Libration control of electrodynamic tethers using the extended time-delayed autosynchronization method

Iñarrea, M. and Pelaez Alvarez, Jesus (2007). Libration control of electrodynamic tethers using the extended time-delayed autosynchronization method. In: "17th AAS/AIAA Space Flight Mechanics Meeting", 28 ene - 1 feb 2007, Sedona, Arizona. ISBN 9780080564050. pp. 1393-1408.

Description

Title: Libration control of electrodynamic tethers using the extended time-delayed autosynchronization method
Author/s:
  • Iñarrea, M.
  • Pelaez Alvarez, Jesus
Item Type: Presentation at Congress or Conference (Article)
Event Title: 17th AAS/AIAA Space Flight Mechanics Meeting
Event Dates: 28 ene - 1 feb 2007
Event Location: Sedona, Arizona
Title of Book: 2007 AAS/AIAA >Space Flight Mechanics Meeting
Date: January 2007
ISBN: 9780080564050
Volume: 127
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

Any electrodynamic tether working in an inclined orbit is affected by a dynamic instability generated by the continuous pumping of energy from electromagnetic forces into the tether attitude motion. In order to overcome the difficulties associated with this instability, a new control scheme has been analyzed in this paper. The background strategy is as follows: we add appropriate forces to the system with the aim of converting an unstable periodic orbit of the governing equations into an asymptotically stable one. The idea is to take such a stabilized periodic orbit as the starting point for the operation of the electrodynamic tether. We use an extended delay feedback control scheme which has been used successfully in problems with one degree of freedom. In order to obtain results with broad validity, some simplifying assumptions have been introduced in the analysis. Thus, we assume a rigid tether with two end masses orbiting along a circular, inclined orbit. We also assume a constant tether current which does not depend on the attitude and orbital position of the tether. The Earth’s magnetic field is modeled as a dipole aligned with the Earth’s rotation axis.

Funding Projects

TypeCodeAcronymLeaderTitle
Government of SpainMTM2005-08595UnspecifiedUnspecifiedUnspecified
Government of SpainESP2004-04376UnspecifiedUnspecifiedDynamics of sayellite orbit descent/raise using electrodynamics tethers

More information

Item ID: 52060
DC Identifier: http://oa.upm.es/52060/
OAI Identifier: oai:oa.upm.es:52060
Official URL: https://www.space-flight.org/AAS_meetings/2007_winter/2007_winter.html
Deposited by: Memoria Investigacion
Deposited on: 25 Mar 2019 08:11
Last Modified: 25 Mar 2019 08:11
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