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

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

Description

Title: Trade-off study on deorbiting S/C in near polar orbit
Author/s:
  • Sanmartín Losada, Juan Ramón
  • Ahedo Galilea, Eduardo
Item Type: Presentation at Congress or Conference (Article)
Event Title: 38th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit
Event Dates: 7 - 10 Jul 2002
Event Location: Indianapolis, Indiana
Title of Book: AIAA/ASME/SAE/ASEE 38th Joint Propulsion Conference and Exhibit: : proceedings of the conference
Date: 2002
ISBN: 978-1-62410-115-1
Subjects:
Faculty: E.T.S.I. Aeronáuticos (UPM)
Department: Física Aplicada a la Ingeniería Aeronáutica [hasta 2014]
Creative Commons Licenses: Recognition - No derivative works - Non commercial

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Abstract

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.

More information

Item ID: 31146
DC Identifier: http://oa.upm.es/31146/
OAI Identifier: oai:oa.upm.es:31146
Deposited by: Biblioteca ETSI Aeronauticos
Deposited on: 01 Oct 2014 13:23
Last Modified: 01 Oct 2014 13:23
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