Garcia-Moreno et al 2017a - Revision history

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Scipediacontent: Scipediacontent moved page Draft Content 580462961 to Garcia-Moreno et al 2017a

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Scipediacontent moved page Draft Content 580462961 to Garcia-Moreno et al 2017a

Scipediacontent: Created page with "== Abstract == Carbon/epoxy pre-impregnated has become one of the most demanded materials for some aeronautics structures. Boeing 787 and Airbus A350 are pioneers in incorpor..."

2022-03-31T12:54:54Z

Created page with "== Abstract == Carbon/epoxy pre-impregnated has become one of the most demanded materials for some aeronautics structures. Boeing 787 and Airbus A350 are pioneers in incorpor..."

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== Abstract ==

Carbon/epoxy pre-impregnated has become one of the most demanded materials for some aeronautics structures. Boeing 787 and Airbus A350 are pioneers in incorporating carbon fiber-reinforced composite materials in primary structures as wings and airframe. Tailoring the laminate ply sequence involves a difficult challenge owing to the rigorous design and operational criteria. Given that composite materials present a high sensitivity to impact loads, it has been indispensable to examine the influence of different factors in the failure mechanisms after an impact event. In this work, the effect of impact energy, stacking sequence and thickness on the impact damage resistance of CFRP composites was investigated. Damage response parameters as peak force, absorbed energy and delamination threshold were obtained from the impact curves. Then, a C-Scan imagen showed the damage extension using the non-destructive inspection Phased Array.

== Full document ==
<pdf>Media:Draft_Content_580462961native-articles-33.pdf</pdf>

@@ Line 115: / Line 115: @@
 a) The absorbed energy by the laminate coincides with the impact energy which means that all the kinetic energy has been transferred from the impactor to the specimen but without penetration. This behavior can be observed in the curve for the 8-ply laminate in Fig. 3.
-[[File:Captura de pantalla 2022-09-05 195455.png|centre|thumb]]
+[[File:Captura de pantalla 2022-09-05 195455.png|centre|600px]]
 <div class="center" style="width: auto; margin-left: auto; margin-right: auto;">
 <span style="text-align: center; font-size: 75%;">'''Figure 3.''' Absorbed energy-time diagram [(0/90)n]s (n=2, 3, 6), (30 J).</span></div>
@@ Line 124: / Line 124: @@
 In the case that penetration occurs, the curve of energy performs in a different way. The penetration energy is located at the point where the curve remains almost constant in the force-time diagram but the energy increases with a constant rate as a result of the friction between the impactor and the perforation edges. A typical absorbed energy-time curve with penetration for a [0/90]<sub>2s</sub> laminate is presented in Fig. 4.
-<div class="center" style="width: auto; margin-left: auto; margin-right: auto;">[[File:Captura de pantalla 2022-09-05 195553.png|centre|453x453px]]<span style="text-align: center; font-size: 75%;">'''Figure 4.''' Abs. energy-time diagram with perforation [(0/90)2]s (50 J).</span> </div>
+<div class="center" style="width: auto; margin-left: auto; margin-right: auto;">[[File:Captura de pantalla 2022-09-05 195553.png|centre|600px]]<span style="text-align: center; font-size: 75%;">'''Figure 4.''' Abs. energy-time diagram with perforation [(0/90)2]s (50 J).</span> </div>
  Force-displacement diagram.
@@ Line 133: / Line 133: @@
 <div class="center" style="width: auto; margin-left: auto; margin-right: auto;"></div>
-[[File:Captura de pantalla 2022-09-05 195722.png|centre|thumb]]
+[[File:Captura de pantalla 2022-09-05 195722.png|centre|600px]]
 <div class="center" style="width: auto; margin-left: auto; margin-right: auto;">
 <span style="text-align: center; font-size: 75%;">'''Figure 5.''' Force-displacement diagram [(0/90)n]s, ( 50 J).</span></div>
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 <div class="center" style="width: auto; margin-left: auto; margin-right: auto;">
-  [[Image:Garcia-Moreno_et_al_2017a-image8.png|264px]] </div>
+  [[Image:Garcia-Moreno_et_al_2017a-image8.png|600px]] </div>
 <div class="center" style="width: auto; margin-left: auto; margin-right: auto;">

