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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 propulsive capabilities and systems constraints. Low-energy asteroid flyby tr...
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| Published in: | Acta astronautica 2020-02, Vol.167, p.146-163 |
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| Language: | English |
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| cited_by | cdi_FETCH-LOGICAL-c458t-adb9662a74a3787159c725723d373a90917b07acc495e299edbb0658e91324873 |
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| cites | cdi_FETCH-LOGICAL-c458t-adb9662a74a3787159c725723d373a90917b07acc495e299edbb0658e91324873 |
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| container_title | Acta astronautica |
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| creator | Machuca, P. Sánchez, J.P. Masdemont, J.J. Gómez, G. |
| 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 propulsive 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 available ΔV 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 the ΔV 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-thrust ΔV requirements, however, may differ significantly from the impulsive results (±15 m/s).
•Asteroid flyby opportunities using CubeSats are common despite their limitations.•ΔV costs below 80 m/s are possible if deployed around the Sun-Earth Lagrange points.•CR3BP is an effective tool to identify target asteroids and estimate ephemeris cost.•Non-impulsive ΔV cost is accurately approximated by an impulsive maneuver model.•Low-thrust ΔV cost can be approximated by an impulsive maneuver model within 15 m/s. |
| doi_str_mv | 10.1016/j.actaastro.2019.09.041 |
| format | article |
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•Asteroid flyby opportunities using CubeSats are common despite their limitations.•ΔV costs below 80 m/s are possible if deployed around the Sun-Earth Lagrange points.•CR3BP is an effective tool to identify target asteroids and estimate ephemeris cost.•Non-impulsive ΔV cost is accurately approximated by an impulsive maneuver model.•Low-thrust ΔV cost can be approximated by an impulsive maneuver model within 15 m/s.</description><identifier>ISSN: 0094-5765</identifier><identifier>EISSN: 1879-2030</identifier><identifier>DOI: 10.1016/j.actaastro.2019.09.041</identifier><language>eng</language><publisher>Elmsford: Elsevier Ltd</publisher><subject>Asteroid missions ; Asteroids ; Computation ; Cubesat ; Flyby missions ; Interplanetary CubeSats ; Lagrangian equilibrium points ; Low-thrust trajectories ; Model accuracy ; Near-Earth asteroids ; Near-Earth Objects ; Space missions ; Sun-Earth Lagrange points ; Three body problem ; Trajectory design ; Voyager 1 spacecraft</subject><ispartof>Acta astronautica, 2020-02, Vol.167, p.146-163</ispartof><rights>2019 IAA</rights><rights>Copyright Elsevier BV Feb 2020</rights><lds50>peer_reviewed</lds50><oa>free_for_read</oa><woscitedreferencessubscribed>false</woscitedreferencessubscribed><citedby>FETCH-LOGICAL-c458t-adb9662a74a3787159c725723d373a90917b07acc495e299edbb0658e91324873</citedby><cites>FETCH-LOGICAL-c458t-adb9662a74a3787159c725723d373a90917b07acc495e299edbb0658e91324873</cites></display><links><openurl>$$Topenurl_article</openurl><openurlfulltext>$$Topenurlfull_article</openurlfulltext><thumbnail>$$Tsyndetics_thumb_exl</thumbnail><link.rule.ids>315,786,790,27957,27958</link.rule.ids></links><search><creatorcontrib>Machuca, P.</creatorcontrib><creatorcontrib>Sánchez, J.P.</creatorcontrib><creatorcontrib>Masdemont, J.J.</creatorcontrib><creatorcontrib>Gómez, G.</creatorcontrib><title>High-fidelity trajectory design to flyby near-Earth asteroids using CubeSats</title><title>Acta astronautica</title><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 propulsive 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 available ΔV 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 the ΔV 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-thrust ΔV requirements, however, may differ significantly from the impulsive results (±15 m/s).
