Libration Transfer Design Using Patched Elliptic Three-Body Models and Graphics Processing Units

Design of the transfer from lunar orbits to the sun-Earth libration point region by direct searching in the high-fidelity ephemeris model is an accurate but time-consuming practice. A computationally efficient methodology that takes advantage of the patched elliptic restricted three-body problem mod...
Ausführliche Beschreibung

Gespeichert in:

Autor*in:	Hao Peng [verfasserIn] Xiaoli Bai Josep J Masdemont Gerard Gómez Shijie Xu

Format:	Artikel
Sprache:	Englisch

Erschienen:	2017

Schlagwörter:	Earth orbits Graphics boards Chinese spacecraft Mathematical models Graphics processing units Lunar orbits Libration Parallel processing Lunar exploration Space missions Three body problem

Übergeordnetes Werk:	Enthalten in: Journal of guidance, control, and dynamics - New York, NY, 1982, 40(2017), 12, Seite 1
Übergeordnetes Werk:	volume:40 ; year:2017 ; number:12 ; pages:1

Links:	Volltext Link aufrufen Link aufrufen

DOI / URN:	10.2514/1.G002692

Katalog-ID:	OLC1998843947

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520			\|a Design of the transfer from lunar orbits to the sun-Earth libration point region by direct searching in the high-fidelity ephemeris model is an accurate but time-consuming practice. A computationally efficient methodology that takes advantage of the patched elliptic restricted three-body problem model, the power of graphics processing unit parallel computing, and the programming platform of MATLAB is presented. Taking the CHANG'E-2 extension mission as an instance, the proposed implementation obtains almost identical results with that in the ephemeris model and shows significant speedup. Moreover, the methodology can be carried out on inexpensive hardware platforms. Numerical results demonstrate that significant speedups can be achieved using the graphics processing unit parallel computing when compared to solving the same problem on the central processing unit.
650		4	\|a Earth orbits
650		4	\|a Graphics boards
650		4	\|a Chinese spacecraft
650		4	\|a Mathematical models
650		4	\|a Graphics processing units
650		4	\|a Lunar orbits
650		4	\|a Libration
650		4	\|a Parallel processing
650		4	\|a Lunar exploration
650		4	\|a Space missions
650		4	\|a Three body problem
700	0		\|a Xiaoli Bai \|4 oth
700	0		\|a Josep J Masdemont \|4 oth
700	0		\|a Gerard Gómez \|4 oth
700	0		\|a Shijie Xu \|4 oth
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spelling	10.2514/1.G002692 doi PQ20171228 (DE-627)OLC1998843947 (DE-599)GBVOLC1998843947 (PRQ)p1142-5c30654a37a71e6eced5371b40c79d7dfbe864e09e1d1c78526681fdbaf934310 (KEY)0032738720170000040001200001librationtransferdesignusingpatchedellipticthreebo DE-627 ger DE-627 rakwb eng 380 DNB Hao Peng verfasserin aut Libration Transfer Design Using Patched Elliptic Three-Body Models and Graphics Processing Units 2017 Text txt rdacontent ohne Hilfsmittel zu benutzen n rdamedia Band nc rdacarrier Design of the transfer from lunar orbits to the sun-Earth libration point region by direct searching in the high-fidelity ephemeris model is an accurate but time-consuming practice. A computationally efficient methodology that takes advantage of the patched elliptic restricted three-body problem model, the power of graphics processing unit parallel computing, and the programming platform of MATLAB is presented. Taking the CHANG'E-2 extension mission as an instance, the proposed implementation obtains almost identical results with that in the ephemeris model and shows significant speedup. Moreover, the methodology can be carried out on inexpensive hardware platforms. Numerical results demonstrate that significant speedups can be achieved using the graphics processing unit parallel computing when compared to solving the same problem on the central processing unit. Earth orbits Graphics boards Chinese spacecraft Mathematical models Graphics processing units Lunar orbits Libration Parallel processing Lunar exploration Space missions Three body problem Xiaoli Bai oth Josep J Masdemont oth Gerard Gómez oth Shijie Xu oth Enthalten in Journal of guidance, control, and dynamics New York, NY, 1982 40(2017), 12, Seite 1 (DE-627)130551910 (DE-600)782987-5 (DE-576)016107497 0731-5090 nnns volume:40 year:2017 number:12 pages:1 http://dx.doi.org/10.2514/1.G002692 Volltext https://search.proquest.com/docview/1929038100 https://search.proquest.com/docview/1978761922 GBV_USEFLAG_A SYSFLAG_A GBV_OLC SSG-OLC-TEC GBV_ILN_70 GBV_ILN_4046 GBV_ILN_4700 AR 40 2017 12 1
