Correction maneuvers calculation of quasi elliptical and circular orbits by engine with low and limit thrust

The problem of optimal correcting quasi elliptical and circular orbits by engine with low and limit thrust in the Earth non-center gravitational field is considered. Application of Laplace vector components in spacecraft motion model has allowed to get analytical solutions. Such solutions are equitable for calculation of control parameters, energy consumption and maneuver time for orbits with small eccentricity up to circular. It is shown that methodology of calculation can be used under conditions with more high levels of thrust acceleration. For the evaluation of methodical inaccuracy of solutions numerical simulation of spacecraft motion is conducted.