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== Abstract ==

Composite laminates subjected to out-of-plane loads develop damage modes that compromise the load-carrying capacity, as in the fuselage skin of an aircraft. Therefore, we aimed to improve the damage resistance and tolerance of carbon/epoxy thin non-crimp fabric (NCF) laminates by (a) reducing the ‘conventional’ ply-thickness (i.e. comparing thick- and thin-plies) (b) interleaving co-polyamide (CoPA) non-woven veils at the interlaminar regions of thin-ply systems. We devised an impact, compression after impact (CAI) and quasi-static indentation (QSI) experimental campaign, where computerized X-ray tomography provided detailed 3D insight on how matrix cracking, delamination and fibre failure interacted during impact and QSI. Thin-ply laminates reduce the amount of matrix cracking and delamination at the cost of premature fibre breakage, therefore decreasing the damage tolerance. Interleaving CoPA veils arrests delamination onset and improves the residual strength with respect to the thin-ply baseline.
 
[1] S.Sihn, R.Y. Kim, K.Kawabe and S.W. Tsai, Compos. Sci. Technol., vol. 67, no. 6, pp. 996–1008 (2007). https://doi.org/10.1016/j.compscitech.2006.06.008[2] V.A.Ramirez, P.J.Hogg and W.W.Sampson, Compos. Sci. Technol., vol. 110, pp. 103–110 (2015). https://doi.org/10.1016/j.compscitech.2015.01.016

== Full document ==
<pdf>Media:Draft_Content_991704431native-articles-45.pdf</pdf>

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 <div class="center" style="width: auto; margin-left: auto; margin-right: auto;">
-<span style="text-align: center; font-size: 75%;">'''Figure 2''' µCT cross-sections and 3D representative damage mechanisms of LTHICK specimens</span></div>
+<span style="text-align: center; font-size: 75%;">'''Figure 2''' µCT cross-sections and 3D representative damage mechanisms of LTHICK specimens.</span></div>
 <div class="center" style="width: auto; margin-left: auto; margin-right: auto;">
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 <div class="center" style="width: auto; margin-left: auto; margin-right: auto;">
-<span style="text-align: center; font-size: 75%;">'''Figure 3''' µCT cross-sections and 3D representative damage mechanisms of LTHIN specimens</span></div>
+<span style="text-align: center; font-size: 75%;">'''Figure 3''' µCT cross-sections and 3D representative damage mechanisms of LTHIN specimens.</span></div>
 <div class="center" style="width: auto; margin-left: auto; margin-right: auto;">
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 <div class="center" style="width: auto; margin-left: auto; margin-right: auto;">
-<span style="text-align: center; font-size: 75%;">'''Figure 4''' µCT cross-sections and 3D representative damage mechanisms of LV2 specimens</span></div>
+<span style="text-align: center; font-size: 75%;">'''Figure 4''' µCT cross-sections and 3D representative damage mechanisms of LV2 specimens.</span></div>
 In both types of thin laminate, damage started at the bottom part of the specimen and grew upwards leading to a ‘reverse pine-tree’ pattern [27]. This is because the thickness of the plate is small compared to  the rest of dimensions (i.e. ~2x100x150 specimens); therefore, bending and membrane effects to predominate over shear [31].
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 <span id='_GoBack'></span>We greatly acknowledge the entreprise Chomarat (Le Cheylard, France) for providing the material neccesary for this study. We also acknowledge the Spanish governement through the Ministerio de Economía y Competitividad co-funded by the UE (FEDER program) under the contract MAT2015-69491-C3-1-R. The first author is particularly grateful for the support of the Secretaría de Universidades e Investigación del Departamento de Economía y Conocimiento of the Governement of Catalonia with the pre-doctoral grant 2016 FI-B00551.
-<div class="center" style="width: auto; margin-left: auto; margin-right: auto;">
+<div class="center" style="width: auto; margin-left: auto; margin-right: auto;">[[File:Captura de pantalla 2022-09-13 163531.png|centre|569x569px]]</div>
- [[Image:Garcia-Rodriguez_et_al_2017a-image10-c.png|600px]] </div>
 <div class="center" style="width: auto; margin-left: auto; margin-right: auto;">
-<span style="text-align: center; font-size: 75%;">'''Figure 5. CAI strength of pristine and impacted LTHICK, LTHIN and LV2 specimens. The vertical bars refer to the scatter between tests'''</span></div>
+<span style="text-align: center; font-size: 75%;">'''Figure 5. CAI strength of pristine and impacted LTHICK, LTHIN and LV2 specimens. The vertical bars refer to the scatter between tests.'''</span></div>
 ==References ==

