Searching for capture and escape trajectories around Jupiter using its Galilean satellites
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Searching for capture and escape trajectories around Jupiter using its Galilean satellites A. F. B. A. Prado · V. M. Gomes
Received: 11 November 2013 / Revised: 7 May 2014 / Accepted: 12 May 2014 © SBMAC - Sociedade Brasileira de Matemática Aplicada e Computacional 2014
Abstract This paper has the goal of searching for natural trajectories that can be used for a particle or a spacecraft coming from a region of the space far from Jupiter system to be captured into this system by making close approaches with the Galilean satellites of the planet. The opposite situation is also possible and escape trajectories can also be found. This type of maneuver is called “Swing-By” and it is usual in astrodynamics. It was used in many space missions to reduce the fuel consumption by gaining or loosing energy from the gravity of a celestial body. Several famous examples are the Voyager, Cassini, Galileo and other missions. The idea of the present research is to study this type of maneuver using the Galilean satellites of Jupiter, to search for trajectories that change the two-body energy (particle or spacecraft)–(Jupiter) from positive to negative (a capture trajectory) or from negative to positive (an escape trajectory). Those trajectories can be used for a spacecraft going or leaving the planet Jupiter or to explain how particles can be captured or escape from Jupiter system by close approaches with the Galilean satellites. Initial conditions are varied to cover the whole possible alternatives and then small regions of captures and escapes are identified. After that, a study is made to see the accuracy of the Tisserand’s method when applied to those close approach trajectories. Keywords Astrodynamics · Swing-By · Orbital maneuvers · Capture trajectories · Escape trajectories Mathematics Subject Classification
37N05 · 70F15 · 70F16
Communicated by Elbert Macau and Cristiano Fiorilo. A. F. B. A. Prado Instituto Nacional de Pesquisas Espaciais, INPE, São José dos Campos, Brazil e-mail: [email protected] V. M. Gomes (B) Univ. Estadual Paulista, FEG-UNESP, Guaratinguetá, Brazil e-mail: [email protected]
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A. F. B. A. Prado, V. M. Gomes
1 Introduction A close approach with a celestial body is a common technique that has been in use for many years now, with the objective of replacing an impulsive maneuver that consumes fuel by a variation of velocity that comes naturally from the main body that is in the way of the spacecraft. Several researches considered this problem. Broucke (1988) has an excellent overview of this phenomenon. Examples of real missions that used this technique can be found in the literature. Carvell (1985) considered an out-of-plane maneuver around Jupiter to change the orbital plane of the spacecraft. Casalino et al. (1999) combined low-thrust propulsion with close approaches. D’amario et al. (1982) studied applications in the Galileo mission. Dunham and Davis (1985) considered optimization of multiple close approaches with the Moon. Minovich (1961) and Kohlhase and Penzo (1977) studied the traject
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