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Libration transfer design using patched elliptic three-body models and graphics processing units

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10.2514/1.G002692
 
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Peng, Hao
Bai, Xiaoli
Masdemont Soler, JosepMés informacióMés informacióMés informació
Gómez Muntané, Gerard
Xu, Shijie
Document typeArticle
Defense date2017-01-01
Rights accessOpen Access
Attribution-NonCommercial-NoDerivs 3.0 Spain
Except where otherwise noted, content on this work is licensed under a Creative Commons license : Attribution-NonCommercial-NoDerivs 3.0 Spain
Abstract
Copyright © 2016 by the American Institute of Aeronautics and Astronautics, Inc. Design of the transfer from lunar orbits to the sun-Earth libration point region by direct searching in the highfidelity 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.
CitationPeng, H., Bai, X., Masdemont, J.J., Gomez Muntané, Gerard, Xu, S. Libration transfer design using patched elliptic three-body models and graphics processing units. "Journal of guidance control and dynamics", 1 Gener 2017, vol. 40, núm. 23, p. 3155-3166. 
URIhttp://hdl.handle.net/2117/112591
DOI10.2514/1.G002692
ISSN0731-5090
Publisher versionhttps://arc.aiaa.org/doi/10.2514/1.G002692
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  • SD - Sistemes Dinàmics de la UPC - Articles de revista [122]
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