Abstract

The motion of a spacecraft with a solar sail is considered within the restricted three-body problem of the Sun–Earth system. The equations of controlled orbital motion of the solar sail in the vicinity of the Sun–Earth collinear libration point \(L_{1}\) are investigated. Modified equations of the circular restricted three-body problem of the Sun–Earth system are used to describe the controlled orbital motion of the spacecraft and to develop the control laws. Our main result is the proposed control law in the form of a feedback that provides spacecraft keeping in the vicinity of the libration point \(L_{1}\) using the light pressure forces.

中文翻译：

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共线共沸点附近太阳帆的受控运动

摘要

带有太阳帆的航天器的运动被认为是在太阳地球系统的受限三体问题内。研究了太阳—太阳共线解放点\（L_ {1} \）附近太阳帆的受控轨道运动方程。日地系统的圆形受限三体问题的修正方程用于描述航天器的受控轨道运动并制定控制律。我们的主要结果是以反馈的形式提出了拟议的控制律，该反馈利用轻压力将航天器保持在解放点\（L_ {1} \）附近。