The elliptic-bi-parabolic planar transfer for artificial satellites
The "elliptic-bi-parabolic transfer" orbit for an artificial satellite is an extension of the bi-parabolic transfer that uses a Swing-By with a natural satellite of the main body to reduce the amount of fuel required by the maneuver. The objective is to find the minimum cost trajectory, in terms of fuel consumed, to transfer a spacecraft from a parking orbit around a planet to an orbit around a natural satellite of this planet or to a higher orbit around the planet. Graphics are built to show in more details the potential savings given by this technique. After that, the idea of using a natural satellite in the maneuver is applied to the problem of making a spacecraft to escape from the main planet to the interplanetary space with maximum velocity at infinity.
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| Format: | Digital revista |
| Language: | English |
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Associação Brasileira de Engenharia e Ciências Mecânicas - ABCM
2003
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| Online Access: | http://old.scielo.br/scielo.php?script=sci_arttext&pid=S1678-58782003000200003 |
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