Inclination Change in Low-Earth Orbit via the Geomagnetic Lorentz Force

Abstract

An electrostatically charged spacecraft is subject to Lorentz force perturbations as it orbits a central body with a magnetic field. On an artificially charged spacecraft, these perturbations may be harnessed for orbital maneuvering and are particularly potent for plane-change maneuvers. The Gaussian form of the variational equations is used to develop a control law for inclination change and to predict the capability of such maneuvers. An analytical expression provides the relative evolution of the semimajor axis and the inclination when the Lorentz force is used to change the inclination of a nearly circular orbit. Despite causing significant changes in the semimajor axis, the Lorentz force may enable substantial propellant savings for inclination change maneuvers. A constellation reconfiguration example is presented in which a specific charge magnitude of 0.01 C/kg leads to a 95 % savings over an impulsive maneuver for the redeployment of a low-Earth-orbit constellation from 34 to 55 deg inclination.