Descripción
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The extension of DROMO formulation to relative motion is evaluated. The orbit of the follower spacecraft can be constructed through differences on the elements defining the orbit of the leader spacecraft. Assuming that the differences are small, the problemis linearized. Typical linearized solutions to relativemotion determine the relative state of the follower spacecraft at a certain time step. Because of the form of DROMO formulation, the performance of a frozen-anomaly transformation is explored. In this case, the relative state is computed for a certain value of the anomaly, equal for leader and follower. Since the time for leader and follower do not coincide, the implicit time delay needs to be corrected to recover the physical sense of the solution. When determining the relative orbit, numerical testing shows significant error reductions compared to previous linearized solutions. | |
Internacional
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Si |
Nombre congreso
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24th AAS/AIAA Space Flight Mechanics Meeting |
Tipo de participación
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960 |
Lugar del congreso
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Santa Fe, New Mexico (EEUU) |
Revisores
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Si |
ISBN o ISSN
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978-0-87703-611-1 |
DOI
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Fecha inicio congreso
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26/01/2014 |
Fecha fin congreso
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30/01/2014 |
Desde la página
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2531 |
Hasta la página
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2546 |
Título de las actas
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SpaceFlight Mechanics 2014 (Volume 152 in the Advances in the Astronautical Sciences Series) |