Design of a Low-Energy Earth-Moon Flight Trajectory Using a Planar Auxiliary Problem

The paper presents a sufficiently simple technique for designing low-energy flight trajectory of spacecraft (SC) from the Earth to Moon with insertion into low circular orbit latter. proposed is based on solution and subsequent analysis special model problem, which variant restricted four-body problem (RC4BP) Earth-Sun-SC-Moon; it assumed that planes orbits all considered bodies coincides. planar motion center mass SC relative as perturbed (Sun, Moon). To describe it, equations in osculating elements are used, obtained by using method variation constants analytical two (RC2BP)—Earth-SC, rotation main axes coordinate system (the plane) synchronized Sun. near-Earth selenocentric one (“full” model—a (R4BP), an ephemeris model) optimization impulse formulation. carried out few (three) stages, each appropriate current auxiliary determined, subsequently used basis initial approximation one.