Eclipse Mitigation Maneuver Strategy for Earth-Moon 3:2 Resonant Orbits

Resonant orbits (ROs) within the Earth-Moon system exhibit periodic motion characterized by a simple integer relationship with the lunar period. These orbits hold significant applications for space situational awareness and the design of transfer orbits in cislunar space. However, due to the expansive scale and extended periods associated with Earth-Moon ROs, the resulting eclipse durations often exceed spacecraft power and thermal system capabilities. This paper conducts an analysis of shadow distribution and eclipse durations within the Earth-Moon 3:2 resonant orbit family. The investigation utilizes relative velocity with respect to the lunar shadow, highlighting the imperative need for eclipse mitigation. The study then proceeds to derive eclipse mitigation methods, specifically employing cross-track maneuver and phasing maneuver techniques. These strategies are applied to mitigate and avoid both Earth and lunar shadows, considering different initial solar phases and eclipse occurrence locations. Simulation results conducted within the circular restricted three-body problem (CRTBP) indicate that the eclipse mitigation strategy via cross-track maneuver incurs a lower Delta V\documentclass[12pt]{minimal} \usepackage{amsmath} \usepackage{wasysym} \usepackage{amsfonts} \usepackage{amssymb} \usepackage{amsbsy} \usepackage{mathrsfs} \usepackage{upgreek} \setlength{\oddsidemargin}{-69pt} \begin{document}$$\Delta V$$\end{document} cost, remaining within the range of 20 m/s. Furthermore, the stability of the resonant orbits post cross-track maneuver is examined. The study presents the maximum allowable cross-track maneuver Delta V\documentclass[12pt]{minimal} \usepackage{amsmath} \usepackage{wasysym} \usepackage{amsfonts} \usepackage{amssymb} \usepackage{amsbsy} \usepackage{mathrsfs} \usepackage{upgreek} \setlength{\oddsidemargin}{-69pt} \begin{document}$$\Delta V$$\end{document}s which maintain orbit stable in five years for the entire resonant orbit family. Ultimately, the paper recommends a 2-hour maximum allowable eclipse duration for spacecraft in Earth-Moon 3:2 resonant orbits, offering valuable insights for the future design of missions within these orbits. The eclipse mitigation and avoidance strategies, along with the analytical methods proposed herein, can be readily extended to other resonant orbit families.