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Descripción
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| A general mathematical framework is presented to treat low thrust trajectory optimization problems using the indirect method and employing a generic set of orbital elements (e.g. classical elements, equinoctial, etc.). An algebraic manipulation of the optimality conditions stemming from Pontryagin Maximum Principle reveals the existence of a new quadratic form of the costate, which governs the costate contribution in all the equations of the first order necessary optimality conditions. The quadratic form provides a simple tool for the mathematical development of the optimality conditions for any chosen set of orbital elements and greatly simplifies the computation of a state transition matrix needed in order to improve the convergence of the associated two-point boundary value problem. Objective functions corresponding to minimum-time, minimum-energy and minimum-fuel problems are considered. | |
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Internacional
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Si |
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Nombre congreso
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26th International Symposium on Space Flight Dynamics (ISSFD) |
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Tipo de participación
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960 |
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Lugar del congreso
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Matsuyama, Japón |
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Revisores
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Si |
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ISBN o ISSN
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DOI
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Fecha inicio congreso
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03/06/2017 |
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Fecha fin congreso
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09/06/2017 |
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Desde la página
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1 |
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Hasta la página
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6 |
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Título de las actas
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