Constructing High-Fidelity Spacecraft Trajectory Baselines with Higher-Dimensional Invariant Tori

In this work, we transition a wide variety of invariant tori found in the Earth-Moon Circular Restricted 3-Body Problem (CR3BP) into three higher-fidelity intermediate dynamical models: the Hill Restricted 4-Body Problem (HR4BP), the Elliptic HR4BP (E-HR4BP), and the Inclined Elliptic HR4BP (IE-HR4BP). The CR3BP orbits we focus on in this work are resonant Lyapunov, halo, butterfly, and dragonfly periodic orbits (POs), as well as 2-D quasi-periodic orbits (QPOs) including Lissajous and quasi-halo orbits around resonant POs. Dynamical equivalents to these CR3BP orbits in the three intermediate models range from 1-D invariant tori (resonant CR3BP POs in the HR4BP) to 4-D invariant tori (resonant CR3BP 2-D QPOs in the IE-HR4BP). We isolate trajectories on these higher-dimensional invariant tori to generate long-term baseline trajectories in an ephemeris model and evaluate how well the ephemeris trajectories are approximated by the tori in the IE-HR4BP This comparison informs astrodynamicists on what dynamical perturbations significantly impact specific orbit structures in cislunar space. Furthermore, if these tori are sufficiently close to ephemeris trajectories, it may be possible to conduct high-fidelity mission design analysis on these orbits without directly using an ephemeris model, expanding the set of analysis tools available to mission designers.