Designing space tethers to perform orbital maneuvers to remove space debris

Space tethers offer a promising method for performing orbital maneuvers without relying on conventional propulsion systems. Tethers can change a spacecraft’s trajectory efficiently. However, the dynamic behavior of space tethers is highly dependent on the tension they experience during deployment, retraction, and maneuver execution. In this sense, this paper aims to design space tethers for performing orbital maneuvers. In particular, it focuses in looking at materials available with current level of technology that can resist the tensions involved in these maneuvers, such as carbon nanotube and Kevlar. A system of two satellites linked by a space tether is used for the present study and the goal is to remove these satellites from orbit after the end of their operational lives, thereby preventing them from becoming space debris. The two satellites connected by the tether are in rotational motion when the tether is released, which generates an impulse in both satellites. We evaluate the impact of tether length, angular velocity, material properties, and the masses of the satellites on the tension in the tether, allowing us to define the diameter and mass of the tether required to perform the maneuver. The findings provide key insights into the problem of reducing space debris in LEO and can be applied to many types of satellites. In particular, remote sensing missions in LEO can benefit from this maneuver to be removed from orbit to free up space for substitutive satellites. © 2025 Elsevier B.V., All rights reserved.