Design and analysis of electro-dynamic tether micro-satellite for active space debris mitigation
- Paper number
IAC-13,A6,5,7,x20214
- Author
Mr. Xinsheng Wang, Beihang University, China
- Coauthor
Mr. Yongchao Dai, Beihang University, China
- Year
2013
- Abstract
Electro-dynamic tethers offer high performance as propellantless deorbiting systems and are among the main candidates for the implementation of active debris removal. After a preliminary review of the current space debris population in Low Earth Orbit, the fundamental aspects of Electro-dynamic Tethers (EDTs) are described. Issues about tether impact risk with other debris and tether maneuverability are also discussed. When the electro-dynamic tether is deployed, the Lorentz force generated by conductive cable cutting the earth's magnetic field produces an electro-dynamic drag leading to a fast satellite orbital decay. This paper presents a study of the process of de-orbiting using electro-dynamic tether system and introduces the research progress of BUAA micro-satellite (BUAA-SAT). A design of de-orbiting system suitable for micro-satellite is put forward. Establish a de-orbiting model and forecast the de-orbiting time by numeric simulation. The simulation results show that the electro-dynamic tether can greatly reduce the de-orbiting time.
- Abstract document
- Manuscript document
IAC-13,A6,5,7,x20214.pdf (🔒 authorized access only).
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