Abstract: A vehicle, such as a satellite or other spacecraft, includes an electrodynamic tether connected thereto. A processor, contained within the vehicle and connected to the electrodynamic tether, is configured to cause a current to be directed to the electrodynamic tether to cause a change in motion of the vehicle. Sensors, such as an attitude sensor, a position sensor, a magnetometer, and an ionosphere sensor, are contained within the vehicle and are connected to the processor. The processor is configured to direct current to the electrodynamic tether based upon input received from the sensors to maintain the vehicle within a specified orbit, such as a highly-inclined eccentric orbit over the polar or other high-latitude region, or to change the vehicle's orbit. The processor may be configured in a closed-loop configuration to account for measured errors by the sensors position, attitude, ionospheric charge density, and/or the Earth's magnetic field.