Trade-off study on deorbiting S/C in near polar orbit

Sanmartín Losada, Juan Ramón y Ahedo Galilea, Eduardo (2002). Trade-off study on deorbiting S/C in near polar orbit. En: "38th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit", 7 - 10 Jul 2002, Indianapolis, Indiana. ISBN 978-1-62410-115-1.

Descripción

Título: Trade-off study on deorbiting S/C in near polar orbit
Autor/es:
  • Sanmartín Losada, Juan Ramón
  • Ahedo Galilea, Eduardo
Tipo de Documento: Ponencia en Congreso o Jornada (Artículo)
Título del Evento: 38th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit
Fechas del Evento: 7 - 10 Jul 2002
Lugar del Evento: Indianapolis, Indiana
Título del Libro: AIAA/ASME/SAE/ASEE 38th Joint Propulsion Conference and Exhibit: : proceedings of the conference
Fecha: 2002
ISBN: 978-1-62410-115-1
Materias:
Escuela: E.T.S.I. Aeronáuticos (UPM) [antigua denominación]
Departamento: Física Aplicada a la Ingeniería Aeronáutica [hasta 2014]
Licencias Creative Commons: Reconocimiento - Sin obra derivada - No comercial

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Resumen

Usual long, flexible, ED tethers kept vertical by the gravity gradient might be less efficient for deorbiting S/C in near-polar orbits than conventional (Hall, Ion) electrical thrusters. A trade-off study on this application is here presented for tethers kept horizontal and perpendicular to the orbital plane. A tether thus oriented must be rigid and short for structural reasons, requiring a non-convex cross section and a power supply as in the case of electrical thrusters. Very recent developments on bare-tether collection theory allow predicting the current collected by an arbitrary cross section. For the horizontal tether, structural considerations on length play the role of ohmic effects in vertical tethers, in determining the optimal contribution of tether mass to the overall deorbiting system. For a given deorbiting-mission impulse, tether-system mass is minimal at some optimal length that increases weakly with the impulse. The horizontal-tether system may beat both the vertical tether and the electrical thruster as regards mass requirements for a narrow length range centered at about 100 m, allowing, however, for a broad mission-impulse range.

Más información

ID de Registro: 31146
Identificador DC: http://oa.upm.es/31146/
Identificador OAI: oai:oa.upm.es:31146
Depositado por: Biblioteca ETSI Aeronauticos
Depositado el: 01 Oct 2014 13:23
Ultima Modificación: 01 Oct 2014 13:23
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