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The low-thrust cargo spacecraft between the earth and the moon is very important for long-term sustainable manned lunar exploration. However, the Earth-Moon transfer of continuous low-thrust cargo spacecraft needs to go through the stages of earth escape and moon capture. The escape/capture orbit near the celestial body is multi-circle spiral, and the transfer duration is long. At the same time, the motion is affected by the gravitational field of the earth and the moon. Therefore, it is difficult to optimize the low-thrust transfer trajectory from the earth parking orbit to the moon target orbit in the Earth-Moon system. In this paper, an optimization method of low-thrust Earth-Moon transfer orbit in three-body system based on sequential convex optimization is proposed. The convex optimization problem of the Earth-Moon transfer is constructed by convexizing the model and constraints. The two-body Earth escape orbit and the lunar capture orbit are designed based on the indirect method in the inertial coordinate system. Then, the two orbits are spliced in the rotating coordinate system as the initial trajectory to solve the convex optimization problem to improve the convergence of the optimization algorithm, and the fuel-optimal transfer trajectory is solved by the successive approximation strategy. Secondly, two schemes of direct earth-moon transfer and earth-moon transfer based on invariant manifold are proposed. The simulation results show that the reliable design of the three-body system Earth-Moon transfer orbit can be realized by using the two-body splicing orbit as the initial value and the iterative solution based on the sequential convex optimization method. The better initial guess path makes the transfer orbit converge around 10 iterations. Compared with the direct transfer, the fuel consumption of the invariant manifold transfer is reduced by 17.52%, and the transfer time is increased by 11.8632%. The two transfer schemes can meet the different needs of the manned lunar exploration mission for the transfer time and fuel consumption of the cargo spacecraft.

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Low-Thrust Earth-Moon Transfer Trajectories Design with Sequential Convex Optimization in Three-Body Systems

  • 会议论文

  • 发表日期：

    2026年

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  • Li Zhenyu,
  • Peng Qibo,
  • Zhou Wanmeng,
  • Li Xiangyu,
  • Qiao Dong

摘要

The low-thrust cargo spacecraft between the earth and the moon is very important for long-term sustainable manned lunar exploration. However, the Earth-Moon transfer of continuous low-thrust cargo spacecraft needs to go through the stages of earth escape and moon capture. The escape/capture orbit near the celestial body is multi-circle spiral, and the transfer duration is long. At the same time, the motion is affected by the gravitational field of the earth and the moon. Therefore, it is difficult to optimize the low-thrust transfer trajectory from the earth parking orbit to the moon target orbit in the Earth-Moon system. In this paper, an optimization method of low-thrust Earth-Moon transfer orbit in three-body system based on sequential convex optimization is proposed. The convex optimization problem of the Earth-Moon transfer is constructed by convexizing the model and constraints. The two-body Earth escape orbit and the lunar capture orbit are designed based on the indirect method in the inertial coordinate system. Then, the two orbits are spliced in the rotating coordinate system as the initial trajectory to solve the convex optimization problem to improve the convergence of the optimization algorithm, and the fuel-optimal transfer trajectory is solved by the successive approximation strategy. Secondly, two schemes of direct earth-moon transfer and earth-moon transfer based on invariant manifold are proposed. The simulation results show that the reliable design of the three-body system Earth-Moon transfer orbit can be realized by using the two-body splicing orbit as the initial value and the iterative solution based on the sequential convex optimization method. The better initial guess path makes the transfer orbit converge around 10 iterations. Compared with the direct transfer, the fuel consumption of the invariant manifold transfer is reduced by 17.52%, and the transfer time is increased by 11.8632%. The two transfer schemes can meet the different needs of the manned lunar exploration mission for the transfer time and fuel consumption of the cargo spacecraft.