<?xml version="1.0" encoding="ISO-8859-1"?><article xmlns:mml="http://www.w3.org/1998/Math/MathML" xmlns:xlink="http://www.w3.org/1999/xlink" xmlns:xsi="http://www.w3.org/2001/XMLSchema-instance">
<front>
<journal-meta>
<journal-id>0185-1101</journal-id>
<journal-title><![CDATA[Revista mexicana de astronomía y astrofísica]]></journal-title>
<abbrev-journal-title><![CDATA[Rev. mex. astron. astrofis]]></abbrev-journal-title>
<issn>0185-1101</issn>
<publisher>
<publisher-name><![CDATA[Universidad Nacional Autónoma de México, Instituto de Astronomía]]></publisher-name>
</publisher>
</journal-meta>
<article-meta>
<article-id>S0185-11012019000200177</article-id>
<article-id pub-id-type="doi">10.22201/ia.01851101p.2019.55.02.05</article-id>
<title-group>
<article-title xml:lang="en"><![CDATA[Minimizing fuel consumption in orbit transfers using universal variable and particle swarm optimization]]></article-title>
</title-group>
<contrib-group>
<contrib contrib-type="author">
<name>
<surname><![CDATA[Echeverry]]></surname>
<given-names><![CDATA[L. M.]]></given-names>
</name>
<xref ref-type="aff" rid="Aff"/>
<xref ref-type="aff" rid="Aaf"/>
</contrib>
<contrib contrib-type="author">
<name>
<surname><![CDATA[Villanueva]]></surname>
<given-names><![CDATA[Y.]]></given-names>
</name>
<xref ref-type="aff" rid="Aff"/>
<xref ref-type="aff" rid="Aaf"/>
</contrib>
</contrib-group>
<aff id="Af1">
<institution><![CDATA[,Sergio Arboleda University School of Exact Sciences and Engineering ]]></institution>
<addr-line><![CDATA[Bogotá ]]></addr-line>
<country>Colombia</country>
</aff>
<aff id="Af2">
<institution><![CDATA[,University of the Andes Department of Mathematics ]]></institution>
<addr-line><![CDATA[Bogotá ]]></addr-line>
<country>Colombia</country>
</aff>
<aff id="Af3">
<institution><![CDATA[,Federal University of Goiás Institute of Mathematics and Statistics ]]></institution>
<addr-line><![CDATA[Goiania ]]></addr-line>
<country>Brazil</country>
</aff>
<pub-date pub-type="pub">
<day>00</day>
<month>00</month>
<year>2019</year>
</pub-date>
<pub-date pub-type="epub">
<day>00</day>
<month>00</month>
<year>2019</year>
</pub-date>
<volume>55</volume>
<numero>2</numero>
<fpage>177</fpage>
<lpage>184</lpage>
<copyright-statement/>
<copyright-year/>
<self-uri xlink:href="http://www.scielo.org.mx/scielo.php?script=sci_arttext&amp;pid=S0185-11012019000200177&amp;lng=en&amp;nrm=iso"></self-uri><self-uri xlink:href="http://www.scielo.org.mx/scielo.php?script=sci_abstract&amp;pid=S0185-11012019000200177&amp;lng=en&amp;nrm=iso"></self-uri><self-uri xlink:href="http://www.scielo.org.mx/scielo.php?script=sci_pdf&amp;pid=S0185-11012019000200177&amp;lng=en&amp;nrm=iso"></self-uri><abstract abstract-type="short" xml:lang="en"><p><![CDATA[ABSTRACT Minimizing fuel consumption in space travels is becoming increasingly important for spatial development. In the present paper, the fuel consumption in orbit transfers (without gravitational assistance) is minimized, where a spacecraft performs a change from an orbit around the Earth to another one around a di&#64256;erent celestial body. Two methods are presented: one of immediate transfer and another with wait time. Minimizing is done by solving a nonlinear system, obtained by applying Lagrange multipliers to the equation modelling the keplerian system, and using the seeds coming from the particle swarm algorithm to execute the Newton&#8217;s method. Numerical simulations with real values were made to compare these methods with the Hohmann transfer and data from the specialized literature.]]></p></abstract>
<abstract abstract-type="short" xml:lang="es"><p><![CDATA[RESUMEN La minimización del gasto de combustible en los viajes espaciales es cada día más importante para el desarrollo espacial. En el presente trabajo se minimiza el gasto de combustible en transferencias de orbita (sin asistencia gravitacional), donde se ejecuta un cambio de órbita de una nave alrededor de la Tierra a una órbita alrededor de otro cuerpo celeste. Se presentan dos métodos, uno de transferencia inmediata y otro con tiempo de espera. La minimización se hace resolviendo un sistema no lineal que aparece después de aplicar multiplicadores de Lagrange a las ecuaciones que modelan el sistema kepleriano, usando las semillas que vienen del algoritmo de enjambres de partículas para ejecutar el método de Newton. Se hicieron simulaciones numéricas con valores reales para comparar estos métodos con la transferencia de Hohmann y los datos que aparecen en la literatura especializada.]]></p></abstract>
<kwd-group>
<kwd lng="en"><![CDATA[celestial mechanics]]></kwd>
<kwd lng="en"><![CDATA[space vehicles]]></kwd>
</kwd-group>
</article-meta>
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