Dynamics of a spacecraft and normalization around Lagrangian points in the Neptune–Triton system

Stuchi, T. J.; Yokoyama, T.; Correa, Alfredo A.; Solórzano, R.H.; Sanchez, Diogo M.; Winter, S. M. Giuliatti; Winter, O. C.

doi:10.1016/j.asr.2007.04.007

Cited by 11 publications

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“…In Oberti & Vienne (2003) the authors compare observational data from the systems Saturn-Tethys-satellite and Saturn-Dione-satellite and they conclude that the corresponding theoretical data are much more accurate when the oblateness of Saturn is taken into consideration. In the same vein, in the work of Stuchi et al (2008) regarding the dynamics of a spacecraft in the Neptune-Triton problem the oblateness coefficient is also included. In the present paper we continue the work initiated in Nagler (2004) and Nagler (2005) (hereafter Paper I and II) following the same numerical techniques.…”

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confidence: 99%

Crash test for the Copenhagen problem with oblateness

Zotos

2015

Celest Mech Dyn Astr

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The case of the planar circular restricted three-body problem where one of the two primaries is an oblate spheroid is investigated. We conduct a thorough numerical analysis on the phase space mixing by classifying initial conditions of orbits and distinguishing between three types of motion: (i) bounded, (ii) escape and (iii) collisional. The presented outcomes reveal the high complexity of this dynamical system. Furthermore, our numerical analysis shows a strong dependence of the properties of the considered escape basins with the total orbital energy, with a remarkable presence of fractal basin boundaries along all the escape regimes. Interpreting the collisional motion as leaking in the phase space we related our results to both chaotic scattering and the theory of leaking Hamiltonian systems. We also determined the escape and collisional basins and computed the corresponding escape/crash times. The highly fractal basin boundaries observed are related with high sensitivity to initial conditions thus implying an uncertainty between escape solutions which evolve to different regions of the phase space. We hope our contribution to be useful for a further understanding of the escape and crash mechanism of orbits in this version of the restricted three-body problem.

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confidence: 99%

Crash test for the Copenhagen problem with oblateness

Zotos

2015

Celest Mech Dyn Astr

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“…In the work of Oberti & Vienne (2003) it was proved that the theoretical data from the celestial systems Saturn-Tethys-satellite and Saturn-Dione-satellite are much more accurate with respect with the corresponding observational data when the oblateness of Saturn is taken into consideration. Similarly, the oblateness of the Neptune was included in the work of Stuchi et al (2008) regarding the dynamics of a spacecraft in the Neptune-Triton system.…”

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How does the oblateness coefficient influence the nature of orbits in the restricted three-body problem?

Zotos¹

2015

Astrophys Space Sci

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We numerically investigate the case of the planar circular restricted three-body problem where the more massive primary is an oblate spheroid. A thorough numerical analysis takes place in the configuration (x, y) and the (x, E) space in which we classify initial conditions of orbits into three categories: (i) bounded, (ii) escaping and (iii) collisional. Our results reveal that the oblateness coefficient has a huge impact on the character of orbits. Interpreting the collisional motion as leaking in the phase space we related our results to both chaotic scattering and the theory of leaking Hamiltonian systems. We successfully located the escape as well as the collisional basins and we managed to correlate them with the corresponding escape and collision times. We hope our contribution to be useful for a further understanding of the escape and collision properties of motion in this interesting version of the restricted three-body problem.

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“…Relacionado con la materia de este artículo, Bengoa et al, (2004), aplican control LQG con propulsión continúa para lograr una posición estable en los puntos de Lagrange, y para mantener la posición relativa de varios satélites (formation flying). En (Stuchi, 2008) se realiza un análisis de los puntos de Lagrange en un sistema distinto del aquí considerado. Otros artículos igualmente interesantes son (Hamilton, 2001;Howell y Marchand, 2003ay 2003b, Scheeres y Vinh, 2000Gurfil y Kasdin, 2001;Ming et al, 2004).…”

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Modelado, Simulación y Control de Satélites en los Puntos de Lagrange del Sistema Tierra - Luna

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Santos

2011

Revista Iberoamericana de Automática e Informática Industrial R

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ResumenEl objetivo de este artículo es modelar, analizar y controlar una constelación de cinco satélites, situados en los puntos de Lagrange del sistema Tierra -Luna. El modelo se ha desarrollado incluyendo efectos complejos no considerados habitualmente, como el viento solar, la no esfericidad de los planetas y la deriva de la órbita lunar, para hacerlo más realista. Sobre los satélites se ejerce una propulsión continua, calculada por medio de controladores tipo PD, tanto convencionales como borrosos, y cuya finalidad es situar y mantener a cada satélite en su punto de Lagrange frente a las inestabilidades y derivas inherentes al sistema. El sistema completo se ha implementado en el lenguaje de modelado Modelica, para el que se han creado una serie de elementos aeroespaciales, y las simulaciones se han desarrollado con el software Dymola. Tanto con los controladores clásicos como con los borrosos se han obtenido muy buenos resultados.

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Dynamics of a spacecraft and normalization around Lagrangian points in the Neptune–Triton system

Cited by 11 publications

References 11 publications

Crash test for the Copenhagen problem with oblateness

Crash test for the Copenhagen problem with oblateness

How does the oblateness coefficient influence the nature of orbits in the restricted three-body problem?

Modelado, Simulación y Control de Satélites en los Puntos de Lagrange del Sistema Tierra - Luna

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