<?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>S0185-11012023000100011</article-id>
<article-id pub-id-type="doi">10.22201/ia.01851101p.2023.59.01.02</article-id>
<title-group>
<article-title xml:lang="en"><![CDATA[Optimal Two-Impulse Interplanetary Trajectories: Earth-Venus and Earth-Mars Missions]]></article-title>
</title-group>
<contrib-group>
<contrib contrib-type="author">
<name>
<surname><![CDATA[Gagg Filho]]></surname>
<given-names><![CDATA[L. A.]]></given-names>
</name>
<xref ref-type="aff" rid="Aff"/>
</contrib>
<contrib contrib-type="author">
<name>
<surname><![CDATA[Fernandes]]></surname>
<given-names><![CDATA[S. da Silva]]></given-names>
</name>
<xref ref-type="aff" rid="Aff"/>
</contrib>
</contrib-group>
<aff id="Af1">
<institution><![CDATA[,Instituto Tecnológico de Aeronáutica Flight Mechanics Department ]]></institution>
<addr-line><![CDATA[São José dos Campos SP]]></addr-line>
<country>Brasil</country>
</aff>
<aff id="Af2">
<institution><![CDATA[,Instituto Tecnológico de Aeronáutica Mathematics Department ]]></institution>
<addr-line><![CDATA[São José dos Campos SP]]></addr-line>
<country>Brasil</country>
</aff>
<pub-date pub-type="pub">
<day>00</day>
<month>00</month>
<year>2023</year>
</pub-date>
<pub-date pub-type="epub">
<day>00</day>
<month>00</month>
<year>2023</year>
</pub-date>
<volume>59</volume>
<numero>1</numero>
<fpage>11</fpage>
<lpage>43</lpage>
<copyright-statement/>
<copyright-year/>
<self-uri xlink:href="http://www.scielo.org.mx/scielo.php?script=sci_arttext&amp;pid=S0185-11012023000100011&amp;lng=en&amp;nrm=iso"></self-uri><self-uri xlink:href="http://www.scielo.org.mx/scielo.php?script=sci_abstract&amp;pid=S0185-11012023000100011&amp;lng=en&amp;nrm=iso"></self-uri><self-uri xlink:href="http://www.scielo.org.mx/scielo.php?script=sci_pdf&amp;pid=S0185-11012023000100011&amp;lng=en&amp;nrm=iso"></self-uri><abstract abstract-type="short" xml:lang="en"><p><![CDATA[ABSTRACT This work describes several models to design optimal interplanetary trajectories. The transfer problem consists in transferring a space vehicle from a circular low Earth orbit (LEO) to a circular low orbit around a destiny planet (Venus or Mars). Models based on the two-body, four-body, and five-body problems are considered. Also, several versions of the patched-conic approximation are utilized including a detailed version that designs a lunar swing-by maneuver. The results show that the optimal trajectories for Earth-Mars and Earth-Venus missions collide with the Moon if a lunar swing-by maneuver with an unspecified altitude of the closest approach is included in the trajectory design; however, sub-optimal trajectories that do not collide with the Moon exist, presenting a smaller fuel consumption than the trajectories without lunar swing-by and with no greater changes in the time of flight.]]></p></abstract>
<abstract abstract-type="short" xml:lang="es"><p><![CDATA[RESUMEN Se describen varios modelos para diseñar trayectorias interplanetarias óptimas. El problema consiste en la transferencia de un vehículo espacial de una órbita circular baja alrededor de la Tierra (LEO) a una órbita circular baja alrededor de un planeta (Venus o Marte). Se consideran modelos basados en el problema de dos cuerpos, el de cuatro cuerpos y el de cinco cuerpos. También se utilizan versiones de la aproximación cónica parchada, incluyendo una que utiliza una maniobra de impulso lunar. Los resultados muestran que las trayectorias óptimas para misiones Tierra-Marte y Tierra-Venus colisionan con la Luna si se incluye la maniobra lunar sin especificar la distancia mínima de acercamiento. Sin embargo, existen trayectorias sub-óptimas que no colisionan con la Luna, no implican cambios en los tiempos de vuelo, y permiten un menor consumo de combustible que aquellas sin la maniobra lunar.]]></p></abstract>
<kwd-group>
<kwd lng="en"><![CDATA[Earth - interplanetary medium - Moon - space vehicles]]></kwd>
</kwd-group>
</article-meta>
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