Earth-Moon Multi-Orbiter Cyclers - New Solutions to the Three-Body Problem

Explore groundbreaking research on a newly discovered class of solutions to the three-body problem in this 15-minute conference presentation. Learn about stable multi-orbiter cyclers that enable spacecraft to alternately orbit both Earth and the Moon naturally and indefinitely without propulsion. Discover how these prograde, ballistic orbits differ from previously known flyby-style cyclers by being aligned with natural Earth-Moon dynamics, requiring no ongoing thrust, maintaining stability without stationkeeping, and offering near-chaotic agility with low delta-v maneuverability. Examine the mathematical framework of the Circular Restricted Three-Body Problem (CR3BP) and understand how these orbits were discovered through differential correction, continuation, and stability analysis via monodromy matrices. Follow the geometric construction of transit pathways and explore various cycler families including (1,1), (2,1), (3,2), (3,1), and (3,3) configurations, each with unique stability characteristics and windows. Investigate the tube dynamics design methodology and see how these discoveries open new possibilities for cislunar mission design while potentially having analogues in binary star systems for rare but dynamically plausible planetary orbits. Gain insights into the mathematical details of orbit construction and stability analysis, with future applications left open for exploration in space mission planning and astrodynamics.