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Abstract <p>The controlled motion of a spacecraft in the vicinity of a Sun–Earth collinear libration point is studied. The spacecraft motion is described by the model of the circular restricted three-body problem. An approach to constructing the orbital spacecraft motion control laws for a long stay in the designed orbits is proposed. The approach is based on the use of a special function of phase variables and time whose value characterizes the deviation of the spacecraft trajectory from the designed orbit. The results of numerical simulations are presented.</p>

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Orbital Motion Control near the Designed Orbitin the Vicinity of a Collinear Libration Point

  • 期刊论文

  • 发表日期：

    2025年11月1日

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  • D. V. Shymanchuk,
  • A. S. Shmyrov,
  • V. A. Shmyrov

摘要

Abstract

The controlled motion of a spacecraft in the vicinity of a Sun–Earth collinear libration point is studied. The spacecraft motion is described by the model of the circular restricted three-body problem. An approach to constructing the orbital spacecraft motion control laws for a long stay in the designed orbits is proposed. The approach is based on the use of a special function of phase variables and time whose value characterizes the deviation of the spacecraft trajectory from the designed orbit. The results of numerical simulations are presented.