This work focuses on the ballistic analysis of a small spacecraft mission based on a unified platform, equipped with an electric propulsion system for flight to the Moon. It discusses the general aspects of delivering a small spacecraft to the Moon and the practical schemes used for launching it onto a departure trajectory. The paper presents and justifies a ride-share launch scheme where the small spacecraft is first placed into near-Earth orbit and then uses an upper-stage to transfer onto a trajectory toward the Moon. An example of a reference transfer trajectory to the Moon is given. The study also includes a launch scheme for deploying several small spacecraft into lunar orbits demonstrating the possibility to develop a lunar constellation.

small spacecraft, sun-assisted low-energy trajectory, rideshare launch, lunar constellation

Theoretical and applied problems of mechanics