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.

Authors
Razoumny Y.N. 1 , Kupreev S.A. 1 , Misra A.K.2
Journal
Advances in the Astronautical Sciences
Publisher
Univelt Inc.
Language
English
Pages
1031-1050
Status
Published
Volume
161
Year
2017
Organizations
  • 1 Department of Mechanics and Mechatronics, Academy of Engineering, Peoples' Friendship University of Russia (RUDN University), 6, Mikluho-Maklaya Str, Moscow, 117198, Russian Federation
  • 2 Department of Mechanical Engineering, McGill University, 817 Sherbrooke Street West, Montreal, QC H3A0C3, Canada
Keywords
Aerodynamic drag; Bifurcation (mathematics); Cobalt compounds; Dynamical systems; Dysprosium compounds; Orbits; Space flight; Space tethers; Upper atmosphere; Bifurcation theory; Braking devices; Efficiency factor; Mathematical tools; Model analysis; Near-circular orbits; Simplified mathematical model; Tethered systems; Sulfur compounds
Date of creation
19.10.2018
Date of change
21.04.2021
Short link
https://repository.rudn.ru/en/records/article/record/5828/
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