An universal system to de-orbit satellites at end of life

Sanmartín Losada, Juan Ramón and Charro, Mario and Chen, Xin and Lorenzini, Enrico C. and Colombatti, Giacomo and Zanutto, Denis and Rousee, Jean-Françoise and Sarrailh, Pierre and Williams, John D. and Xie, Khan and Metz, Garret E. and Carrasco, Jose A. and García de Quirós, Francisco and Kroemer, Olaf and Rosta, Roland and Zoest, Tim van and Lasa, Joseba and Marcos, Jesús (2012). An universal system to de-orbit satellites at end of life. "The Journal of Space Technology and Science", v. 26 (n. 1); pp. 21-32. ISSN 0911-551X. https://doi.org/10.11230/jsts.26.1_21.

Description

Title: An universal system to de-orbit satellites at end of life
Author/s:
  • Sanmartín Losada, Juan Ramón
  • Charro, Mario
  • Chen, Xin
  • Lorenzini, Enrico C.
  • Colombatti, Giacomo
  • Zanutto, Denis
  • Rousee, Jean-Françoise
  • Sarrailh, Pierre
  • Williams, John D.
  • Xie, Khan
  • Metz, Garret E.
  • Carrasco, Jose A.
  • García de Quirós, Francisco
  • Kroemer, Olaf
  • Rosta, Roland
  • Zoest, Tim van
  • Lasa, Joseba
  • Marcos, Jesús
Item Type: Article
Título de Revista/Publicación: The Journal of Space Technology and Science
Date: 2012
ISSN: 0911-551X
Volume: 26
Subjects:
Faculty: E.T.S.I. Aeronáuticos (UPM)
Department: Física Aplicada a la Ingeniería Aeronáutica [hasta 2014]
Creative Commons Licenses: Recognition - No derivative works - Non commercial

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Abstract

A 3-year Project financed by the European Commission is aimed at developing a universal system to de-orbit satellites at their end of life, as a fundamental contribution to limit the increase of debris in the Space environment. The operational system involves a conductive tapetether left bare to establish anodic contact with the ambient plasma as a giant Langmuir probe. The Project will size the three disparate dimensions of a tape for a selected de-orbit mission and determine scaling laws to allow system design for a general mission. Starting at the second year, mission selection is carried out while developing numerical codes to implement control laws on tether dynamics in/off the orbital plane; performing numerical simulations and plasma chamber measurements on tether-plasma interaction; and completing design of subsystems: electronejecting plasma contactor, power module, interface elements, deployment mechanism, and tether-tape/end-mass. This will be followed by subsystems manufacturing and by currentcollection, free-fall, and hypervelocity impact tests.

More information

Item ID: 30313
DC Identifier: http://oa.upm.es/30313/
OAI Identifier: oai:oa.upm.es:30313
DOI: 10.11230/jsts.26.1_21
Official URL: https://www.jstage.jst.go.jp/article/jsts/26/1/26_1_21/_article
Deposited by: Biblioteca ETSI Aeronauticos
Deposited on: 28 Jun 2014 05:16
Last Modified: 24 Sep 2014 17:25
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