Descripción
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The minimum-time, low-constant-thrust, same circular orbit rendezvous problem is studied using a relative motion description of the system dynamics. The resulting Optimal Control Problem in the thrust orientation angle is formulated using both the Direct and Indirect method. An extensive set of test cases is numerically solved with the former, while perturbation techniques applied to the later allow to obtain several approximate solutions and provide a greater insight on the underlying physics. These results show that the structure of the solutions undergoes fundamental changes depending on the value of the non-dimensional thrust parameter.missions. To this end, an optimal control formulation based in Dromo and a direct transcription method is used to solve several LEO-GEO and escape from Earth problems; the obtained results clearly show the suitability of this orbital propagation for such purposes. | |
Internacional
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Si |
Nombre congreso
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25th AAS/AIAA Space Flight Mechanics Meeting |
Tipo de participación
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960 |
Lugar del congreso
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Williamsburg, Virginia (EEUU) |
Revisores
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Si |
ISBN o ISSN
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1081-6003 |
DOI
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Fecha inicio congreso
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11/01/2015 |
Fecha fin congreso
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15/01/2015 |
Desde la página
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1783 |
Hasta la página
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1801 |
Título de las actas
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Advances in the Astronautical Sciences Volume 155, Spaceflight Mechanics Subseries |