Interplanetary Transfers Between Halo Orbits: Connectivity Between Escape and Capture Trajectories

摘要

Spacecraft escape and capture trajectories from or to Halo orbits about the L1or L2 points using impulsivernmaneuvers at periapsis of the manifolds for interplanetary transfers are analyzed in the restricted Hill three-bodyrnproblem. This application ismotivated by future proposals to place deep-space ports at the Earth andMars L1or L2rnpoints. First, the feasibility of interplanetary trajectories between Earth Halo orbits and Mars Halo orbits isrninvestigated. In this study, unstable and stable manifolds associated with the Halo orbits are used to approach thernvicinity of the planet’s surface, and use impulsive maneuvers at periapsis for escape and capture trajectories to andrnfrom Halo orbits. Interplanetary trajectories between Earth and Mars Halo orbits with reasonable u0001V and flightrntime are found. Next, applying these dynamics to an Earth–Mars transportation system using spaceports on Earthrnand Mars Halo orbits, the system is evaluated in terms of the spacecraft mass of round-trip transfer. As a result,rntransfer between low Earth orbits and low Mars orbits via the planets’ Halo orbits can reduce spacecraft wet massrncompared with a direct round-trip transfer, by leaving propellant for the return.