<?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>1390-6542</journal-id>
<journal-title><![CDATA[Enfoque UTE]]></journal-title>
<abbrev-journal-title><![CDATA[Enfoque UTE]]></abbrev-journal-title>
<issn>1390-6542</issn>
<publisher>
<publisher-name><![CDATA[Universidad UTE]]></publisher-name>
</publisher>
</journal-meta>
<article-meta>
<article-id>S1390-65422021000200037</article-id>
<article-id pub-id-type="doi">10.29019/enfoqueute.723</article-id>
<title-group>
<article-title xml:lang="es"><![CDATA[Ensayos experimentales y análisis numérico de la estructura del material compuesto alternativo para la reparación de superficies de vuelo en aeronaves]]></article-title>
<article-title xml:lang="en"><![CDATA[Experimental tests and numerical analysis of the structure of the alternative composite material for the repair of flight surfaces in aircraft]]></article-title>
</title-group>
<contrib-group>
<contrib contrib-type="author">
<name>
<surname><![CDATA[Arroba Arroba]]></surname>
<given-names><![CDATA[César]]></given-names>
</name>
<xref ref-type="aff" rid="Aff"/>
</contrib>
<contrib contrib-type="author">
<name>
<surname><![CDATA[Telenchana Flores]]></surname>
<given-names><![CDATA[Manuel]]></given-names>
</name>
<xref ref-type="aff" rid="Aff"/>
</contrib>
<contrib contrib-type="author">
<name>
<surname><![CDATA[Paredes Salinas]]></surname>
<given-names><![CDATA[Juan]]></given-names>
</name>
<xref ref-type="aff" rid="Aff"/>
</contrib>
<contrib contrib-type="author">
<name>
<surname><![CDATA[Fiallo Ortega]]></surname>
<given-names><![CDATA[Salomón]]></given-names>
</name>
<xref ref-type="aff" rid="Aff"/>
</contrib>
<contrib contrib-type="author">
<name>
<surname><![CDATA[Vaca Ortega]]></surname>
<given-names><![CDATA[Henry]]></given-names>
</name>
<xref ref-type="aff" rid="Aff"/>
</contrib>
</contrib-group>
<aff id="Af1">
<institution><![CDATA[,Universidad Técnica de Ambato  ]]></institution>
<addr-line><![CDATA[ ]]></addr-line>
<country>Ecuador</country>
</aff>
<aff id="Af2">
<institution><![CDATA[,Universidad Técnica de Ambato  ]]></institution>
<addr-line><![CDATA[ ]]></addr-line>
<country>Ecuador</country>
</aff>
<aff id="Af3">
<institution><![CDATA[,Universidad Técnica de Ambato  ]]></institution>
<addr-line><![CDATA[ ]]></addr-line>
<country>Ecuador</country>
</aff>
<aff id="Af4">
<institution><![CDATA[,Centro de Investigación de la Fuerza Aérea Ecuatoriana  ]]></institution>
<addr-line><![CDATA[ ]]></addr-line>
<country>Ecuador</country>
</aff>
<aff id="Af5">
<institution><![CDATA[,Universidad Técnica de Ambato  ]]></institution>
<addr-line><![CDATA[ ]]></addr-line>
<country>Ecuador</country>
</aff>
<pub-date pub-type="pub">
<day>00</day>
<month>06</month>
<year>2021</year>
</pub-date>
<pub-date pub-type="epub">
<day>00</day>
<month>06</month>
<year>2021</year>
</pub-date>
<volume>12</volume>
<numero>2</numero>
<fpage>37</fpage>
<lpage>51</lpage>
<copyright-statement/>
<copyright-year/>
<self-uri xlink:href="http://scielo.senescyt.gob.ec/scielo.php?script=sci_arttext&amp;pid=S1390-65422021000200037&amp;lng=en&amp;nrm=iso"></self-uri><self-uri xlink:href="http://scielo.senescyt.gob.ec/scielo.php?script=sci_abstract&amp;pid=S1390-65422021000200037&amp;lng=en&amp;nrm=iso"></self-uri><self-uri xlink:href="http://scielo.senescyt.gob.ec/scielo.php?script=sci_pdf&amp;pid=S1390-65422021000200037&amp;lng=en&amp;nrm=iso"></self-uri><abstract abstract-type="short" xml:lang="es"><p><![CDATA[Resumen En la actualidad, los materiales compuestos de matriz polimérica son utilizados en múltiples aplicaciones, una de las áreas más importantes de aplicación es en el sector aeronáutico, debido a la relativamente baja densidad que tienen los materiales combinados. Estos compuestos tienen buenas propiedades mecánicas, comparables con materiales metálicos, pero que aportan beneficios adicionales. El objetivo de este trabajo es hacer los ensayos experimentales y el análisis numérico de la estructura del material compuesto alternativo para emplearlos en la reparación de las superficies de vuelo de aeronaves del CIDFAE. Se manejó un proceso ampliamente extendido de envasado al vacío (vacuum bagging) para obtener un compuesto más homogéneo, Lo que redujo los defectos en el procesamiento, y controló mejor la fracción de las fibras y el espesor global del compuesto. Se elaboraron probetas de resina epóxica reforzada con capas de tejido plano de tres fibras distintas de: carbono, vidrio y aramida, en diferentes orientaciones, que fueron ensayadas a tracción, flexión e impacto para determinar sus propiedades mecánicas. Se ha demostrado que los resultados conseguidos mediante la metodología analítica y el método de elementos finitos son aproximados a los resultados que se obtienen con ensayos destructivos. Los resultados experimentales muestran que los valores de resistencia a la tracción son mayores en los materiales de resina epóxica reforzados con 4 capas de fibra de carbono en orientación 0°-90°.]]></p></abstract>
<abstract abstract-type="short" xml:lang="en"><p><![CDATA[Abstract Nowadays, polymeric matrix composite materials are used in multiple applications. One of the important areas of application is in the aeronautical sector, due to the relatively low density of the combined materials; these compounds have good mechanical properties, comparable to metallic materials, but providing additional benefits. The objective of this work is to carry out the experimental tests and the numerical analysis of the structure of the alternative composite material to be used to repair of the flight surfaces of CIDFAE aircraft. A widely extended vacuum bagging process was used to obtain a more homogeneous compound, thus reducing defects in processing, better controlling the fiber fraction and the overall thickness of the compound. Specimens of epoxy resin reinforced with layers of flat fabric of three different fibers of: carbon, glass and aramid, in different orientations, were made, which were tested for traction, bending and impact to determine their mechanical properties. It has been shown that the results obtained by analytical methodology and the finite element method are approximate to the results obtained with destructive tests. The experimental results show that the tensile strength values are higher in epoxy resin materials reinforced with 4 layers of carbon fiber in orientation 0 ° -90 °.]]></p></abstract>
<kwd-group>
<kwd lng="es"><![CDATA[superficie de vuelo]]></kwd>
<kwd lng="es"><![CDATA[compuesto]]></kwd>
<kwd lng="es"><![CDATA[reparación]]></kwd>
<kwd lng="es"><![CDATA[aeronaves]]></kwd>
<kwd lng="es"><![CDATA[configuración]]></kwd>
<kwd lng="en"><![CDATA[flight surface]]></kwd>
<kwd lng="en"><![CDATA[compound]]></kwd>
<kwd lng="en"><![CDATA[repair]]></kwd>
<kwd lng="en"><![CDATA[aircraft]]></kwd>
<kwd lng="en"><![CDATA[configuration]]></kwd>
</kwd-group>
</article-meta>
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