Descripción
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It has recently been proposed to use bare electrodynamic tethers (EDTs) in connection with nanosatellites, either to provide a cheap test of OML current collection theory or to devise a lightweight deorbiting system for cubesats experiments. In the present article we investigate the orbital evolution of small satellites (1- 5 kg) equipped with electrodynamic tethers of different lengths (100-1000 m) and for different orbital conditions. Tether integration in the microsatellite system and tether deployment is also addressed. Results show that a small dedicated experiment involving one or two cubesat(s) is feasible in favorable conditions with tether length of 100-200m. | |
Internacional
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Si |
Nombre congreso
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20th AAS / AIAA Space Flight Mechanics Meeting |
Tipo de participación
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960 |
Lugar del congreso
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San Diego, California, EE.UU. |
Revisores
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Si |
ISBN o ISSN
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1081-6003 |
DOI
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Fecha inicio congreso
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14/02/2010 |
Fecha fin congreso
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17/02/2010 |
Desde la página
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2515 |
Hasta la página
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2522 |
Título de las actas
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Spaceflight Mechanics 2010, Vol. 136. Part I |