Mass Ratio of Electrodynamic Tether to Spacecraft on Deorbit Stability and Efficiency
Author:
Affiliation:
1. Northwest Polytechnical University, 710072 Xi’an, People’s Republic of China
2. York University, Toronto, Ontario M3J 1P3, Canada
Publisher
American Institute of Aeronautics and Astronautics (AIAA)
Subject
Applied Mathematics,Electrical and Electronic Engineering,Space and Planetary Science,Aerospace Engineering,Control and Systems Engineering
Link
http://arc.aiaa.org/doi/pdf/10.2514/1.G000429
Reference14 articles.
1. Risks in Space from Orbiting Debris
2. Electrodynamic Tether Applications and Constraints
3. Benefits and risks of using electrodynamic tethers to de-orbit spacecraft
4. Generator Regime of Self-Balanced Electrodynamic Bare Tethers
5. Optimum sizing of bare-tape tethers for de-orbiting satellites at end of mission
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