The repositioning maneuver of artificial Earth satellite in a circular orbit with the phasing coils trajectory

The article describes a fundamentally new method for solving the problem of calculating the flight time between two points of the central gravitational field of elliptic and hyperbolic orbits. It as an independent variable instead of the linear elements – semi-major axis or the focal parameter of the orbit – the angular parameter used (the angle between the starting point radius vector between and initial velocity vector of the trip).