Design of low-energy transfer from lunar orbit to asteroid in the Sun-Earth-Moon system

Abstract

Asteroid exploration trajectories which start from a lunar orbit are investigated in this work. It is assumed that the probe departs from lunar orbit and returns to the vicinity of Earth, then escapes from the Earth by performing a perigee maneuver. A low-energy transfer in Sun-EarthMoon system is adopted. First, the feasible region of lowenergy transfer from lunar orbit to perigee within 5 000 km height above the Earth surface in Sun-Earth-Moon system is calculated and analyzed. Three transfer types are found, i.e., large maneuver and fast transfers, small maneuver and fast transfers, and disordered and slow transfers. Most of feasibility trajectories belong to the first two types. Then, the lowenergy trajectory leg from lunar orbit to perigee and a heliocentric trajectory leg from perigee to asteroid are patched by a perigee maneuver. The optimal full-transfer trajectory is obtained by exploiting the differential evolution algorithm. Finally, taking 4179 Toutatis asteroid as the target, some low-energy transfer trajectories are obtained and analyzed.

Integrated Design of Moon-to-Earth Transfer Trajectory Considering Re-Entry Constraints

“…For the Earth-to-Moon trajectory design, researchers have developed multiple trajectory design technologies. The traditional impulse transfer is the classic method adopted by the first Moon exploration missions [27,28], while the small thrust transfer [29][30][31][32][33][34][35] and the weak stable boundary (WSB) transfer methods [36][37][38] appeared in the 1990s. In recent years, there have been the use of Moon flybys to achieve libration point transfers and even the deployment of Earth's high-orbit satellites [39,40].…”