Satellite deorbiting by means of electrodynamic tethers Part II: System (Articolo in rivista)

Type
Label
  • Satellite deorbiting by means of electrodynamic tethers Part II: System (Articolo in rivista) (literal)
Anno
  • 2002-01-01T00:00:00+01:00 (literal)
Alternative label
  • Iess L., Bruno C., Ulivieri C., Vannaroni G. (2002)
    Satellite deorbiting by means of electrodynamic tethers Part II: System
    (literal)
Http://www.cnr.it/ontology/cnr/pubblicazioni.owl#autori
  • Iess L., Bruno C., Ulivieri C., Vannaroni G. (literal)
Pagina inizio
  • 407 (literal)
Pagina fine
  • 416 (literal)
Http://www.cnr.it/ontology/cnr/pubblicazioni.owl#numeroVolume
  • 50(7) (literal)
Note
  • ISI Web of Science (WOS) (literal)
Titolo
  • Satellite deorbiting by means of electrodynamic tethers Part II: System (literal)
Abstract
  • This paper aims to assess the efficiency of a de-orbiting system based upon conductive tethers under realistic assumptions for its interaction with the ionospheric environment. We analyze the configuration made up of a 2.5 - 10 km tether, a passive inflatable collector of 2.5 - 10 m radius at the positive termination and a hollow cathode at the negative one. Voltages and current in the system are computed from the equation of the equivalent circuit, making use of the IRI-90 ionospheric model. The resulting electromagnetic drag forces have been used to compute the evolution of the orbital elements (especially the semi-major axis) and the re-entry times. Our results indicate that a typical satellite of 500 kg mass at 1300 km altitude can de-orbit in 20-100 days, for a broad range of orbital inclinations and solar activity. The validity of the concept is further strengthened by the comparison with alternative propulsion systems. (literal)

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