Two trajectory configurations for the low-thrust transfer between northern and southern halo orbits in the Earth-Moon system

Abstract

This paper presents a study of the low-thrust transfer problem between L2 northern and southern halo orbits using the Pontryagin minimum principle (PMP) in the Earth-Moon circular restricted three-body problem (CRTBP). The northern and southern halo families exist in the vicinity of the Moon, and have the same orbital period distribution, which can be used for space missions such as lunar navigation constellations, lunar relay communications and lunar space stations. Traditional low-thrust transfer trajectories are multi-revolution structures, which are modeled in this problem as multiple rotations around the libration point. The characteristics of the transfer are affected by the number of revolutions. Moreover, we propose a novel approach using invariant manifolds associated with periodic orbits in the CRTBP to construct L2 north–south halo orbit transfers. This approach results in superior transfer performance, which involves shorter time of flight, lower fuel consumption and reduced engine thrust requirements. A complete set of low-thrust time-, energy- and fuel-optimal transfer algorithms using moving point strategies and continuation methods is proposed. The computational procedures and analysis presented in this paper provide a reliable reference for the design of related orbital transfer missions.