Method of tethered system control for deorbiting objects using earth's atmosphere

A space tethered system used as an atmospheric braking device for deorbiting small satellites from low orbits is considered. A simplified mathematical model of a small space tethered system that takes into account aerodynamic drag of the upper layers of the atmosphere and tether mass has been developed. A mathematical tool of dynamic systems qualitative theory and bifurcation theory is used for the given model analysis. The feasible modes of tethered system motion during descent in the upper layers of the atmosphere are defined. The most rational mode of tethered system is singled out relying on the stated efficiency factors. Based on CubeSat-Type spacecraft, the application of different tethered system design options have been reviewed. Tethered systems of approximately 2 km long are proved to be efficient for deorbiting small satellites from low nearcircular orbits. © 2017 Univelt Inc. All rights reserved.