@@ Line 188: / Line 188: @@
   [[Image:Garcia-Moreno_et_al_2017a-image13.png|414px]] </div>
-<span style="text-align: center; font-size: 75%;">'''Figure 10.''' </span>Ultrasonic images of the impact area for a Cross Ply configuration. a), c) and e): 20 J impact; b), d) and f): 30 J impact.
+<div class="center" style="width: auto; margin-left: auto; margin-right: auto;">[[File:Captura de pantalla 2022-09-05 195553.png|centre|453x453px]]<span style="text-align: center; font-size: 75%;">'''Figure 4.''' Ultrasonic images of the impact area for a Cross Ply configuration. a), c) and e): 20 J impact; b), d) and f): 30 J impact.
 ==='''3.2''' Stacking sequence effect===

@@ Line 135: / Line 135: @@
 [[File:Captura de pantalla 2022-09-05 195722.png|centre|thumb]]
 <div class="center" style="width: auto; margin-left: auto; margin-right: auto;">
-<span style="text-align: center; font-size: 75%;">'''Figure 5.''' Force-displacement diagram [(0/90)n]s, ( 50 J)</span></div>
+<span style="text-align: center; font-size: 75%;">'''Figure 5.''' Force-displacement diagram [(0/90)n]s, ( 50 J).</span></div>
 ==='''2.3''' Ultrasonic Phased Array ===
@@ Line 146: / Line 146: @@
 <div class="center" style="width: auto; margin-left: auto; margin-right: auto;">
-<span style="text-align: center; font-size: 75%;">'''Figure 6.''' Transductor Phased Array</span></div>
+<span style="text-align: center; font-size: 75%;">'''Figure 6.''' Transductor Phased Array.</span></div>
 The method selected for the inspection is a raster scan as it is described in Fig. 7. A total of three sweeps have been necessary to obtain a complete view of the damage extension in the plane. A superposed band between sweeps is required to avoid the loss of information about the damage in these zones. The origin has been defined as ‘A’ and it is convenient to maintain a security zone near the edges.
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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 7.''' Raster Scan map for the Ultrasonic inspection</span></div>
+<span style="text-align: center; font-size: 75%;">'''Figure 7.''' Raster Scan map for the Ultrasonic inspection.</span></div>
 A C-Scan imagen is characterized by a scale where color represents the registered signal amplitude or depth at each point. In this work, each color corresponds to a different depth in which the reflection of the ultrasonic beam occurs. The maximum value in the scale is 6 mm marked by the thickest laminate. Delamination causes the beam reflection due to a discontinuity in the material, but other failure mechanisms are more difficult to detect and require different inspection techniques.
@@ Line 169: / Line 169: @@
 <div class="center" style="width: auto; margin-left: auto; margin-right: auto;">
-<span style="text-align: center; font-size: 75%;">'''Figure 8.''' Summary of the different case studies</span></div>
+<span style="text-align: center; font-size: 75%;">'''Figure 8.''' Summary of the different case studies.</span></div>
 ==='''3.1''' Impact energy and thickness effect===
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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 9.''' Summary of the different case studies</span></div>
+<span style="text-align: center; font-size: 75%;">'''Figure 9.''' Summary of the different case studies.</span></div>
 <div class="center" style="width: auto; margin-left: auto; margin-right: auto;">
   [[Image:Garcia-Moreno_et_al_2017a-image13.png|414px]] </div>
-<span style="text-align: center; font-size: 75%;">'''Figure 10.''' </span>Ultrasonic images of the impact area for a Cross Ply configuration. a), c) and e): 20 J impact; b), d) and f): 30 J impact
+<span style="text-align: center; font-size: 75%;">'''Figure 10.''' </span>Ultrasonic images of the impact area for a Cross Ply configuration. a), c) and e): 20 J impact; b), d) and f): 30 J impact.
 ==='''3.2''' Stacking sequence effect===
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 {|
 |-
-| [[Image:Garcia-Moreno_et_al_2017a-image15-c.png|264px]]
+|[[File:Captura de pantalla 2022-09-05 200002.png|centre|264x264px]]
 | [[Image:Garcia-Moreno_et_al_2017a-image16.png|center|240px]]
 |}
 </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 12.''' Absorbed energy impact diagrams for 24 and 8 plies laminates and 30 J impact. Cross ply, Angle Ply and Quasi-Isotropic stacking sequence</span></div>
+<span style="text-align: center; font-size: 75%;">'''Figure 12.''' Absorbed energy impact diagrams for 24 and 8 plies laminates and 30 J impact. Cross ply, Angle Ply and Quasi-Isotropic stacking sequence.</span></div>
+[[File:Garcia-Moreno_et_al_2017a-image19-c.png|centre|379x379px]]
-[[Image:Garcia-Moreno_et_al_2017a-image19-c.png|600px]]
 <div class="center" style="width: auto; margin-left: auto; margin-right: auto;">
-  [[Image:Garcia-Moreno_et_al_2017a-image20-c.png|516px]] </div>
+  [[Image:Garcia-Moreno_et_al_2017a-image20-c.png|384x384px]] </div>
 <div class="center" style="width: auto; margin-left: auto; margin-right: auto;">
-<span style="text-align: center; font-size: 75%;">'''Figure 13.''' Absorbed energy impact diagrams for 16 plies laminates and 30 J impact. Cross ply, Angle Ply and Quasi-Isotropic with ply level sequence</span></div>
+<span style="text-align: center; font-size: 75%;">'''Figure 13.''' Absorbed energy impact diagrams for 16 plies laminates and 30 J impact. Cross ply, Angle Ply and Quasi-Isotropic with ply level sequence.</span></div>
 ==='''3.3''' Sublaminate / Ply level sequence===

