Assessing the vulnerability to debris impacts of electrodynamic tethers during typical de-orbiting missions (Contributo in atti di convegno)

Type

• Contributo in atti di convegno (Classe)
• Prodotto della ricerca (Classe)

Label

• Assessing the vulnerability to debris impacts of electrodynamic tethers during typical de-orbiting missions (Contributo in atti di convegno) (literal)

Anno

• 2005-01-01T00:00:00+01:00 (literal)

Alternative label

• Pardini C.(a); Anselmo L.(a); Hanada T.(b); Hirayama H.(b) (2005)
  Assessing the vulnerability to debris impacts of electrodynamic tethers during typical de-orbiting missions
  in 4th European Conference on Space Debris, Darmstadt (D), Germany, 18-20 April 2005
  (literal)

Http://www.cnr.it/ontology/cnr/pubblicazioni.owl#autori

• Pardini C.(a); Anselmo L.(a); Hanada T.(b); Hirayama H.(b) (literal)

Pagina inizio

• 353 (literal)

Pagina fine

• 360 (literal)

Http://www.cnr.it/ontology/cnr/pubblicazioni.owl#titoloVolume

• Proceedings of the Fourth European Conference on Space Debris (literal)

Http://www.cnr.it/ontology/cnr/pubblicazioni.owl#volumeInCollana

• ESA SP-587 (literal)

Http://www.cnr.it/ontology/cnr/pubblicazioni.owl#note

• (Germany, 18-20 April, 2005 ). Proceedings, Vol. ESA SP-587, pp. 353-360. D. Danesy (ed.). European Space Agency (ESA) Publications Division, 2005. (literal)

Http://www.cnr.it/ontology/cnr/pubblicazioni.owl#descrizioneSinteticaDelProdotto

• ABSTRACT: De-orbiting devices based on the use of conducting tethers have been recently proposed as innovative solutions to mitigate the growth of orbital debris. Electrodynamic tether drag might actually provide a cost-effective method to rapidly and safely remove spent upper stages and defunct satellites from low Earth orbits. However, because of their small diameter, tethers of normal design may have a high probability of being severed by impacts with relatively small meteoroids and orbital debris. In order to assess the vulnerability of electrodynamic tether systems during typical de-orbiting missions, specific work has been carried out at ISTI/CNR (Pisa, Italy) and Kyushu University (Fukuoka, Japan) over the last few years, and suitable models and methods have been specifically developed for the analysis of single and double line tethers in circular orbit and aligned along the gravity gradient. The purpose of this paper is to present the two different approaches, which have been applied to realistic de-orbiting missions of spacecraft with inclinations up to about 75 deg and initial altitudes up to 1400 km. (literal)

Note

• Google Scholar (literal)
• Scopu (literal)

Http://www.cnr.it/ontology/cnr/pubblicazioni.owl#affiliazioni

• (a)ISTI/CNR, Pisa, Italy; (b)Kyushu University, Fukuoka, Japan (literal)

Titolo

• Assessing the vulnerability to debris impacts of electrodynamic tethers during typical de-orbiting missions (literal)

Http://www.cnr.it/ontology/cnr/pubblicazioni.owl#isbn

• 92-9092-898-0 (literal)

Http://www.cnr.it/ontology/cnr/pubblicazioni.owl#curatoriVolume

• D. Danesy (literal)

Abstract

• De-orbiting devices based on the use of conducting tethers have been recently proposed as innovative solutions to mitigate the growth of orbital debris. Electrodynamic tether drag might actually provide a cost-effective method to rapidly and safely remove spent upper stages and defunct satellites from low Earth orbits. However, because of their small diameter, tethers of normal design may have a high probability of being severed by impacts with relatively small meteoroids and orbital debris. In order to assess the vulnerability of electrodynamic tether systems during typical de-orbiting missions, specific work has been carried out at ISTI/CNR (Pisa, Italy) and Kyushu University (Fukuoka, Japan) over the last few years, and suitable models and methods have been specifically developed for the analysis of single and double line tethers in circular orbit and aligned along the gravity gradient. The purpose of this paper is to present the two different approaches, which have been applied to realistic de-orbiting missions of spacecraft with inclinations up to about 75 deg and initial altitudes up to 1400 km. (literal)

Editore

• ESA Publications Division (Editore)

Prodotto di

• Modelli matematici e metodi numerici per la dinamica del volo e la meccanica dei solidi (ICT.P11.006.001) (Modulo)
• Istituto di scienza e tecnologie dell'informazione \"Alessandro Faedo\" (ISTI) (Istituto)

Autore CNR

• LUCIANO ANSELMO (Unità di personale interno)
• CARMEN PARDINI (Unità di personale interno)

Insieme di parole chiave

• Parole chiave di "Assessing the vulnerability to debris impacts of electrodynamic tethers during typical de-orbiting missions" (Insieme di parole chiave)

Incoming links:

Prodotto

• Istituto di scienza e tecnologie dell'informazione \"Alessandro Faedo\" (ISTI) (Istituto)
• Modelli matematici e metodi numerici per la dinamica del volo e la meccanica dei solidi (ICT.P11.006.001) (Modulo)

Autore CNR di

• CARMEN PARDINI (Unità di personale interno)
• LUCIANO ANSELMO (Unità di personale interno)

Editore di

• ESA Publications Division (Editore)

Insieme di parole chiave di

• Parole chiave di "Assessing the vulnerability to debris impacts of electrodynamic tethers during typical de-orbiting missions" (Insieme di parole chiave)