Assessing the vulnerability to debris impacts of electrodynamic tethers during typical de-orbiting missions

C. Pardini, L. Anselmo, T. Hanada, H. Hirayama

研究成果: ジャーナルへの寄稿会議記事査読

10 被引用数 (Scopus)

抄録

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.

本文言語英語
ページ(範囲)353-360
ページ数8
ジャーナルEuropean Space Agency, (Special Publication) ESA SP
587
出版ステータス出版済み - 8月 2005
イベント4th European Conference on Space Debris - Darmstadt, ドイツ
継続期間: 4月 18 20054月 20 2005

!!!All Science Journal Classification (ASJC) codes

  • 航空宇宙工学
  • 宇宙惑星科学

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