Rapid Evaluation of the Decay Time of a Plasma Brake-Based CubeSat

The plasma brake is a propellantless device conceived for de-orbiting purposes. It consists of an electrically charged thin tether that generates a Coulomb drag by interacting with the ionosphere. In essence, a plasma brake may be used to decelerate an out-of-service satellite and to ensure its atmo...
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Autor*in:	Marco Bassetto [verfasserIn] Lorenzo Niccolai [verfasserIn] Alessandro A. Quarta [verfasserIn] Giovanni Mengali [verfasserIn]

Format:	E-Artikel
Sprache:	Englisch

Erschienen:	2022

Schlagwörter:	plasma brake relative trajectory space debris mitigation

Übergeordnetes Werk:	In: Aerospace - MDPI AG, 2014, 9(2022), 11, p 636
Übergeordnetes Werk:	volume:9 ; year:2022 ; number:11, p 636

Links:	Link aufrufen Link aufrufen Link aufrufen Journal toc

DOI / URN:	10.3390/aerospace9110636

Katalog-ID:	DOAJ085546259

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language	English
source	In Aerospace 9(2022), 11, p 636 volume:9 year:2022 number:11, p 636
sourceStr	In Aerospace 9(2022), 11, p 636 volume:9 year:2022 number:11, p 636
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callnumber-first	T - Technology
author	Marco Bassetto
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topic_title	TL1-4050 Rapid Evaluation of the Decay Time of a Plasma Brake-Based CubeSat plasma brake relative trajectory space debris mitigation
topic	misc TL1-4050 misc plasma brake misc relative trajectory misc space debris mitigation misc Motor vehicles. Aeronautics. Astronautics
topic_unstemmed	misc TL1-4050 misc plasma brake misc relative trajectory misc space debris mitigation misc Motor vehicles. Aeronautics. Astronautics
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title	Rapid Evaluation of the Decay Time of a Plasma Brake-Based CubeSat
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title_auth	Rapid Evaluation of the Decay Time of a Plasma Brake-Based CubeSat
abstract	The plasma brake is a propellantless device conceived for de-orbiting purposes. It consists of an electrically charged thin tether that generates a Coulomb drag by interacting with the ionosphere. In essence, a plasma brake may be used to decelerate an out-of-service satellite and to ensure its atmospheric re-entry within the time limits established by the Inter-Agency Space Debris Coordination Committee. Moreover, since it only needs a small amount of electric power to work properly, the plasma brake is one of the most cost-effective systems for space debris mitigation. This paper exploits a recent plasma brake acceleration model to construct an iterative algorithm for the rapid evaluation of the decay time of a plasma-braked CubeSat, which initially traced a circular low Earth orbit. The altitude loss at the end of each iterative step was calculated using the linearized Hill–Clohessy–Wiltshire equations. It showed that the proposed algorithm, which was validated by comparing the approximate solution with the results from numerically integrating the nonlinear equations of motion, reduced computational time by up to four orders of magnitude with negligible errors in CubeSat position.
abstractGer	The plasma brake is a propellantless device conceived for de-orbiting purposes. It consists of an electrically charged thin tether that generates a Coulomb drag by interacting with the ionosphere. In essence, a plasma brake may be used to decelerate an out-of-service satellite and to ensure its atmospheric re-entry within the time limits established by the Inter-Agency Space Debris Coordination Committee. Moreover, since it only needs a small amount of electric power to work properly, the plasma brake is one of the most cost-effective systems for space debris mitigation. This paper exploits a recent plasma brake acceleration model to construct an iterative algorithm for the rapid evaluation of the decay time of a plasma-braked CubeSat, which initially traced a circular low Earth orbit. The altitude loss at the end of each iterative step was calculated using the linearized Hill–Clohessy–Wiltshire equations. It showed that the proposed algorithm, which was validated by comparing the approximate solution with the results from numerically integrating the nonlinear equations of motion, reduced computational time by up to four orders of magnitude with negligible errors in CubeSat position.
abstract_unstemmed	The plasma brake is a propellantless device conceived for de-orbiting purposes. It consists of an electrically charged thin tether that generates a Coulomb drag by interacting with the ionosphere. In essence, a plasma brake may be used to decelerate an out-of-service satellite and to ensure its atmospheric re-entry within the time limits established by the Inter-Agency Space Debris Coordination Committee. Moreover, since it only needs a small amount of electric power to work properly, the plasma brake is one of the most cost-effective systems for space debris mitigation. This paper exploits a recent plasma brake acceleration model to construct an iterative algorithm for the rapid evaluation of the decay time of a plasma-braked CubeSat, which initially traced a circular low Earth orbit. The altitude loss at the end of each iterative step was calculated using the linearized Hill–Clohessy–Wiltshire equations. It showed that the proposed algorithm, which was validated by comparing the approximate solution with the results from numerically integrating the nonlinear equations of motion, reduced computational time by up to four orders of magnitude with negligible errors in CubeSat position.
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title_short	Rapid Evaluation of the Decay Time of a Plasma Brake-Based CubeSat
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