•Asteroid flyby opportunities using CubeSats are common despite their limitations.•ΔV costs below 80 m/s are possible if deployed around the Sun-Earth Lagrange points.•CR3BP is an effective tool to identify target asteroids and estimate ephemeris cost.•Non-impulsive ΔV cost is accurately approximated by an impulsive maneuver model.•Low-thrust ΔV cost can be approximated by an impulsive maneuver model within 15 m/s.</description><subject>Asteroid missions</subject><subject>Asteroids</subject><subject>Computation</subject><subject>Cubesat</subject><subject>Flyby missions</subject><subject>Interplanetary CubeSats</subject><subject>Lagrangian equilibrium points</subject><subject>Low-thrust trajectories</subject><subject>Model accuracy</subject><subject>Near-Earth asteroids</subject><subject>Near-Earth Objects</subject><subject>Space missions</subject><subject>Sun-Earth Lagrange points</subject><subject>Three body problem</subject><subject>Trajectory design</subject><subject>Voyager 1 spacecraft</subject><issn>0094-5765</issn><issn>1879-2030</issn><fulltext>true</fulltext><rsrctype>article</rsrctype><creationdate>2020</creationdate><recordtype>article</recordtype><recordid>eNqFkF1LwzAUhoMoOKe_wYDXnSdfTXM5xnTCwAv1OqRJuqXMdiap0H9vx8Rb4YVz835wHoTuCSwIkPKxXRibjUk59gsKRC1gEicXaEYqqQoKDC7RDEDxQshSXKOblFoAkLRSM7TdhN2-aILzh5BHnKNpvc19HLHzKew6nHvcHMZ6xJ03sVibmPd4GvOxDy7hIYVuh1dD7d9MTrfoqjGH5O9-7xx9PK3fV5ti-_r8slpuC8tFlQvjalWW1EhumKwkEcpKKiRljklmFCgia5DGWq6Ep0p5V9dQisorwiivJJujh3PvMfZfg09Zt_0Qu2lSUyYU46QsYXLJs8vGPqXoG32M4dPEURPQJ3S61X_o9AmdhkmcTMnlOemnJ76DjzrZ4DvrXYgTHe368G_HD2suezU</recordid><startdate>202002</startdate><enddate>202002</enddate><creator>Machuca, P.</creator><creator>Sánchez, J.P.</creator><creator>Masdemont, J.J.</creator><creator>Gómez, G.</creator><general>Elsevier Ltd</general><general>Elsevier BV</general><scope>AAYXX</scope><scope>CITATION</scope><scope>7TB</scope><scope>7TG</scope><scope>8FD</scope><scope>FR3</scope><scope>H8D</scope><scope>KL.</scope><scope>L7M</scope></search><sort><creationdate>202002</creationdate><title>High-fidelity trajectory design to flyby near-Earth asteroids using CubeSats</title><author>Machuca, P. ; Sánchez, J.P. ; Masdemont, J.J. ; Gómez, G.</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-LOGICAL-c458t-adb9662a74a3787159c725723d373a90917b07acc495e299edbb0658e91324873</frbrgroupid><rsrctype>articles</rsrctype><prefilter>articles</prefilter><language>eng</language><creationdate>2020</creationdate><topic>Asteroid missions</topic><topic>Asteroids</topic><topic>Computation</topic><topic>Cubesat</topic><topic>Flyby missions</topic><topic>Interplanetary CubeSats</topic><topic>Lagrangian equilibrium points</topic><topic>Low-thrust trajectories</topic><topic>Model accuracy</topic><topic>Near-Earth asteroids</topic><topic>Near-Earth Objects</topic><topic>Space missions</topic><topic>Sun-Earth Lagrange points</topic><topic>Three body problem</topic><topic>Trajectory design</topic><topic>Voyager 1 spacecraft</topic><toplevel>peer_reviewed</toplevel><toplevel>online_resources</toplevel><creatorcontrib>Machuca, P.</creatorcontrib><creatorcontrib>Sánchez, J.P.</creatorcontrib><creatorcontrib>Masdemont, J.J.</creatorcontrib><creatorcontrib>Gómez, G.</creatorcontrib><collection>CrossRef</collection><collection>Mechanical & Transportation Engineering Abstracts</collection><collection>Meteorological & Geoastrophysical Abstracts</collection><collection>Technology Research Database</collection><collection>Engineering Research Database</collection><collection>Aerospace Database</collection><collection>Meteorological & Geoastrophysical Abstracts - Academic</collection><collection>Advanced Technologies Database with Aerospace</collection><jtitle>Acta astronautica</jtitle></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext</fulltext></delivery><addata><au>Machuca, P.</au><au>Sánchez, J.P.</au><au>Masdemont, J.J.</au><au>Gómez, G.</au><format>journal</format><genre>article</genre><ristype>JOUR</ristype><atitle>High-fidelity trajectory design to flyby near-Earth asteroids using CubeSats</atitle><jtitle>Acta astronautica</jtitle><date>2020-02</date><risdate>2020</risdate><volume>167</volume><spage>146</spage><epage>163</epage><pages>146-163</pages><issn>0094-5765</issn><eissn>1879-2030</eissn><abstract>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 propulsive 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 available ΔV 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 the ΔV 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-thrust ΔV requirements, however, may differ significantly from the impulsive results (±15 m/s).
•Asteroid flyby opportunities using CubeSats are common despite their limitations.•ΔV costs below 80 m/s are possible if deployed around the Sun-Earth Lagrange points.•CR3BP is an effective tool to identify target asteroids and estimate ephemeris cost.•Non-impulsive ΔV cost is accurately approximated by an impulsive maneuver model.•Low-thrust ΔV cost can be approximated by an impulsive maneuver model within 15 m/s.</abstract><cop>Elmsford</cop><pub>Elsevier Ltd</pub><doi>10.1016/j.actaastro.2019.09.041</doi><tpages>18</tpages><oa>free_for_read</oa></addata></record> |
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| source | ScienceDirect Journals |
| subjects | Asteroid missions Asteroids Computation Cubesat Flyby missions Interplanetary CubeSats Lagrangian equilibrium points Low-thrust trajectories Model accuracy Near-Earth asteroids Near-Earth Objects Space missions Sun-Earth Lagrange points Three body problem Trajectory design Voyager 1 spacecraft |
| title | High-fidelity trajectory design to flyby near-Earth asteroids using CubeSats |
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