High-fidelity trajectory design to flyby near-earth asteroids using cubesats

Fast development of CubeSat technology now enables the first interplanetary missions. The potential application of CubeSats to flyby near-Earth asteroids is explored in this paper in consideration of CubeSats' limited pro- pulsive capabilities and systems constraints. Low-energy asteroid flyby...

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Detalles Bibliográficos
Autores: Machuca, P., Sánchez, J.P., Masdemont, Josep J., Gómez Muntané, Gerardo
Tipo de recurso: artículo
Estado:Versión aceptada para publicación
Fecha de publicación:2020
País:España
Institución:Universidad de Barcelona
Repositorio:Dipòsit Digital de la UB
OAI Identifier:oai:diposit.ub.edu:2445/194753
Acceso en línea:https://hdl.handle.net/2445/194753
Access Level:acceso abierto
Palabra clave:Satèl·lits artificials
Dinàmica
Artificial satellites
Dynamics
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spelling High-fidelity trajectory design to flyby near-earth asteroids using cubesatsMachuca, P.Sánchez, J.P.Masdemont, Josep J.Gómez Muntané, GerardoSatèl·lits artificialsDinàmicaArtificial satellitesDynamicsFast development of CubeSat technology now enables the first interplanetary missions. The potential application of CubeSats to flyby near-Earth asteroids is explored in this paper in consideration of CubeSats' limited pro- pulsive capabilities and systems constraints. Low-energy asteroid flyby trajectories are designed assuming a CubeSat is initially parked around to the Sun-Earth Lagrange points. High-impulse and low-thrust trajectories with realistic thrusting models are computed first in the Circular Restricted Three-Body Problem (CR3BP), and then in a high-fidelity ephemeris model. Analysis in the ephemeris model is used to confirm that trajectories computed in the CR3BP model also exist in a more realistic dynamical model, and to verify the validity of the results obtained in CR3BP analysis. A catalogue of asteroid flyby opportunities between years 2019 and 2030 is provided, with 80 m/s of availableΔV and departure from halo orbits around the first and second Sun-Earth Lagrange points (of similar size to those typically used by scientific missions). Results show that the CR3BP model can serve as an effective tool to identify reachable asteroids and can provide an initial estimation of the ΔV cost in the ephemeris model (with ± 15 m/s accuracy). An impulsive maneuver model can also provide an accurate estimation of theΔV requirement for a CubeSat equipped with a high-impulse thruster (with 4 m/s accuracy), even if its thrust magnitude is small and requires duty cycling; low-thrustΔV requirements, however, may differ significantly from the impulsive results ( ± 15 m/s).Elsevier Ltd2020info:eu-repo/semantics/articleinfo:eu-repo/semantics/acceptedVersionapplication/pdfhttps://hdl.handle.net/2445/194753Articles publicats en revistes (Matemàtiques i Informàtica)reponame:Dipòsit Digital de la UBinstname:Universidad de BarcelonaInglésVersió postprint del document publicat a: https://doi.org/10.1016/j.actaastro.2019.09.041Acta Astronautica, 2020, vol. 167, p. 146-163https://doi.org/10.1016/j.actaastro.2019.09.041cc-by-nc-nd (c) Elsevier Ltd, 2020https://creativecommons.org/licenses/by-nc-nd/4.0/info:eu-repo/semantics/openAccessoai:diposit.ub.edu:2445/1947532026-05-27T06:46:51Z
dc.title.none.fl_str_mv High-fidelity trajectory design to flyby near-earth asteroids using cubesats
title High-fidelity trajectory design to flyby near-earth asteroids using cubesats
spellingShingle High-fidelity trajectory design to flyby near-earth asteroids using cubesats
Machuca, P.
Satèl·lits artificials
Dinàmica
Artificial satellites
Dynamics
title_short High-fidelity trajectory design to flyby near-earth asteroids using cubesats
