PUMA
Istituto di Scienza e Tecnologie dell'Informazione     
Pardini C., Anselmo L. IADC AI 19.1 on 'Benefits and Risks of using Electrodynamic Tethers to De-Orbit Spacecraft' - Methodology used at ISTI/CNR to Assess the Sever Probability of Space Tethers. In: Inter-Agency Space Debris Coordination Committee Meeting (Abano Terme, Italy, 19-22 April 2004).
 
 
Abstract
(English)
The methods used at ISTI/CNR to compute the fatal impact rate of meteoroids and orbital debris on space tethers and to assess the survival probability of electrodynamic tether systems during a de-orbiting mission are presented. The tethers are supposed to be in circular orbit and aligned along the gravity gradient. Two basically different designs have been considered: 1. Single tether: a single wire or a cylindrical multi- line structure; 2. Double tether: two cables are separated each other by a distance significantly larger than their diameter and form N loops, tied together in N + 1 equidistant knots. In order to assess the survivability of double line tethers, a numerical multi-step algorithm has been specifically developed at ISTI. For a tether at a given orbital altitude, it computes: 1. The sever probability of a single cable; 2. The sever/survival probability of both lines of the same tether segment; 3. The sever/survival probability of the whole tether. Concerning an electrodynamic tether for satellite de-orbiting, its altitude changes during the mission, and with it also the space debris flux. In order to take into account the debris flux variation, as a function of the decreasing altitude, in the survivability assessment, the overall altitude range traversed by the tether is subdivided in a number of altitude intervals, where the space debris flux can be assumed constant. Taking into account that the tether - single or double line - survives during the de-orbiting mission only if it survives in each altitude interval, the overall survival probability during the mission is eventually estimated.
Subject Electrodynamic Tethers
Space Debris
De-Orbiting Missions
Vulnerability of Space Tethers
J.2 Physical Sciences and Engineering


Icona documento 1) Download Document PDF


Icona documento Open access Icona documento Restricted Icona documento Private

 


Per ulteriori informazioni, contattare: Librarian http://puma.isti.cnr.it

Valid HTML 4.0 Transitional