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Descripción
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| A new code to solve the Kepler equation for elliptic and hyperbolic orbits has been developed. The motivation of the study is the determination of an appropriate seed to initialize the numerical method, considering the optimization already tested of the well-known Newton-Raphson method. To do that, we take advantage of the full potential of the symbolic manipulators. The final algorithm is stable, reliable and solves successfully the solution of the Kepler equation in the singular corner (M << 1 and e close to 1). In most of the cases, the seed generated by the Space Dynamics Group at UPM (SDG-code) leads to reach machine error accuracy with the modified Newton-Raphson methods with no iterations or just one iteration. This approach improves the computational time compared with other methods currently in use. The advantage of our approach is its applicability to other problems as for example the Lambert problem for low thrust trajectories. | |
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Internacional
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Si |
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JCR del ISI
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No |
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Título de la revista
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Advances in the Astronautical Sciences |
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ISSN
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1081-6003 |
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Factor de impacto JCR
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Información de impacto
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SPACEFLIGHT MECHANICS 2017 |
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Volumen
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160 |
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DOI
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Número de revista
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Part-IV |
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Desde la página
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4143 |
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Hasta la página
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4160 |
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Mes
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SIN MES |
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Ranking
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