allfields_unstemmed	10.2514/1.G002692 doi PQ20171228 (DE-627)OLC1998843947 (DE-599)GBVOLC1998843947 (PRQ)p1142-5c30654a37a71e6eced5371b40c79d7dfbe864e09e1d1c78526681fdbaf934310 (KEY)0032738720170000040001200001librationtransferdesignusingpatchedellipticthreebo DE-627 ger DE-627 rakwb eng 380 DNB Hao Peng verfasserin aut Libration Transfer Design Using Patched Elliptic Three-Body Models and Graphics Processing Units 2017 Text txt rdacontent ohne Hilfsmittel zu benutzen n rdamedia Band nc rdacarrier Design of the transfer from lunar orbits to the sun-Earth libration point region by direct searching in the high-fidelity ephemeris model is an accurate but time-consuming practice. A computationally efficient methodology that takes advantage of the patched elliptic restricted three-body problem model, the power of graphics processing unit parallel computing, and the programming platform of MATLAB is presented. Taking the CHANG'E-2 extension mission as an instance, the proposed implementation obtains almost identical results with that in the ephemeris model and shows significant speedup. Moreover, the methodology can be carried out on inexpensive hardware platforms. Numerical results demonstrate that significant speedups can be achieved using the graphics processing unit parallel computing when compared to solving the same problem on the central processing unit. Earth orbits Graphics boards Chinese spacecraft Mathematical models Graphics processing units Lunar orbits Libration Parallel processing Lunar exploration Space missions Three body problem Xiaoli Bai oth Josep J Masdemont oth Gerard Gómez oth Shijie Xu oth Enthalten in Journal of guidance, control, and dynamics New York, NY, 1982 40(2017), 12, Seite 1 (DE-627)130551910 (DE-600)782987-5 (DE-576)016107497 0731-5090 nnns volume:40 year:2017 number:12 pages:1 http://dx.doi.org/10.2514/1.G002692 Volltext https://search.proquest.com/docview/1929038100 https://search.proquest.com/docview/1978761922 GBV_USEFLAG_A SYSFLAG_A GBV_OLC SSG-OLC-TEC GBV_ILN_70 GBV_ILN_4046 GBV_ILN_4700 AR 40 2017 12 1
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allfieldsSound	10.2514/1.G002692 doi PQ20171228 (DE-627)OLC1998843947 (DE-599)GBVOLC1998843947 (PRQ)p1142-5c30654a37a71e6eced5371b40c79d7dfbe864e09e1d1c78526681fdbaf934310 (KEY)0032738720170000040001200001librationtransferdesignusingpatchedellipticthreebo DE-627 ger DE-627 rakwb eng 380 DNB Hao Peng verfasserin aut Libration Transfer Design Using Patched Elliptic Three-Body Models and Graphics Processing Units 2017 Text txt rdacontent ohne Hilfsmittel zu benutzen n rdamedia Band nc rdacarrier Design of the transfer from lunar orbits to the sun-Earth libration point region by direct searching in the high-fidelity ephemeris model is an accurate but time-consuming practice. A computationally efficient methodology that takes advantage of the patched elliptic restricted three-body problem model, the power of graphics processing unit parallel computing, and the programming platform of MATLAB is presented. Taking the CHANG'E-2 extension mission as an instance, the proposed implementation obtains almost identical results with that in the ephemeris model and shows significant speedup. Moreover, the methodology can be carried out on inexpensive hardware platforms. Numerical results demonstrate that significant speedups can be achieved using the graphics processing unit parallel computing when compared to solving the same problem on the central processing unit. Earth orbits Graphics boards Chinese spacecraft Mathematical models Graphics processing units Lunar orbits Libration Parallel processing Lunar exploration Space missions Three body problem Xiaoli Bai oth Josep J Masdemont oth Gerard Gómez oth Shijie Xu oth Enthalten in Journal of guidance, control, and dynamics New York, NY, 1982 40(2017), 12, Seite 1 (DE-627)130551910 (DE-600)782987-5 (DE-576)016107497 0731-5090 nnns volume:40 year:2017 number:12 pages:1 http://dx.doi.org/10.2514/1.G002692 Volltext https://search.proquest.com/docview/1929038100 https://search.proquest.com/docview/1978761922 GBV_USEFLAG_A SYSFLAG_A GBV_OLC SSG-OLC-TEC GBV_ILN_70 GBV_ILN_4046 GBV_ILN_4700 AR 40 2017 12 1
