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Kirpichnikov, S. N.; Vorobyev, A. Y.; Teterin, S. N.

doi:10.1023/a:1026094115801

Cited by 1 publication

(2 citation statements)

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“…Some of the authors of this paper (Lacruz 2010) have calculated the solution for the generalized non-coplanar Hohmann transfer only for the first configuration (there exist four configurations that minimize the energy according to Kamel and Soliman (1999)). In this paper we consider elliptic orbits and N = 2 impulse transfers (Broucke and Prado 1994); taking a split between initial and transference planes (i it = 0 • ), this improves and generalizes the work of Mabsout et al (2009) and differs from Kirpichnikov et al (2003) since we will not consider the launch time of spacecraft. We consider non-coplanar orbits, which improve the solution of Arlulkar and Naik (2012).…”

Section: Introductionmentioning

confidence: 99%

“…On the other hand, different techniques of standard optimization had been used for minimizing a cost function. For example, one studied the isoperimetric problem of finding the extremal transfers for the given characteristic velocity for the orbits (Kirpichnikov et al 2003). Some of the authors of this paper (Lacruz 2010) have calculated the solution for the generalized non-coplanar Hohmann transfer only for the first configuration (there exist four configurations that minimize the energy according to Kamel and Soliman (1999)).…”

Section: Introductionmentioning

confidence: 99%

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On non-coplanar Hohmann transfer using angles as parameters

Rincón

Rojo

Lacruz³

et al. 2015

Astrophys Space Sci

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Artículo de publicación ISIWe 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

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