On non-coplanar Hohmann transfer using angles as parameters
Author
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Rincón Rivero, Ángel
Author
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Rojo Rubke, Ángel
Author
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Lacruz, Elvis
Author
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Abellán, Gabriel
Author
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Díaz, Sttiwuer
Admission date
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2015-11-13T14:11:16Z
Available date
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2015-11-13T14:11:16Z
Publication date
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2015
Cita de ítem
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Astrophys Space Sci (2015) 359:6
en_US
Identifier
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DOI 10.1007/s10509-015-2463-8
Identifier
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https://repositorio.uchile.cl/handle/2250/135084
General note
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Artículo de publicación ISI
en_US
Abstract
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We study a more complex case of Hohmann orbital
transfer of a satellite by considering non-coplanar and
elliptical orbits, instead of planar and circular orbits. We use
as parameter the angle between the initial and transference
planes that minimizes the energy, and therefore the fuel of a
satellite, through the application of two non-tangential impulses
for all possible cases. We found an analytical expression
that minimizes the energy for each configuration. Some
reasonable physical constraints are used: we apply impulses
at perigee or apogee of the orbit, we consider the duration of
the impulse to be short compared to the duration of the trip,
we take the nodal line of three orbits to be coincident and
the three semimajor axes to lie in the same plane. We study
the only four possible cases but assuming non-coplanar elliptic
orbits. In addition, we validate our method through a
numerical solution obtained by using some of the actual orbital
elements of Sputnik I and Vanguard I satellites. For
these orbits, we found that the most fuel-efficient transfer
is obtained by applying the initial impulse at apocenter and
keeping the transfer orbit aligned with the initial orbit.