2019-11-17T02:44:33Z
http://oa.upm.es/cgi/oai2
oai:oa.upm.es:26066
2014-09-22T11:39:39Z
7374617475733D707562
7375626A656374733D6165726F6E617574696361
7375626A656374733D666973696361
747970653D636F6E666572656E63655F6974656D
Tape-tether design for de-orbiting from given altitude and inclination
Sanmartín Losada, Juan Ramón
Sánchez-Torres, Antonio
Khan, S. B.
Sánchez Arriaga, Gonzalo
Charro, Mario
Aeronautics
Physics
The product of the tether-to-satellite mass ratio and the
probability of tether cuts by small debris must be small
to make electrodynamic bare tethers a competitive and
useful de-orbiting technology. In the case of a circular
orbit and assuming a model for the debris population, the
product can be written as a function that just depends
on the initial orbit parameters (altitude and inclination)
and the tether geometry. This formula, which does not
contain the time explicitly and ignores the details of the
tether dynamics during the de-orbiting, is used to find design rules for the tape dimensions and the orbit parameter
ranges where tethers dominate other de-orbiting technologies
like rockets, electrical propulsion, and sails.
E.T.S.I. Aeronáuticos (UPM)
http://creativecommons.org/licenses/by-nc-nd/3.0/es/
2013-04-22
info:eu-repo/semantics/conferenceObject
Presentation at Congress or Conference
Proceedings of the 6th European Conference on Space Debris | 6th European Conference on Space Debris | 22-4-2012/ 25-4-2012 | Darmstadt, Germany
PeerReviewed
application/pdf
eng
info:eu-repo/semantics/openAccess
http://oa.upm.es/26066/