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+<span id="OLE_LINK4"></span>
-−
-<div class="center" style="width: auto; margin-left: auto; margin-right: auto;">
-S.M. García-Rodríguez<sup>a</sup>, A. Bardera<sup>b</sup>, A. Sasikumar<sup>a</sup>, M. Ruiz<sup>b</sup>, V. Singery<sup>c</sup>, I. Boada<sup>b</sup>, D. Trias<sup>a</sup>, J. Costa<sup>a </sup></div>
-−
-<div id="OLE_LINK6" class="center" style="width: auto; margin-left: auto; margin-right: auto;">
-<span style="text-align: center; font-size: 75%;"><sup>a</sup>AMADE, Polytechnic School, University of Girona, Campus Montilivi s/n, 17003, Girona Spain</span></div>
-−
-<div class="center" style="width: auto; margin-left: auto; margin-right: auto;">
-<span style="text-align: center; font-size: 75%;"><sup>b</sup>Department of Informatics, Applied mathematics and Statistics, University of Girona, Campus Montilivi s/n, 17003, Girona Spain</span></div>
-−
-<div class="center" style="width: auto; margin-left: auto; margin-right: auto;">
-<span style="text-align: center; font-size: 75%;"><sup>c </sup>Chomarat, 39 Avenue de Chabannes, 07160, Le Cheylard, France</span></div>
-−
-{| style="width: 87%;border-collapse: collapse;"
-|-
-|  colspan='2'  style="vertical-align: top;"|<span id='OLE_LINK4'></span><big>Efecto del espesor de capa en la respuesta a impacto de laminados ‘non-crimp-fabric’ intercalados con velos: investigación por tomografía computarizada de Rayos-X</big>
-|-
-|  style="border-bottom: 1pt solid black;vertical-align: top;"|<span style="text-align: center; font-size: 75%;"> [[Image:Garcia-Rodriguez_et_al_2017a-image1.png|54px]] </span>
-|  style="vertical-align: top;"|
-|-
-|  style="border-top: 1pt solid black;border-bottom: 1pt solid black;vertical-align: top;"|<span style="text-align: center; font-size: 75%;">Historia del artículo:</span>
-−
-<span style="text-align: center; font-size: 75%;">Recibido 5 de Mayo 2017</span>
-−
-<span style="text-align: center; font-size: 75%;">En la versión revisada 5 de Mayo 2017</span>
-−
-<span style="text-align: center; font-size: 75%;">Aceptado 31 de Mayo 2017</span>
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-<span style="text-align: center; font-size: 75%;">Accesible online 21 de Junio 2017</span>
-|  rowspan='4' style="vertical-align: top;"|<span style="text-align: center; font-size: 75%;">Los materiales compuestos son susceptibles a cargas de impacto ya que éstas deterioran la integridad estructural de, por ejemplo, la piel del fuselaje de un avión. Por tanto, nuestro objetivo es mejorar la resistencia y tolerancia al daño de laminados finos (2.14-2.16 mm thickness) manufacturados con ‘non-crimp-fabrics’ (NCF) (a) reduciendo el espesor de capa convencional (considerando ‘thin-plies’ [1]) (b) intercalando velos no-tejidos</span><span style="text-align: center; font-size: 75%;">—‘non-woven veils’ [2]) de fibra de co-poliamida en las intercaras de laminados con capas finas. Para ello, hemos realizado ensayos de impacto, compresión después de impacto (CAI) e indentación cuasi-estática. Además, inspecciones por tomografía computarizada de rayos-X ilustran cómo grietas en la matriz, deslaminaciones y rotura de fibra interaccionan durante impacto e indentación. </span>
-−
-<span style="text-align: center; font-size: 75%;">Reducir el espesor de capa disminuye el tamaño de grietas y deslaminaciones a costa de una rotura de fibras prematura, disminuyendo la tolerancia al daño. Por otra parte, intercalar velos en laminados de capas ultradelgadas evita la iniciación de deslaminaciones y aumenta la resistencia a CAI. </span>
-−
-−
-|-
-|  style="border-top: 1pt solid black;border-bottom: 1pt solid black;vertical-align: top;"|<span style="text-align: center; font-size: 75%;">Palabras clave:</span>
-−
-<span style="text-align: center; font-size: 75%;">Impacto</span>
-−
-<span style="text-align: center; font-size: 75%;">Capas finas</span>
-−
-<span style="text-align: center; font-size: 75%;">Velos</span>
-−
-<span style="text-align: center; font-size: 75%;">Tomografía computarizada de rayos-X</span>
-|-
-|  style="border-top: 1pt solid black;vertical-align: top;"|
-|-
-|  colspan='2'  style="vertical-align: top;"|<big>Effect of ply-thickness on the impact response of interleaved thin-ply non-crimp-fabric laminates: X-ray tomography investigation</big>
-|-
-|  style="border-bottom: 1pt solid black;vertical-align: top;"|<span style="text-align: center; font-size: 75%;"> [[Image:Garcia-Rodriguez_et_al_2017a-image2.png|54px]] </span>
-|  style="vertical-align: top;"|
-|-
-|  style="border-top: 1pt solid black;border-bottom: 1pt solid black;vertical-align: top;"|<span style="text-align: center; font-size: 75%;">Keywords:</span>
-−
-<span style="text-align: center; font-size: 75%;">Impact</span>
-−
-<span style="text-align: center; font-size: 75%;">Thin-ply</span>
-−
-<span style="text-align: center; font-size: 75%;">Interleaving</span>
-−
-<span style="text-align: center; font-size: 75%;">X-ray micro-computed tomography</span>
-|  rowspan='2' style="vertical-align: top;"|<span style="text-align: center; font-size: 75%;">Composite laminates subjected to out-of-plane loads develop damage modes that compromise the load-carrying capacity, as in the fuselage skin of an aircraft. Therefore, we aimed to improve the damage resistance and tolerance of carbon/epoxy thin non-crimp fabric (NCF) laminates by (a) reducing the ‘conventional’ ply-thickness (i.e. comparing thick- and thin-plies) (b) interleaving co-polyamide (CoPA) non-woven veils at the interlaminar regions of thin-ply systems.</span><span style="text-align: center; font-size: 75%;">We devised an impact, compression after impact (CAI) and quasi-static indentation (QSI) experimental campaign, where computerized X-ray tomography provided detailed 3D insight on how matrix cracking, delamination and fibre failure interacted during impact and QSI. </span>
-−
-<span style="text-align: center; font-size: 75%;">Thin-ply laminates reduce the amount of matrix cracking and delamination at the cost of premature fibre breakage, therefore decreasing the damage tolerance. Interleaving CoPA veils arrests delamination onset and improves the residual strength with respect to the thin-ply baseline. </span>
-|-
-|  style="border-top: 1pt solid black;vertical-align: top;"|
-|}
-−
-−
 ==1 Introduction ==
@@ Line 98: / Line 29: @@
 Every indented specimen and representative impacted specimens were inspected by µCT. To improve the signal-to-noise ratio, indented specimens were cut through-the-width prior to inspection (Figure 1b)) [24]. The use of penetrant dies was avoided to ensure that matrix cracking and delamination were observed regardless their interconnection.
+[[File:Garcia-Rodriguez_et_al_2017a-image5-c.png|centre|600x600px]]
-''' [[Image:Garcia-Rodriguez_et_al_2017a-image5-c.png|600px]] '''
+'''  '''
 <div class="center" style="width: auto; margin-left: auto; margin-right: auto;">
-<span style="text-align: center; font-size: 75%;">'''Figure 1 '''a) Non-conventional compression after impact (CAI) test fixture (based on Remacha M. ''et al. ''(2015) [23]) b) Specimens cutting prior to inspection by micro-computed tomography (µCT)</span></div>
+<span style="text-align: center; font-size: 75%;">'''Figure 1 '''a) Non-conventional compression after impact (CAI) test fixture (based on Remacha M. ''et al. ''(2015) [23]) b) Specimens cutting prior to inspection by micro-computed tomography (µCT).</span></div>
 In indented specimens, the position of the inspected sample with respect to the X-ray souce and the detector was adjusted to observe the totality of the damage scenario (as previously observed by C-scan). This yielded to voxel sizes of 5 µm (d= 4 and 4.4 mm) and 7 µm (5.24 mm). In impacted specimens, only a detailed zone centred at the impact point was observed; voxel sizes of 6.5 and 10 µm for 10 and 14 J energy. Finally, in some cases, damage mechanisms were represented in 3D using the software Starviewer [25].

