Publication Date:
2019
Description:
〈h3〉Abstract〈/h3〉
〈p〉We studied Earth–Moon transfer trajectories in the circular restricted three-body problem (CRTBP) from the viewpoint of families and considered their applications in transferring a spacecraft from the Earth to periodic orbits around Sun–Earth libration point 〈span〉
〈span〉\(L_{2}\)〈/span〉
〈/span〉 (SE–L2). Initially, twelve families of trajectories with transfer time shorter than fifty days are identified in the Earth–Moon system. By connecting these transfers with stable manifolds of the target orbit, low-energy transfers from the low Earth orbit to a small-amplitude periodic orbit around SE–L2 are determined in two separate CRTBPs (Earth–Moon and Sun–Earth CRTBPs). Then, taking the patched trajectories as initial guesses and introducing a small maneuver at the perilune, we optimize the whole transfer trajectories in the Sun–Earth–Moon–Spacecraft system. Results indicate that it is possible to realize low-energy transfers to small-amplitude orbits around SE–L2 by patching the Earth–Moon transfers with stable manifolds of the target orbits.〈/p〉
Print ISSN:
0004-640X
Electronic ISSN:
1572-946X
Topics:
Physics
