Graciani et al 2018a - Revision history

Materiales.Compuestos at 17:21, 14 October 2022

2022-10-14T17:21:43Z

Materiales.Compuestos at 17:20, 14 October 2022

2022-10-14T17:20:57Z

Show changes

Scipediacontent at 07:59, 3 May 2022

2022-05-03T07:59:51Z

Scipediacontent at 07:32, 3 May 2022

2022-05-03T07:32:32Z

Show changes

Scipediacontent: Scipediacontent moved page Draft Content 891914023 to Graciani et al 2018a

2022-03-31T15:51:14Z

Scipediacontent moved page Draft Content 891914023 to Graciani et al 2018a

Scipediacontent: Created page with "== Abstract == A comparative study of four different finite element (FE) models is presented, to determine the thermal deformations in a typical aeronautical structure. A det..."

2022-03-31T15:51:11Z

Created page with "== Abstract == A comparative study of four different finite element (FE) models is presented, to determine the thermal deformations in a typical aeronautical structure. A det..."

New page

== Abstract ==

A comparative study of four different finite element (FE) models is presented, to determine the thermal deformations in a typical aeronautical structure. A detailed FE model with solid elements is used as a reference to determine the accuracy given by three FE model with shell elements. The component consists in four planar laminates with (relatively small) curved zones at the joints.
The analysis shows that a correct modelling of the curved laminates is needed for obtaining accurate results.
If the FE model with shell elements ignores the existence of the curved zones, as is typically done in models used for stress calculations under pressures and loads, unsatisfactory results are obtained. Precision is not significantly increased if the curved zones are modelled in detail and the properties of the shell elements are defined as in the planar zones.
For this reason, a technique for modifying the in-plane thermal properties of the elements modelling the curved laminates, that forces them to follow the same shape changes observed in the real curved laminates is presented. The FE model with shell elements obtained with this technique provides the same accuracy than the FE model with solid elements, with a significantly lower computational cost.

== Full document ==
<pdf>Media:Draft_Content_891914023native-articles-153.pdf</pdf>

@@ Line 60: / Line 60: @@
 Se ha considerado que la lámina es transversalmente isótropa, por tanto, el comportamiento en el plano 23 (perpendicular a las fibras) es isótropo. Por consiguiente, el coeficiente de expansión térmica empleado en la dirección del espesor, <math display="inline">{\alpha }_{3}</math>, es idéntico a <math display="inline">{\alpha }_{2}</math>. Es difícil encontrar en la bibliografía información referente a medidas experimentales de <math display="inline">{\alpha }_{3}</math> en laminados de materiales compuestos, por lo tanto la validez de esta hipótesis es cuestionable. No obstante, las conclusiones del presente artículo no se ven afectadas por el hecho de emplear diferentes valores para <math display="inline">{\alpha }_{2}</math> y <math display="inline">{\alpha }_{3}</math>.
 {| style="width: 100%;border-collapse: collapse;"
 |-
@@ Line 100: / Line 102: @@
-<div class="center" style="width: auto; margin-left: auto; margin-right: auto;">
-<span style="text-align: center; font-size: 75%;">'''Tabla 1.''' Propiedades del material en ejes de ortotropía</span></div>
 Se asume que el curado ocurre a 180 C y la temperatura ambiente son 25 C, por tanto, en los modelos se considerará que la pieza ha sufrido un enfriamiento de 155 K.
@@ Line 107: / Line 108: @@
 El espesor de cada lámina es de 0.2 mm, y las secuencias de apilado de cada panel son las mostradas en la Tabla 2. Las fibras a 0 están orientadas en la dirección longitudinal del componente. La secuencia de apilado se aplica en cada componente en el sentido indicado por las flechas mostradas en la Fig. 2. Las orientaciones de 45, -45 y 90 se obtienen girando las fibras en el sentido indicado por dichas flechas y la regla de la mano derecha.
 {| style="width: 81%;margin: 1em auto 0.1em auto;border-collapse: collapse;"
 |-
@@ Line 120: / Line 123: @@
-<div class="center" style="width: auto; margin-left: auto; margin-right: auto;">
-<span style="text-align: center; font-size: 75%;">'''Tabla 2.''' Secuencia de apilado de los laminados</span></div>
 ==3 Modelo MEF con elementos sólidos==

@@ Line 349: / Line 349: @@
 <div class="center" style="width: auto; margin-left: auto; margin-right: auto;">
-  [[Image:Graciani_et_al_2018a-image14.png|600px]] </div>
+  [[Image:Graciani_et_al_2018a_9661_Graciani_Fig8.png|600px]] </div>
 <span id='OLE_LINK101'></span><span id='OLE_LINK102'></span><div id="OLE_LINK103" class="center" style="width: auto; margin-left: auto; margin-right: auto;">
@@ Line 357: / Line 357: @@
 <div id="OLE_LINK1" class="center" style="width: auto; margin-left: auto; margin-right: auto;">
-  [[Image:Graciani_et_al_2018a-image15.png|600px]] </div>
+  [[Image:Graciani_et_al_2018a_8814_Graciani_Fig9.png|600px]] </div>
 <div class="center" style="width: auto; margin-left: auto; margin-right: auto;">

← Older revision	Revision as of 15:51, 31 March 2022
(No difference)