Barbu et al 2022a - Revision history

Materiales.Compuestos at 17:15, 17 November 2022

2022-11-17T17:15:26Z

Materiales.Compuestos at 17:13, 17 November 2022

2022-11-17T17:13:27Z

Materiales.Compuestos: Materiales.Compuestos moved page Review 547815354168 to Barbu et al 2022a

2022-05-29T19:11:50Z

Materiales.Compuestos moved page Review 547815354168 to Barbu et al 2022a

Materiales.Compuestos: Materiales.Compuestos moved page Review 747983046108 to Review 547815354168

2022-05-28T09:51:04Z

Materiales.Compuestos moved page Review 747983046108 to Review 547815354168

Materiales.Compuestos: Materiales.Compuestos moved page Draft Compuestos 827471348 to Review 747983046108

2022-05-28T09:50:56Z

Materiales.Compuestos moved page Draft Compuestos 827471348 to Review 747983046108

Materiales.Compuestos at 19:35, 1 May 2022

2022-05-01T19:35:16Z

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Materiales.Compuestos: Created page with "
L.G. Barbu^ab, X. Martinez^ab, S. Oller^ac

2022-05-01T19:23:34Z

Created page with " <div class="center" style="width: auto; margin-left: auto; margin-right: auto;"> L.G. Barbu<sup>ab</sup>, X. Martinez<sup>ab</sup>, S. Oller<sup>ac</sup></div> <div class="..."
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 Regarding the composite used for the skin of the sandwich paned, two eco-composite panels (CR and RR) were manufactured at AI-CRT and delivered to UNIMAN for mechanical testing. Prepreg materials for composite manufacturing was prepared and provided by Chinese partners. Details of the prepreg material used with a number, orientation and dimensions of the plies and the thickness for the skin composite are given in table 1. Only the ramie rosin RR composite has been considered for the numerical simulation of the four point bending case so the data for this composite is shown.
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 |  style="border: 1pt solid black;text-align: center;vertical-align: top;"|2.11 ± 0.01
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 The ramie rosin sandwich (SRR) composite  has a core made from 1 layer of green honeycomb oriented in the L direction and the skins are made from the woven composite described in Table 1, applied in 5 layers in the 0º warp direction. The total thickness of the panel is 12 mm.
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 The micro-model developed to analyze the skin of the sandwich specimen is shown in Figure 4. The model has been developed in accordance with the microstructure observed in the same figure.  The geometry has been meshed with four node tetrahedrons in a total of 9547 finite elements and 2287 nodes. The mesh can be seen in Figure 5.
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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.''' Geometry of the woven ramie RVE together with the real microstructure.</span></div>
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 | [[Image:Draft_Compuestos_827471348-image11-c.png|center|282px]]
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 In order to numerically model the core of the sandwich panel a honeycomb RVE has been developed. The geometry together with a view of the real internal structure of the honeycomb can be observed in Figure 6. In Figure 7 the mesh used in the numerical simulation can be seen together with a zoom where the discretization in the thickness of the honeycomb wall can be observed. The geometry was meshed into 9600 linear hexahedral elements and 15666 nodes with two elements in the thickness direction of the honeycomb wall.
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 <div class="center" style="width: auto; margin-left: auto; margin-right: auto;">
 <span style="text-align: center; font-size: 75%;">'''Figura 6.''' Geometry of the honeycomb RVE together with the real microstructure.</span></div>
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 The behavior of the honeycomb RVE has also been studied in a different simulation. The macromodel consisted this time of only one linear hexahedral FE with 8 integration points. The movement of one face of the element has been restricted and a tensile displacement has been applied on its opposite face. At each of these integration points the honeycomb RVE has been computed. The material properties of the RVE are shown in Table 2. These values were calibrated to be same as the standard values available for a HexWeb A1 honeycomb.
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 |  colspan='2'  style="border-bottom: 1pt solid black;text-align: center;"|0.0761
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 Figure 12 presents the distribution of the main tensile stresses on the honeycomb RVE.
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   [[Image:Draft_Compuestos_827471348-image24.png|456px]] </div>
-<span style="text-align: center; font-size: 75%;">'''Figure 16.''' Distribution of the internal damage variable on the honeycomb micromodel.</span>
+<div class="center" style="width: auto; margin-left: auto; margin-right: auto;">
 A comparison is made in Figure 17 between the behaviour of the model in the numerical simulation and in the experimental test in terms of the force – displacement curve. The reaction in the vertical direction is plotted versus the displacement of the node situated in the middle span of the specimen, on the inferior skin.

