<?xml version="1.0" encoding="UTF-8"?>
<feed xmlns="http://www.w3.org/2005/Atom" xmlns:dc="http://purl.org/dc/elements/1.1/">
  <title>E-Archivo Collection:</title>
  <link rel="alternate" href="http://hdl.handle.net/10016/7184" />
  <subtitle />
  <id>http://hdl.handle.net/10016/7184</id>
  <updated>2013-06-18T05:11:41Z</updated>
  <dc:date>2013-06-18T05:11:41Z</dc:date>
  <entry>
    <title>Análisis experimental del comportamiento a flexión dinámica de vigas sándwich</title>
    <link rel="alternate" href="http://hdl.handle.net/10016/7683" />
    <author>
      <name>Ivañez, Inés</name>
    </author>
    <author>
      <name>Santiuste, Carlos</name>
    </author>
    <author>
      <name>Sánchez-Sáez, Sonia</name>
    </author>
    <id>http://hdl.handle.net/10016/7683</id>
    <updated>2013-06-07T00:07:16Z</updated>
    <published>2009-09-30T22:00:00Z</published>
    <summary type="text">Title: Análisis experimental del comportamiento a flexión dinámica de vigas sándwich
Author(s): Ivañez, Inés; Santiuste, Carlos; Sánchez-Sáez, Sonia
Abstract: En este trabajo, se ha analizado experimentalmente el comportamiento a flexión dinámica de vigas sándwich con pieles de fibra de vidrio/poliéster y núcleo de espuma de PVC. Se han llevado a cabo ensayos dinámicos de flexión en tres puntos, de los que se ha obtenido la fuerza de contacto, la energía absorbida y el desplazamiento máximo de ambas pieles. Se ha analizado la influencia de la energía de impacto sobre estas variables y en el modo de fallo de las vigas, observando que la compresión del núcleo bajo el área de contacto provoca una localización del daño que favorece la rotura de la piel superior.
Description: Proceeding of: V International Conference on Science and Technology of Composite Materials, 8° Congreso Nacional de Materiales Compuestos, COMATCOMP '09, San Sebastián, Spain, 6-9 octubre 2009</summary>
    <dc:date>2009-09-30T22:00:00Z</dc:date>
  </entry>
  <entry>
    <title>Influence of temperature on composite aeronautical structural bolted joints</title>
    <link rel="alternate" href="http://hdl.handle.net/10016/14576" />
    <author>
      <name>Santiuste, Carlos</name>
    </author>
    <author>
      <name>Barbero, Enrique</name>
    </author>
    <author>
      <name>Miguélez, Henar</name>
    </author>
    <id>http://hdl.handle.net/10016/14576</id>
    <updated>2012-09-17T15:08:29Z</updated>
    <published>2009-05-31T22:00:00Z</published>
    <summary type="text">Title: Influence of temperature on composite aeronautical structural bolted joints
Author(s): Santiuste, Carlos; Barbero, Enrique; Miguélez, Henar
Abstract: This work focuses on the analysis of temperature and bolt torque influence on aeronautical joint behaviour. A numerical model based on finite elements was developed. Results obtained from numerical simulations showed coupled influence of temperature combined with torque level on the joint
Description: 15th International Conference on Composite Structures (ICCS/15), University of Porto, Porto, Portugal, 15-17 June 2009</summary>
    <dc:date>2009-05-31T22:00:00Z</dc:date>
  </entry>
  <entry>
    <title>Modelling of composite sandwich structures with honeycomb core subjected to high velocity impact</title>
    <link rel="alternate" href="http://hdl.handle.net/10016/14575" />
    <author>
      <name>Buitrago, Brenda L.</name>
    </author>
    <author>
      <name>Santiuste, Carlos</name>
    </author>
    <author>
      <name>Sánchez-Sáez, Sonia</name>
    </author>
    <author>
      <name>Barbero, Enrique</name>
    </author>
    <author>
      <name>Navarro, Carlos</name>
    </author>
    <id>http://hdl.handle.net/10016/14575</id>
    <updated>2012-06-14T13:51:02Z</updated>
    <published>2009-05-31T22:00:00Z</published>
    <summary type="text">Title: Modelling of composite sandwich structures with honeycomb core subjected to high velocity impact
Author(s): Buitrago, Brenda L.; Santiuste, Carlos; Sánchez-Sáez, Sonia; Barbero, Enrique; Navarro, Carlos
Abstract: In this study the behaviour of composite sandwich panels with aluminium honeycomb core subjected to high velocity impact was analysed by a numerical model which was validated by experimental tests.
Description: Proceeding of: 15th International Conference on Composite Structures (ICCS/15), University of Porto, Porto, Portugal, 15-17 June 2009</summary>
    <dc:date>2009-05-31T22:00:00Z</dc:date>
  </entry>
  <entry>
    <title>Ballistic behavior of preloading CFRPs panels</title>
    <link rel="alternate" href="http://hdl.handle.net/10016/9304" />
    <author>
      <name>García-Castillo, Shirley K.</name>
    </author>
    <author>
      <name>Sánchez-Sáez, Sonia</name>
    </author>
    <author>
      <name>Barbero, Enrique</name>
    </author>
    <author>
      <name>Navarro, Carlos</name>
    </author>
    <id>http://hdl.handle.net/10016/9304</id>
    <updated>2012-06-14T12:33:59Z</updated>
    <published>2010-10-04T22:00:00Z</published>
    <summary type="text">Title: Ballistic behavior of preloading CFRPs panels
Author(s): García-Castillo, Shirley K.; Sánchez-Sáez, Sonia; Barbero, Enrique; Navarro, Carlos
Abstract: In this paper the effect of static biaxial preloading of CFRPs plates under high velocity impact is investigated experimentally. Results are compared with those obtained when no static loads are applied to the specimens. Two magnitudes were measured from the tests: the residual velocity of the impacting projectile and the extension of the damage area in the laminate.
Description: ICCE 12. Twelve International Conference on Composites / Nano Engineering. Tenerife, Spain, August 1-6, 2005</summary>
    <dc:date>2010-10-04T22:00:00Z</dc:date>
  </entry>
</feed>

