<?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>S0185-11012018000100008</article-id>
<title-group>
<article-title xml:lang="en"><![CDATA[A numerical-analytical approach based on canonical transformations for computing optimal low-thrust transfers]]></article-title>
</title-group>
<contrib-group>
<contrib contrib-type="author">
<name>
<surname><![CDATA[Fernandes]]></surname>
<given-names><![CDATA[Sandro da Silva]]></given-names>
</name>
<xref ref-type="aff" rid="Aff"/>
</contrib>
<contrib contrib-type="author">
<name>
<surname><![CDATA[Carvalho]]></surname>
<given-names><![CDATA[Francisco das Chagas]]></given-names>
</name>
<xref ref-type="aff" rid="Aff"/>
</contrib>
<contrib contrib-type="author">
<name>
<surname><![CDATA[Romão]]></surname>
<given-names><![CDATA[João Victor Bateli]]></given-names>
</name>
<xref ref-type="aff" rid="Aff"/>
</contrib>
</contrib-group>
<aff id="Af1">
<institution><![CDATA[,Instituto Tecnológico de Aeronáutica Departamento de Matemática ]]></institution>
<addr-line><![CDATA[ ]]></addr-line>
<country>Brazil</country>
</aff>
<aff id="Af2">
<institution><![CDATA[,Universidade Federal de Sao Paulo Instituto de Ciencia e Tecnologia ]]></institution>
<addr-line><![CDATA[ ]]></addr-line>
<country>Brazil</country>
</aff>
<pub-date pub-type="pub">
<day>00</day>
<month>00</month>
<year>2018</year>
</pub-date>
<pub-date pub-type="epub">
<day>00</day>
<month>00</month>
<year>2018</year>
</pub-date>
<volume>54</volume>
<numero>1</numero>
<fpage>0</fpage>
<lpage>0</lpage>
<copyright-statement/>
<copyright-year/>
<self-uri xlink:href="http://www.scielo.org.mx/scielo.php?script=sci_arttext&amp;pid=S0185-11012018000100008&amp;lng=en&amp;nrm=iso"></self-uri><self-uri xlink:href="http://www.scielo.org.mx/scielo.php?script=sci_abstract&amp;pid=S0185-11012018000100008&amp;lng=en&amp;nrm=iso"></self-uri><self-uri xlink:href="http://www.scielo.org.mx/scielo.php?script=sci_pdf&amp;pid=S0185-11012018000100008&amp;lng=en&amp;nrm=iso"></self-uri><abstract abstract-type="short" xml:lang="en"><p><![CDATA[Abstract A numerical-analytical procedure based on infinitesimal canonical transformations is developed for computing optimal time-fixed low-thrust limited power transfers (no rendezvous) between coplanar orbits with small eccentricities in an inverse-square force field. The optimization problem is formulated as a Mayer problem with a set of non-singular orbital elements as state variables. Second order terms in eccentricity are considered in the development of in the maximum Hamiltonian describing the optimal trajectories. The two-point boundary value problem of going from an initial orbit to a final orbit is solved by means of a two-stage Newton-Raphson algorithm which uses an infinitesimal canonical transformation. Numerical results are presented for some transfers between circular orbits with moderate radius ratio, including a preliminary analysis of Earth-Mars and Earth-Venus missions.]]></p></abstract>
<abstract abstract-type="short" xml:lang="es"><p><![CDATA[Resumen Se desarrolla un procedimiento numérico-analítico fundamentado en la transformación canónica infinitesimal para calcular transferencias de bajo empuje y potencia limitada con tiempo fijo entre órbitas coplanares de baja excentricidad en un campo de fuerza 1/r2. La optimización se formula como un problema del Mayer con un conjunto de elementos orbitales no singulares como variables de estado. Los términos de segundo orden en la excentricidad se consideran en el desarrollo del máximo Hamiltoniano que describe las trayectorias óptimas. El problema del valor l &#769;&#305;mite de dos puntos al ir de una órbita inicial a una órbita final se resuelve mediante un algoritmo de Newton-Raphson de dos etapas que utiliza una transformación canónica infinitesimal. Se presentan resultados numéricos para transferencias entre órbitas circulares con una razón de radio moderada, y se incluye un análisis preliminar de las misiones Tierra-Marte y Tierra-Venus.]]></p></abstract>
<kwd-group>
<kwd lng="en"><![CDATA[celestial mechanics]]></kwd>
<kwd lng="en"><![CDATA[methods: analytical]]></kwd>
<kwd lng="en"><![CDATA[methods: numerical]]></kwd>
</kwd-group>
</article-meta>
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