Third‐Body Perturbation in the Case of Elliptic Orbits for the Disturbing Body

Domingos, R. C.; Moraes, Rodolpho Vilhena de; Prado, A. F. B. A.

doi:10.1155/2008/763654

Cited by 58 publications

(50 citation statements)

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“…Similar computations as in [7] will lead to more accurate model useful with longer time transfers. Finally the lunar perturbation and the J 2 -effect can be superposed and their effects numerically analysed for space mission where both effects have to be taken into account.…”

Section: Extensionsmentioning

confidence: 86%

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Lunar Perturbation of the Metric Associated to the Averaged Orbital Transfer

Bonnard

Henninger²,

Rouot³

2015

Springer INdAM Series

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Abstract. In a series of previous article [1,2], we introduced a Riemannian metric associated to the energy minimizing orbital transfer with low propulsion. The aim of this article is to study the deformation of this metric due to a standard perturbation in space mechanics, the lunar attraction. Using Hamiltonian formalism, we describe the effects of the perturbation on the orbital transfers and the deformation of the conjugate and cut loci of the original metric.

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Section: Extensionsmentioning

confidence: 86%

“…(see [7] for more precise expansions). A simplified academic model is to set the eccentricity ρ to zero, the inclination i to zero and to restrict the control to this plane, the lunar perturbing potential becomes…”

Section: Development Of the Term Cosmentioning

confidence: 99%

Lunar Perturbation of the Metric Associated to the Averaged Orbital Transfer

Bonnard

Henninger²,

Rouot³

2015

Springer INdAM Series

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“…Costa & Prado (2002) discussed the critical angle of a third-body perturbation that is a value for the inclination such that any near-circular orbit with inclination below this value remains near-circular. Domingos et al (2008) showed an analytical expansion to study the third-body perturbation for a case where the perturbing body is in an elliptical orbit, based on the expansion of the perturbing function in polynomials of Legendre.…”

Section: Introductionmentioning

confidence: 99%

“…In this paper, the study done by Broucke (2003), Prado (2003) and Domingos et al (2008) is expanded, including the eccentricity and inclination of the perturbing body. A three-dimensional model is used to study the effects of a third-body gravitational potential on the spacecraft that orbits near a celestial body including the eccentricity and the inclination of the third-body in the formulation.…”

Section: Introductionmentioning

confidence: 99%

Orbital Elements Evolution Due to a Perturbing Body in an Inclined Elliptical Orbit

Rahoma¹

2014

Journal of Astronomy and Space Sciences

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“…As an example, we can cite the Jupiter Europa Orbiter (JEO, NASA) and the Jupiter IcyMoon Explorer (JUICE, ESA). Several papers have contributed to a better understanding of the dynamics involved in this type of mission (see for example Scheeres et al, 2001;Prado, 2003;Paskowitz & Scheeres, 2005a, 2005b Lara & Russel, 2006, 2007Domingos et al, 2008;Carvalho et al, 2010 Carvalho et al, , 2012a Carvalho et al, , 2012bLiu et al, 2012). The study performed in this paper is related to the orbital motion of artificial satellites around Europa considering polygenic perturbations due to its non-spherical shape and the third-body perturbation due to Jupiter.…”

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confidence: 99%

Stable low-altitude polar orbits around Europa

Santos¹,

Carvalho²,

Moraes³

2013

Proceeding Series of the Brazilian Society of Computational and Applied Mathematics

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Abstract-In this paper, a search for low-altitude orbits around Europa is performed. An emphasis is given in frozen orbits. These orbits are used in the planning of aerospace activities to be conducted around this planetary satellite, with respect to the stability of orbits of artificial satellites. The study considers orbits of artificial satellites around Europa under the influence of the third-body perturbation (the gravitational attraction of Jupiter) and the polygenic perturbations. These last ones occur due to forces such as the non-uniform distribution of mass (J2 and J3) of the main (central) body. A simplified dynamic model for these perturbations is used. The Lagrange planetary equations, which compose a system of nonlinear differential equations, are used to describe the orbital motion of the artificial satellite around Europa. The equations of motion are developed in closed form to avoid expansions in power series. Low-altitude polar orbits and frozen orbits with long lifetimes were found. This study can be used for planning of future space missions which seek to visit Europa and other planetary satellites.Keywords-Astrodynamics and Orbital Mechanics, Frozen orbits, Planetary Satellite, Europa, Singleaveraged method.Resumo-Neste trabalho, uma busca porórbitas de baixa altitude em torno de Europaé realizada. Umâ enfaseé dada emórbitas congeladas. Estasórbitas serão utilizadas no planejamento de atividades aeroespaciais a serem conduzidas em torno deste satélite planetário, no que diz respeitoà estabilidade deórbitas de satélites artificiais. O estudo leva em consideraçãoórbitas de satélites artificiais em torno de Europa sob a influência da perturbação de terceiro corpo (a atração gravitacional de Júpiter) e das perturbações devidasàs forças poligênicas. Estasúltimas ocorrem devidoàs forças tais como a distribuição não uniforme de massa (J2 e J3) do corpo principal (central). Aquié utilizado um modelo dinâmico simplificado para essas perturbações. As equações do movimento são desenvolvidas em forma fechada para evitar expansões em séries de potência.Órbitas polares de baixa altitude eórbitas congeladas com tempos de vida longos foram encontradas. Este estudo pode ser utilizado para o planejamento de futuras missões espaciais que pretendem visitar Europa e outros satélites planetários.Palavras-chave-Astrodinâmica e Mecânica Orbital,Órbitas Congeladas, Satélite Planetário, Europa, Mé-todo da média simples. IntrodutionEuropa is one of the four largest moons of Jupiter. It is one of the planetary satellites of greater interest at the present moment among the scientific community. In the last years are being planned some missions to visit Europa. As an example, we can cite the Jupiter Europa Orbiter (JEO, NASA) and the Jupiter IcyMoon Explorer (JUICE, ESA). Several papers have contributed to a better understanding of the dynamics involved in this type of mission (see for example Scheeres et al., 2001;Prado, 2003;Paskowitz & Scheeres, 2005a, 2005b Lara & Russel, 2006, 2007Domingos et al., 2008;Carvalho et a...

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Third‐Body Perturbation in the Case of Elliptic Orbits for the Disturbing Body

Cited by 58 publications

References 10 publications

Lunar Perturbation of the Metric Associated to the Averaged Orbital Transfer

Lunar Perturbation of the Metric Associated to the Averaged Orbital Transfer

Orbital Elements Evolution Due to a Perturbing Body in an Inclined Elliptical Orbit

Stable low-altitude polar orbits around Europa

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