<?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>0012-7353</journal-id>
<journal-title><![CDATA[DYNA]]></journal-title>
<abbrev-journal-title><![CDATA[Dyna rev.fac.nac.minas]]></abbrev-journal-title>
<issn>0012-7353</issn>
<publisher>
<publisher-name><![CDATA[Universidad Nacional de Colombia]]></publisher-name>
</publisher>
</journal-meta>
<article-meta>
<article-id>S0012-73532020000300100</article-id>
<article-id pub-id-type="doi">10.15446/dyna.v87n214.75361</article-id>
<title-group>
<article-title xml:lang="en"><![CDATA[Experimental modal analysis of an aircraft wing prototype for SAE Aerodesign Competition]]></article-title>
<article-title xml:lang="es"><![CDATA[Análisis modal experimental de un prototipo de ala de avión para la competencia SAE Aerodesign]]></article-title>
</title-group>
<contrib-group>
<contrib contrib-type="author">
<name>
<surname><![CDATA[Gasparetto]]></surname>
<given-names><![CDATA[Victor E.L.]]></given-names>
</name>
<xref ref-type="aff" rid="Aff"/>
</contrib>
<contrib contrib-type="author">
<name>
<surname><![CDATA[Machado]]></surname>
<given-names><![CDATA[Marcela R.]]></given-names>
</name>
<xref ref-type="aff" rid="Aff"/>
</contrib>
<contrib contrib-type="author">
<name>
<surname><![CDATA[Carneiro]]></surname>
<given-names><![CDATA[Sergio H.S.]]></given-names>
</name>
<xref ref-type="aff" rid="Aff"/>
</contrib>
</contrib-group>
<aff id="Af1">
<institution><![CDATA[,Carleton University Department of Mechanical and Aerospace Engineering ]]></institution>
<addr-line><![CDATA[Ottawa ]]></addr-line>
<country>Canada</country>
</aff>
<aff id="Af2">
<institution><![CDATA[,University of Brasilia Department of Mechanical Engineering ]]></institution>
<addr-line><![CDATA[Brasilia DF ]]></addr-line>
<country>Brazil</country>
</aff>
<aff id="Af3">
<institution><![CDATA[,University of Brasilia Department of Aerospace Engineering ]]></institution>
<addr-line><![CDATA[Brasilia ]]></addr-line>
<country>Brazil</country>
</aff>
<pub-date pub-type="pub">
<day>00</day>
<month>09</month>
<year>2020</year>
</pub-date>
<pub-date pub-type="epub">
<day>00</day>
<month>09</month>
<year>2020</year>
</pub-date>
<volume>87</volume>
<numero>214</numero>
<fpage>100</fpage>
<lpage>110</lpage>
<copyright-statement/>
<copyright-year/>
<self-uri xlink:href="http://www.scielo.org.co/scielo.php?script=sci_arttext&amp;pid=S0012-73532020000300100&amp;lng=en&amp;nrm=iso"></self-uri><self-uri xlink:href="http://www.scielo.org.co/scielo.php?script=sci_abstract&amp;pid=S0012-73532020000300100&amp;lng=en&amp;nrm=iso"></self-uri><self-uri xlink:href="http://www.scielo.org.co/scielo.php?script=sci_pdf&amp;pid=S0012-73532020000300100&amp;lng=en&amp;nrm=iso"></self-uri><abstract abstract-type="short" xml:lang="en"><p><![CDATA[Abstract This work presents an experimental modal analysis of an aircraft wing prototype, designed by the Aerodesign team of the University of Brasilia, and performs a ground vibration testing of the prototype. The dynamic response data were acquired using the software LabVIEW, and the modal parameters were identified through the EasyMod toolbox. The modal parameters are characterised for the first seven vibration modes of the structure, with the firsts two being suspension modes of vibration. The effect of small changes in the experimental procedure on the identified modal parameters is discussed. It was observed that the use of an excitation signal as a logarithmic sine sweep and with a frequency range of excitation between 2 to 150 Hz resulted in less noise and more accurate measurement of the structure&#8217;s response. Results for different modal identification methods were verified using the Modal Assurance Criterion (MAC), and good correlation was achieved.]]></p></abstract>
<abstract abstract-type="short" xml:lang="es"><p><![CDATA[Resumen Este trabajo presenta el análisis modal experimental de un prototipo de ala de avión diseñado por el equipo de Aerodesign de la Universidad de Brasilia, que realiza una prueba de vibración del suelo en el prototipo. Los datos de respuesta dinámica se obtienen con el software LabVIEW y los parámetros modales identificados a través de la caja de herramientas EasyMod. Los parámetros modales se caracterizan por los primeros siete modos de vibración de la estructura. Se discute el efecto de pequeños cambios en el procedimiento experimental sobre los parámetros modales identificados. Se observó que el uso de la señal de excitación como barrido sinusoidal logarítmico y con un rango de frecuencia de excitación entre 2 y 150 Hz dio como resultado menos ruido y una medición más precisa de la respuesta de la estructura. Los resultados para diferentes métodos de identificación modal se verificaron utilizando el Criterio de Garantía Modal (MAC), y se logró una buena correlación.]]></p></abstract>
<kwd-group>
<kwd lng="en"><![CDATA[experimental modal analysis]]></kwd>
<kwd lng="en"><![CDATA[ground vibration testing]]></kwd>
<kwd lng="en"><![CDATA[SAE AeroDesign]]></kwd>
<kwd lng="en"><![CDATA[modal assurance criterion]]></kwd>
<kwd lng="es"><![CDATA[análisis modal experimental]]></kwd>
<kwd lng="es"><![CDATA[prueba de vibración del suelo]]></kwd>
<kwd lng="es"><![CDATA[SAE AeroDesign]]></kwd>
<kwd lng="es"><![CDATA[criterio de garantía modal]]></kwd>
</kwd-group>
</article-meta>
</front><back>
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