Utilizing the geometric mechanics framework to predict attitude in a full ephemeris model of the Cislunar region

Abstract

Predicting the attitude of spacecraft traveling within the Cislunar region is crucial to ensure the success of future missions planned within that realm of space. To consider the coupled nature of translational and rotational motion, the circular restricted full three-body problem (CRF3BP), previously proposed by the authors, is utilized to obtain an initial guess for the orbit and attitude motion of the spacecraft. Then, that initial guess is used to transition the trajectory into a full ephemeris model, which considers the additional perturbations due to the Sun’s gravitational effect and the eccentricity of the Moon’s orbit. Orbit/attitude coupling is studied for multiple orbits obtained within the CRF3BP considering spacecraft of different sizes. The trajectories selected for analysis are an L2 Lyapunov orbit, a distant retrograde orbit, a northern halo orbit, and a Lunar transfer from low-Earth orbit. The efficacy of the CRF3BP is demonstrated by studying how spacecraft motion, notably its attitude, is predicted in the full ephemeris model using this formalism.