<?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>1405-7743</journal-id>
<journal-title><![CDATA[Ingeniería, investigación y tecnología]]></journal-title>
<abbrev-journal-title><![CDATA[Ing. invest. y tecnol.]]></abbrev-journal-title>
<issn>1405-7743</issn>
<publisher>
<publisher-name><![CDATA[Universidad Nacional Autónoma de México, Facultad de Ingeniería]]></publisher-name>
</publisher>
</journal-meta>
<article-meta>
<article-id>S1405-77432024000200003</article-id>
<article-id pub-id-type="doi">10.22201/fi.25940732e.2024.25.2.011</article-id>
<title-group>
<article-title xml:lang="en"><![CDATA[Modeling and analysis of a theoretical composite material for aerospace use]]></article-title>
<article-title xml:lang="es"><![CDATA[Análisis y modelado de un material compuesto teórico para uso aeroespacial]]></article-title>
</title-group>
<contrib-group>
<contrib contrib-type="author">
<name>
<surname><![CDATA[Saldaña-Heredia]]></surname>
<given-names><![CDATA[Alonso]]></given-names>
</name>
<xref ref-type="aff" rid="Aff"/>
</contrib>
<contrib contrib-type="author">
<name>
<surname><![CDATA[Martínez-Calzada]]></surname>
<given-names><![CDATA[Víctor]]></given-names>
</name>
<xref ref-type="aff" rid="Aff"/>
</contrib>
<contrib contrib-type="author">
<name>
<surname><![CDATA[Cosgalla-Marín]]></surname>
<given-names><![CDATA[Cristina Lizzete]]></given-names>
</name>
<xref ref-type="aff" rid="Aff"/>
</contrib>
<contrib contrib-type="author">
<name>
<surname><![CDATA[Rodríguez-Torres]]></surname>
<given-names><![CDATA[Adriana]]></given-names>
</name>
<xref ref-type="aff" rid="Aff"/>
</contrib>
</contrib-group>
<aff id="Af1">
<institution><![CDATA[,Universidad Politécnica Metropolitana de Hidalgo  ]]></institution>
<addr-line><![CDATA[ ]]></addr-line>
<country>Mexico</country>
</aff>
<aff id="Af2">
<institution><![CDATA[,Universidad Politécnica Metropolitana de Hidalgo  ]]></institution>
<addr-line><![CDATA[ ]]></addr-line>
<country>Mexico</country>
</aff>
<aff id="Af3">
<institution><![CDATA[,Universidad Politécnica Metropolitana de Hidalgo  ]]></institution>
<addr-line><![CDATA[ ]]></addr-line>
<country>Mexico</country>
</aff>
<aff id="Af4">
<institution><![CDATA[,Universidad Politécnica Metropolitana de Hidalgo  ]]></institution>
<addr-line><![CDATA[ ]]></addr-line>
<country>Mexico</country>
</aff>
<pub-date pub-type="pub">
<day>00</day>
<month>06</month>
<year>2024</year>
</pub-date>
<pub-date pub-type="epub">
<day>00</day>
<month>06</month>
<year>2024</year>
</pub-date>
<volume>25</volume>
<numero>2</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=S1405-77432024000200003&amp;lng=en&amp;nrm=iso"></self-uri><self-uri xlink:href="http://www.scielo.org.mx/scielo.php?script=sci_abstract&amp;pid=S1405-77432024000200003&amp;lng=en&amp;nrm=iso"></self-uri><self-uri xlink:href="http://www.scielo.org.mx/scielo.php?script=sci_pdf&amp;pid=S1405-77432024000200003&amp;lng=en&amp;nrm=iso"></self-uri><abstract abstract-type="short" xml:lang="en"><p><![CDATA[Abstract The objective of this article is to present a composite material as a reusable element applied to the aerospace sector. The material is proposed to be part of a two-stage rocket, which will be subjected to both a thermal load due to liftoff and an axial load. For this, the material was simulated through a stress test following the ASTM standard and thermal expansion was studied through three theories. The answer was analyzed using two software: firstly, we used MATLAB® to analytically model the stress test and we focused on determining which would be the best proportion based on the rule of mixtures; likewise, we studied the effect of thermal expansion and proposed a cycle (takeoff-landing), in which material wear was considered as residual stress. The result of this first analysis was to obtain the best ratio (fiber-matrix) to subsequently model it in ANSYS®. In this software, the material was modeled defining itself as a laminated composite; we studied the difference between the number of sheets. Similarly, we analyze the material from an axial load test and adding the thermal load. As a result, it was found that the theoretical material could achieve maximum performance using four fiber sheets. Analytically calculated strains were analyzed through the mixture rule in MATLAB® and compared with those calculated numerically in ANSYS®. From this comparison, an accuracy of 99 % was obtained using a polymeric composite laminated with four fiber sheets.]]></p></abstract>
<abstract abstract-type="short" xml:lang="es"><p><![CDATA[Resumen El objetivo de este artículo es presentar un material compuesto como elemento reutilizable aplicado al sector aeroespacial. Se propone que el material sea parte de un cohete de dos etapas, mismo que estará sometido tanto a una carga térmica debido al despegue como a una carga axial. Para ello, el material se simuló a través de una prueba de tensión siguiendo la norma ASTM y se estudió la dilatación térmica a través de tres teorías. La respuesta fue analizada utilizando dos softwares: Primero se usó MATLAB® para modelar analíticamente la prueba de tensión y se determinó cuál sería la mejor proporción basándose en la regla de las mezclas, así mismo, se estudió el efecto de la dilatación térmica y se propuso un ciclo (despegue-aterrizaje) en el que se contempló un desgaste del material como esfuerzo residual. El resultado de este primer análisis fue la obtención de la mejor proporción (fibra-matriz) para posteriormente modelarlo en ANSYS®. En este software se modeló el material definiéndose como un compuesto laminado, asimismo se estudió la diferencia entre el número de láminas. De igual forma, se analizó el material a partir de una prueba de carga axial y se sumó la carga térmica. Como resultado, se observó que el material teórico podría alcanzar un rendimiento máximo utilizando cuatro láminas de fibra. Se analizaron las deformaciones calculadas analíticamente a través de la regla de las mezclas en MATLAB® y se compararon con las calculadas numéricamente en ANSYS®. De dicha comparativa se obtuvo una precisión de 99 %, utilizando un compuesto polimérico laminado con cuatro láminas de fibra.]]></p></abstract>
<kwd-group>
<kwd lng="en"><![CDATA[Composite material]]></kwd>
<kwd lng="en"><![CDATA[reusable]]></kwd>
<kwd lng="en"><![CDATA[modeled]]></kwd>
<kwd lng="en"><![CDATA[theoretical]]></kwd>
<kwd lng="en"><![CDATA[strain]]></kwd>
<kwd lng="es"><![CDATA[Material compuesto]]></kwd>
<kwd lng="es"><![CDATA[reusable]]></kwd>
<kwd lng="es"><![CDATA[modelado]]></kwd>
<kwd lng="es"><![CDATA[teórico]]></kwd>
<kwd lng="es"><![CDATA[deformación]]></kwd>
</kwd-group>
</article-meta>
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