title_full High-fidelity trajectory design to flyby near-earth asteroids using cubesats
title_fullStr High-fidelity trajectory design to flyby near-earth asteroids using cubesats
title_full_unstemmed High-fidelity trajectory design to flyby near-earth asteroids using cubesats
title_sort High-fidelity trajectory design to flyby near-earth asteroids using cubesats
dc.creator.none.fl_str_mv Machuca, P.
Sánchez, J.P.
Masdemont, Josep J.
Gómez Muntané, Gerardo
author Machuca, P.
author_facet Machuca, P.
Sánchez, J.P.
Masdemont, Josep J.
Gómez Muntané, Gerardo
author_role author
author2 Sánchez, J.P.
Masdemont, Josep J.
Gómez Muntané, Gerardo
author2_role author
author
author
dc.subject.none.fl_str_mv Satèl·lits artificials
Dinàmica
Artificial satellites
Dynamics
topic Satèl·lits artificials
Dinàmica
Artificial satellites
Dynamics
description Fast development of CubeSat technology now enables the first interplanetary missions. The potential application of CubeSats to flyby near-Earth asteroids is explored in this paper in consideration of CubeSats' limited pro- pulsive capabilities and systems constraints. Low-energy asteroid flyby trajectories are designed assuming a CubeSat is initially parked around to the Sun-Earth Lagrange points. High-impulse and low-thrust trajectories with realistic thrusting models are computed first in the Circular Restricted Three-Body Problem (CR3BP), and then in a high-fidelity ephemeris model. Analysis in the ephemeris model is used to confirm that trajectories computed in the CR3BP model also exist in a more realistic dynamical model, and to verify the validity of the results obtained in CR3BP analysis. A catalogue of asteroid flyby opportunities between years 2019 and 2030 is provided, with 80 m/s of availableΔV and departure from halo orbits around the first and second Sun-Earth Lagrange points (of similar size to those typically used by scientific missions). Results show that the CR3BP model can serve as an effective tool to identify reachable asteroids and can provide an initial estimation of the ΔV cost in the ephemeris model (with ± 15 m/s accuracy). An impulsive maneuver model can also provide an accurate estimation of theΔV requirement for a CubeSat equipped with a high-impulse thruster (with 4 m/s accuracy), even if its thrust magnitude is small and requires duty cycling; low-thrustΔV requirements, however, may differ significantly from the impulsive results ( ± 15 m/s).
publishDate 2020
dc.date.none.fl_str_mv 2020
dc.type.none.fl_str_mv info:eu-repo/semantics/article
info:eu-repo/semantics/acceptedVersion
format article
status_str acceptedVersion
dc.identifier.none.fl_str_mv https://hdl.handle.net/2445/194753
url https://hdl.handle.net/2445/194753
dc.language.none.fl_str_mv Inglés
language_invalid_str_mv Inglés
dc.relation.none.fl_str_mv Versió postprint del document publicat a: https://doi.org/10.1016/j.actaastro.2019.09.041
Acta Astronautica, 2020, vol. 167, p. 146-163
https://doi.org/10.1016/j.actaastro.2019.09.041
dc.rights.none.fl_str_mv cc-by-nc-nd (c) Elsevier Ltd, 2020
https://creativecommons.org/licenses/by-nc-nd/4.0/
info:eu-repo/semantics/openAccess
rights_invalid_str_mv cc-by-nc-nd (c) Elsevier Ltd, 2020
https://creativecommons.org/licenses/by-nc-nd/4.0/
eu_rights_str_mv openAccess
dc.format.none.fl_str_mv application/pdf
dc.publisher.none.fl_str_mv Elsevier Ltd
publisher.none.fl_str_mv Elsevier Ltd
dc.source.none.fl_str_mv Articles publicats en revistes (Matemàtiques i Informàtica)
reponame:Dipòsit Digital de la UB
instname:Universidad de Barcelona
instname_str Universidad de Barcelona
reponame_str Dipòsit Digital de la UB
collection Dipòsit Digital de la UB
repository.name.fl_str_mv
repository.mail.fl_str_mv
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score 15.300719

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