TugSat: Removing Space Debris from Geostationary Orbits Using Solar Sails

Abstract

Space debris accumulation is on the rise as commercial space applications become more affordable and existing satellites near the end of their operational lifetimes. For geosynchronous equatorial orbits, solar radiation pressure provides a unique solution for the removal of larger debris such as inoperable satellites. Given the current state of the art in solar sailing technology, a CubeSat can be tasked to deorbit satellites on the order of 1000 kg using a high-performance solar sail for propulsion. This CubeSat, called “TugSat,” is simulated in this study, virtually deorbiting a satellite from geostationary orbit without the use of standard propulsion systems. This same TugSat can be reused indefinitely, between the geosynchronous equatorial orbit belt and the retirement orbit, to continuously remove debris from valuable geostationary orbit slots. The entire deorbit maneuver will demonstrate control of a satellite’s semimajor axis, eccentricity, inclination, and geosynchronous equatorial orbit belt longitude: all using techniques to optimize time rates of change in the satellite’s orbital elements. The TugSat concept provides a low-cost reusable means for geosynchronous equatorial orbit belt cleanup or open-ended geosynchronous equatorial orbit belt mission applications.