Using electrodynamic tethers to perform orbit maneuvers in sun-synchronous satellites

This paper investigates the utilization of electrodynamic tethers for orbital maneuvers, focusing on remote sensing satellites in sun-synchronous orbits, which are a critical asset for environmental monitoring and sustainable development. Electrodynamic tethers present a sustainable and cost-effective alternative to traditional propulsion systems by using the Lorentz force generated through interactions with Earth’s magnetic field, thus eliminating the need for chemical propellants. The study emphasizes the development of new control laws aimed at minimizing the total electrical charge required for orbital adjustments, particularly in semi-major axis and inclination, which are vital for maintaining sun-synchronous orbits. Simulations demonstrate significant improvements, with a reduction of up to 22.36% in charge consumption compared to solutions available in the literature, while ensuring that the satellite remains within its precise orbital parameters. These methods not only extend the satellite’s operational life, but also reduce the need for extensive tether lengths by allowing larger currents. The findings highlight the potential of electrodynamic tethers for satellite propulsion, providing an efficient solution for both orbital maintenance and deorbiting. The research shows the importance of this technology for future space missions, offering a viable pathway to enhance satellite management and contribute to sustainable space exploration. © 2025 Elsevier B.V., All rights reserved.