It has been recently suggested that conductive tethers, besides other applications, may be effective for the de-orbiting of satellites at the end of their operational life. In this paper we give a preliminary evaluation of this capability with respect to a well-defined tether system and using the expertise and results from the recently flown TSS-1 project. The system considered is a long conducting tether, covered by an insulator, with a passive electron collector at the positive termination and a hollow-cathode electron emitter at the opposite end. In analyzing this system, we point out the crucial importance of the contact impedances associated to the coupling between the tether terminations and the ionospheric plasma. We give a first evaluation of the de-orbiting time for a typical case and conclude about feasibility of a tether system to de-orbit satellites.
Satellite deorbiting by means of electrodynamic tethers: general concepts and requirements / Iess, Luciano; Bruno, Claudio; Ulivieri, Carlo; Vannaroni, G.; Bertotti, B.; Anselmo, L.; Ponzi, Ugo; Dobrowolny, M.; VENUTO F, De; Parisse, Maurizio; Laneve, Giovanni. - STAMPA. - (1998), pp. 1-4. (Intervento presentato al convegno 49th International Astronautical Congress tenutosi a Melbourne).
Satellite deorbiting by means of electrodynamic tethers: general concepts and requirements
IESS, Luciano
Membro del Collaboration Group
;BRUNO, ClaudioMembro del Collaboration Group
;ULIVIERI, CarloMembro del Collaboration Group
;PONZI, UgoMembro del Collaboration Group
;PARISSE, MaurizioMembro del Collaboration Group
;LANEVE, GiovanniMembro del Collaboration Group
1998
Abstract
It has been recently suggested that conductive tethers, besides other applications, may be effective for the de-orbiting of satellites at the end of their operational life. In this paper we give a preliminary evaluation of this capability with respect to a well-defined tether system and using the expertise and results from the recently flown TSS-1 project. The system considered is a long conducting tether, covered by an insulator, with a passive electron collector at the positive termination and a hollow-cathode electron emitter at the opposite end. In analyzing this system, we point out the crucial importance of the contact impedances associated to the coupling between the tether terminations and the ionospheric plasma. We give a first evaluation of the de-orbiting time for a typical case and conclude about feasibility of a tether system to de-orbit satellites.I documenti in IRIS sono protetti da copyright e tutti i diritti sono riservati, salvo diversa indicazione.