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		<label>lattes: 7340081273816424 3 FariaVendittiRoccPrad:2012:MuOpIn</label>
		<citationkey>FariaVendittiRoccPrad:2012:MuOpIn</citationkey>
		<title>Multi-Objective Optimization of Interplanetary Trajectories with Sequential Gravity Assisted Maneuvers</title>
		<year>2012</year>
		<secondarytype>PRE CN</secondarytype>
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		<author>Faria Venditti, Flaviane Cristine,</author>
		<author>Rocco, Evandro Marconi,</author>
		<author>Prado, Antonio Fernando Bertachini de Almeida,</author>
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		<group>DMC-ETE-INPE-MCTI-GOV-BR</group>
		<group>DMC-ETE-INPE-MCTI-GOV-BR</group>
		<affiliation>Instituto Nacional de Pesquisas Espaciais (INPE)</affiliation>
		<affiliation>Instituto Nacional de Pesquisas Espaciais (INPE)</affiliation>
		<affiliation>Instituto Nacional de Pesquisas Espaciais (INPE)</affiliation>
		<electronicmailaddress>flaviane.venditti@gmail.com</electronicmailaddress>
		<electronicmailaddress>evandro@dem.inpe.br</electronicmailaddress>
		<electronicmailaddress>prado@dem.inpe.br</electronicmailaddress>
		<e-mailaddress>prado@dem.inpe.br</e-mailaddress>
		<conferencename>Congresso Nacional de Engenharia Mecânica, 7 (CONEM).</conferencename>
		<conferencelocation>São Luís</conferencelocation>
		<date>2012</date>
		<publisher>ABCM</publisher>
		<volume>1</volume>
		<pages>1-10</pages>
		<booktitle>Anais</booktitle>
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		<keywords>Astrodinâmica, Dinâmica Orbital, Swing-By.</keywords>
		<abstract>This work is a study of optimization of interplanetary trajectories using gravity assisted maneuvers on different planets on the same mission. This maneuver consists in using the gravity of a planet to gain or lose energy, velocity and angular momentum, minimizing fuel consumption. The trajectory is divided into three parts, where the first and the last one are inside the sphere of influence of a planet, and the intermediate part is a heliocentric phase. This methodology is called Patched Conics. When the optimization of more than one objective is desired, considering that the objectives are conflicting, a multi-objective method is needed. The optimization problem is solved using a methodology based on the Non Inferiority Criterion (Pareto, 1909) and the Smallest Loss Criterion (Rocco et al. 2003), where all objectives are considered simultaneously, without reducing the problem to the case of optimizing a single objective as occurs in most methods found in literature. For this purpose a sequence of gravity assisted maneuvers on some planets were tested with different combinations of dates for the maneuvers, launch and arriving windows.</abstract>
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		<language>en</language>
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