The launch of a spacecraft into the stable, high polar orbits of a Moon artificial satellite is considered. These orbits can be used to construct a lunar multifunctional satellite system, as well as a near-Moon orbital spaceport. Analysis and comparison of three schemes of direct spacecraft transfer from the Earth to the Moon—with a one-, two-. and three-impulse maneuver of transition into the final orbit—are performed. In particular, the energy, geometrical, and temporal characteristics of a two-impulse transfer obtained under significant influence of gravitational perturbations are compared with their one- and three-impulse analogues.
Analysis of Trajectories of Spacecraft Launching into High Circular Orbits of the Moon Artificial Satellite
Cosmic Res
Cosmic Research ; 60 , 3 ; 202-212
2022-06-01
11 pages
Aufsatz (Zeitschrift)
Elektronische Ressource
Englisch