellites along the heliocentric Earth-following orbits.
机译：本说明介绍了太阳帆日心向地球跟踪轨道的概念。通过利用太阳帆上太阳辐射压力产生的力，使日心中心轨道的后方线旋转，从而使后视线始终沿太阳地球线指向。该轨道控制已通过简单的后舵转向定律实现。通过进一步假设半长轴和偏心距沿轨道保持恒定，可以得出所需帆性能的解析表达式。删除此假设后，对于较小的帆亮度数，可以使性能更好的日心向地跟踪轨道运行。与惯性固定的开普勒轨道相比，日心跟随地球的轨道使帆的性能等于NASA的Sunjammer任务（即最大帆）的平均时间，使围绕太阳-地球线的预定锥内所花费的时间平均增加1.17倍。亮度值为0.0455）。对于最优的太阳帆转向定律，该定律比后沿转向定律更径向地定向，该系数进一步增加到平均系数1.31。当考虑更大的帆轻度数0.1时，可以实现性能的进一步提高，将来应该通过为Sunjammer开发的技术来实现。与开普勒轨道相比，该亮度数字可以将观察时间的百分比增加1.79倍。已确定日心跟踪地球轨道的应用是空间天气预报和近地天体监视，这两者都需要沿太阳-地球线进行连续观测。这可以通过沿日心向地跟踪轨道的太阳帆卫星的分阶段星座来实现。

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