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Descripción
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| The reliable and accurate propagation of interplanetary orbits is of crucial importance in several applications in celestial mechanics and astrodynamics, for example asteroid impact monitoring and mitigation, and interplanetary mission analysis and design. When planetary close encounters are involved, numerical propagation is complicated by the amplification of the numerical error in the position and velocity after the encounter. Therefore, the presence of subsequent encounters (for example resonant returns) makes accurate orbit computation a difficult and challenging task. In this work, we investigate the possibility of reducing global numerical error by employing regularized formulations of orbital dynamics, such as the Dromo formulation. Test cases are performed both for geocentric hyperbolic trajectories and for whole interplanetary trajectories with a resonant close encounter. Results show that Dromo, along with the Kustaanheimo-Stiefel formulation, is able to significantly reduce the propagation error with respect to Cowell?s method. In particular, the addition of a time element to Dromo is highly beneficial in containing the error produced by the integration of time. | |
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Internacional
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Si |
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Nombre congreso
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25th AAS/AIAA Space Flight Mechanics Meeting |
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Tipo de participación
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960 |
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Lugar del congreso
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Williamsburg, Virginia, EE. UU. |
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Revisores
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No |
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ISBN o ISSN
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9780877036234 |
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DOI
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Fecha inicio congreso
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11/01/2015 |
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Fecha fin congreso
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15/01/2015 |
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Desde la página
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1003 |
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Hasta la página
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1020 |
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Título de las actas
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Volume 155 of the Advances in the Astronautical Sciences Series (AAS/AIAA Spaceflight Mechanics Meeting 2015) |