@@ Line 202: / Line 202: @@
 ==References ==
-<span style="text-align: center; font-size: 75%;">[1] S.Sihn, R.Y. Kim, K.Kawabe and S.W. Tsai, ''Compos. Sci. Technol.'', vol. '''67''', no. 6, pp. 996–1008 (2007).</span> <span style="text-align: center; font-size: 75%;">[https://doi.org/10.1016/j.compscitech.2006.06.008 https://doi.org/10.1016/j.compscitech.2006.06.008]</span>
+[1] S.Sihn, R.Y. Kim, K.Kawabe and S.W. Tsai, ''Compos. Sci. Technol.'', vol. '''67''', no. 6, pp. 996–1008 (2007).[https://doi.org/10.1016/j.compscitech.2006.06.008 https://doi.org/10.1016/j.compscitech.2006.06.008]
-<span style="text-align: center; font-size: 75%;">[2] V.A.Ramirez, P.J.Hogg and W.W.Sampson, ''Compos. Sci. Technol.'', vol. '''110''', pp. 103–110 (2015).</span> <span style="text-align: center; font-size: 75%;">[https://doi.org/10.1016/j.compscitech.2015.01.016 https://doi.org/10.1016/j.compscitech.2015.01.016]</span>
+[2] V.A.Ramirez, P.J.Hogg and W.W.Sampson, ''Compos. Sci. Technol.'', vol. '''110''', pp. 103–110 (2015). [https://doi.org/10.1016/j.compscitech.2015.01.016 https://doi.org/10.1016/j.compscitech.2015.01.016]
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