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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 1.''' Test specimens for 4PB: SCR (black) and SRR (yellow).</span></div>
+[[File:Draft_Compuestos_827471348-image6.png|centre|600x600px]]
-[[Image:Draft_Compuestos_827471348-image6.png|600px]]
 <div class="center" style="width: auto; margin-left: auto; margin-right: auto;">
 <span style="text-align: center; font-size: 75%;">'''Figure 2.''' View of the mesh used in the numerical simulation of the four point bending case.</span></div>
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 The behavior of the woven RR RVE has been analyzed by simulating a tensile test. The mesh used for the macro finite element model is shown in Figure 8. The mesh of the macromodel consists of 3500 linear hexahedral elements and 4928 nodes. At each integration point of the macro structure the woven RR RVE is computed in the first step of the linear domain.
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 The distribution of the main tensile stress is shown in Figure 9. The highest stress gradient can be seen, as expected, in the area closest to the tabs.
+[[File:Draft_Compuestos_827471348-image17-c.png|centre|600x600px]]
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 In Figure 13 the distribution of the main tensile stress can be seen on the deformed shape of the model for the two woven ramie rosin skins. As expected in a bending case, the tensile stresses appear on the inferior skin.
+[[File:Draft_Compuestos_827471348-image21-c.png|centre|600x600px]]
-[[Image:Draft_Compuestos_827471348-image21-c.png|600px]]
 <div class="center" style="width: auto; margin-left: auto; margin-right: auto;">
-<span style="text-align: center; font-size: 75%;">'''Figure 13.''' Distribution of the main tensile stress on the skins of the sandwich</span></div>
+<span style="text-align: center; font-size: 75%;">'''Figure 13.''' Distribution of the main tensile stress on the skins of the sandwich.</span></div>
 Figure 14 ehxibits the same result on the core of the sandwich where two symmetrical lateral areas are clearly marked as the most loaded ones.
+[[File:Draft_Compuestos_827471348-image22-c.png|centre|600x600px]]
-[[Image:Draft_Compuestos_827471348-image22-c.png|600px]]
 <div class="center" style="width: auto; margin-left: auto; margin-right: auto;">
-<span style="text-align: center; font-size: 75%;">'''Figure 14.''' Distribution of the main tensile stress on the honeycomb core</span></div>
+<span style="text-align: center; font-size: 75%;">'''Figure 14.''' Distribution of the main tensile stress on the honeycomb core.</span></div>
+[[File:Draft_Compuestos_827471348-image23-c.png|centre|600x600px]]
-[[Image:Draft_Compuestos_827471348-image23-c.png|600px]]
 <div class="center" style="width: auto; margin-left: auto; margin-right: auto;">
-<span style="text-align: center; font-size: 75%;">'''Figure 15.''' Distribution of the damage internal variable on the honeycomb core</span></div>
+<span style="text-align: center; font-size: 75%;">'''Figure 15.''' Distribution of the damage internal variable on the honeycomb core.</span></div>
 Figure 15 shows the distribution of the internal damage variable on the model. Damage appears in the area where bending stresses develop and the pattern observed on the two faces of the model is a diagonal distribution that is found in shear failures. This is consistent with the failure mode observed in the experiment.
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   [[Image:Draft_Compuestos_827471348-image24.png|456px]] </div>
-<span style="text-align: center; font-size: 75%;">'''Figure 16.''' Distribution of the internal damage variable on the honeycomb micromodel</span>
+<span style="text-align: center; font-size: 75%;">'''Figure 16.''' Distribution of the internal damage variable on the honeycomb micromodel.</span>
 A comparison is made in Figure 17 between the behaviour of the model in the numerical simulation and in the experimental test in terms of the force – displacement curve. The reaction in the vertical direction is plotted versus the displacement of the node situated in the middle span of the specimen, on the inferior skin.
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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 17.''' Comparison between the experimental and numerical force – displacement  curve</span></div>
+<span style="text-align: center; font-size: 75%;">'''Figure 17.''' Comparison between the experimental and numerical force – displacement  curve.</span></div>
 ==4 Conclusions==

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