Earth-moon resonant orbits design in the ephemeris model

Abstract There is a growing interest in trajectories to support missions throughout cislunar space. As the number of spacecraft in cis-lunar space increases, the demand for long-term observation of these spacecraft also grows. The Earth-Moon resonant orbits could be orbital options for the placement of cislunar space situational awareness satellites. This paper proposes a high-fidelity Earth-Moon resonant orbit design method. To begin with, the continuation method facilitates the transition from a low-fidelity model to a high-fidelity ephemeris model, leading to improved convergence in solving the problem. Furthermore, this paper adopts the time-variable forward/backward multiple-shooting method for numerical iteration, which further reduces the nonlinearity of the solution model. The simulation results indicate that the approach presented in this paper enhances convergence and effectively generates high-fidelity resonant orbits.