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Descripción
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| This paper faces the design of the trajectory of a tether mission to Saturn. To reduce the hyperbolic excess velocity at arrival to the planet, a gravity assist at Jupiter is included. The Earth-to-Jupiter portion of the transfer is unpropelled. The Jupiter-to-Saturn trajectory has two parts: a first coasting arc followed by a second arc where a low thrust engine is switched on. An optimization process provides the law of thrust control that minimizes the velocity relative to Saturn at arrival, thus facilitating the tethered orbit insertion. | |
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Internacional
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Si |
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JCR del ISI
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Título de la revista
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8TH EUROPEAN CONFERENCE FOR AERONAUTICS AND AEROSPACE SCIENCES (EUCASS) |
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Volumen
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DOI
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Desde la página
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1 |
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Hasta la página
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15 |
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Mes
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SIN MES |
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