A Method for Constructing Low-Energy Trajectories for Earth–Moon Transfers.

The paper proposes a method for constructing trajectories for launching a spacecraft into a circular polar orbit of an artificial Moon satellite (AMS) based on the use of the properties of invariant manifolds of solutions to the circular restricted three-body problem. This approach, in comparison with the classical Hohmann transfer, makes it possible to significantly reduce the braking impulse by increasing the flight time. The process of constructing flight orbits includes two stages. At the first stage, solutions to the circular restricted three-body problem are analyzed, as a result of which the least costly options for entering the AMS orbit are selected. At the second stage, orbits corresponding to the found options and passing at a given distance from the Earth are constructed in the ephemeris model of the Solar System. The developed method was applied to analyze the possibilities of flights to polar orbits of the AMS with an altitude of 150 km in 2030. Options for entering the orbit of the AMS are described corresponding to the braking impulse values of 619.5 and 623.3 m/s with a flight duration of 111 days and 93 days, respectively. [ABSTRACT FROM AUTHOR]