Low-Thrust Many-Revolution Transfer between Near Rectilinear Halo Orbit and Low Lunar Orbit Using Hybrid Differential Dynamic Programming

2025/04/10 by Oue, Kohei, Ozaki, Naoya, Chujo, Toshihiro
#Earth and Planetary Astrophysics (astro-ph.EP) #FOS: Mathematics #FOS: Physical sciences #Instrumentation and Methods for Astrophysics (astro-ph.IM) #Optimization and Control (math.OC)

paper · doi:10.48550/arxiv.2504.07723

Abstract

Low-thrust, many-revolution transfers between near-rectilinear halo orbits and low lunar orbits are challenging due to the many-revolutions and is further complicated by three-body perturbation. To address these challenges, we extend hybrid differential dynamic programming by enhancing with a continuation of dynamical system. The optimization begins with the Sundman-transformed two-body problem and gradually transitions to the Sundman-transformed circular restricted three-body problem expressed in the moon-centered inertial frame. Numerical examples demonstrate the robust convergence of our method, where optimal transfers from low lunar orbit to near-rectilinear halo orbit are obtained with a poor initial guess of low lunar orbit.

Related

• Optimization of Transfers linking Ballistic Captures to Earth-Moon Periodic Orbit Families
• Systematic Design of Optimal Low-Thrust Transfers for the Three-Body Problem
• Low-Thrust Many-Revolution Trajectory Design Under Operational Uncertainties for DESTINY+ Mission
• Optimal Multi-Mode Propulsion Mission Design Using Direct Collocation
• Families of Transfers from circular low Earth orbit to Distant Prograde Orbit around the Moon