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author	Hao Peng
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title_auth	Libration Transfer Design Using Patched Elliptic Three-Body Models and Graphics Processing Units
abstract	Design of the transfer from lunar orbits to the sun-Earth libration point region by direct searching in the high-fidelity ephemeris model is an accurate but time-consuming practice. A computationally efficient methodology that takes advantage of the patched elliptic restricted three-body problem model, the power of graphics processing unit parallel computing, and the programming platform of MATLAB is presented. Taking the CHANG'E-2 extension mission as an instance, the proposed implementation obtains almost identical results with that in the ephemeris model and shows significant speedup. Moreover, the methodology can be carried out on inexpensive hardware platforms. Numerical results demonstrate that significant speedups can be achieved using the graphics processing unit parallel computing when compared to solving the same problem on the central processing unit.
abstractGer	Design of the transfer from lunar orbits to the sun-Earth libration point region by direct searching in the high-fidelity ephemeris model is an accurate but time-consuming practice. A computationally efficient methodology that takes advantage of the patched elliptic restricted three-body problem model, the power of graphics processing unit parallel computing, and the programming platform of MATLAB is presented. Taking the CHANG'E-2 extension mission as an instance, the proposed implementation obtains almost identical results with that in the ephemeris model and shows significant speedup. Moreover, the methodology can be carried out on inexpensive hardware platforms. Numerical results demonstrate that significant speedups can be achieved using the graphics processing unit parallel computing when compared to solving the same problem on the central processing unit.
abstract_unstemmed	Design of the transfer from lunar orbits to the sun-Earth libration point region by direct searching in the high-fidelity ephemeris model is an accurate but time-consuming practice. A computationally efficient methodology that takes advantage of the patched elliptic restricted three-body problem model, the power of graphics processing unit parallel computing, and the programming platform of MATLAB is presented. Taking the CHANG'E-2 extension mission as an instance, the proposed implementation obtains almost identical results with that in the ephemeris model and shows significant speedup. Moreover, the methodology can be carried out on inexpensive hardware platforms. Numerical results demonstrate that significant speedups can be achieved using the graphics processing unit parallel computing when compared to solving the same problem on the central processing unit.
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title_short	Libration Transfer Design Using Patched Elliptic Three-Body Models and Graphics Processing Units
url	http://dx.doi.org/10.2514/1.G002692 https://search.proquest.com/docview/1929038100 https://search.proquest.com/docview/1978761922
remote_bool	false
author2	Xiaoli Bai Josep J Masdemont Gerard Gómez Shijie Xu
author2Str	Xiaoli Bai Josep J Masdemont Gerard Gómez Shijie Xu
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author2_role	oth oth oth oth
doi_str	10.2514/1.G002692
up_date	2024-07-04T05:50:15.576Z
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