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 Fig. 5 represents three typical force-displacement curves encountered in an impact event. The first part of the curve is linear and represents the stiffness of the non-damaged laminate. The second part of the curve can perform in two different ways resulting in closed and open type curves, respectively. Open type force-displacement curves have a horizontal section at the end due to damage perforation in the specimens. 8-ply laminate in Fig. 5 shows an open force-displacement curve. In contrast, for specimens having rebounding there is an elastic recovery because the impact energy is unable to cause perforation and both, force and displacement decrease resulting in closed curves in which the enclosed areas represent the absorbed energy [12]. 16-ply and 24-ply laminates in Fig. 5 show closed force-displacement curve.
-<div class="center" style="width: auto; margin-left: auto; margin-right: auto;">
+<div class="center" style="width: auto; margin-left: auto; margin-right: auto;"></div>
+[[File:Captura de pantalla 2022-09-05 195722.png|centre|thumb]]
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-| [[Image:Garcia-Moreno_et_al_2017a-picture-Cuadro de texto 18.svg|center|71px]]
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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 5.''' Force-displacement diagram [(0/90)n]s, ( 50 J)</span></div>
@@ Line 157: / Line 143: @@
 The device used in this work is the Olympus OmniScan MX2 with 64 elements at 5 MHz. The purpose of the ultrasonic inspection is to identify the area affected by the low velocity impact in the material. C-Scan images are the most useful view in this work because provide a two dimensional presentation of data displayed as a top or planar view of the specimen where the damage extension can be represented completely. A mechanical scanner with encoders was used to track the transducer’s coordinates to the desired index resolution as it is shown in Fig. 6.
-<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 2022-09-05 195801.png|centre|414x414px]]</div>
-−
-{|
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-| [[Image:Garcia-Moreno_et_al_2017a-picture-Cuadro de texto 27.svg|center|70px]]
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- [[Image:Garcia-Moreno_et_al_2017a-image7.png|414px]] </div>
 <div class="center" style="width: auto; margin-left: auto; margin-right: auto;">

@@ Line 115: / Line 115: @@
 a) The absorbed energy by the laminate coincides with the impact energy which means that all the kinetic energy has been transferred from the impactor to the specimen but without penetration. This behavior can be observed in the curve for the 8-ply laminate in Fig. 3.
+[[File:Captura de pantalla 2022-09-05 195455.png|centre|thumb]]
-{|
-|-
-| [[Image:Garcia-Moreno_et_al_2017a-picture-Cuadro de texto 11.svg|center|56px]]
-| [[Image:Garcia-Moreno_et_al_2017a-chart2.svg|center|516px]]
-|}
-−
-−
 <div class="center" style="width: auto; margin-left: auto; margin-right: auto;">
-<span style="text-align: center; font-size: 75%;">'''Figure 3.''' Absorbed energy-time diagram [(0/90)n]s (n=2, 3, 6), (30 J)</span></div>
+<span style="text-align: center; font-size: 75%;">'''Figure 3.''' Absorbed energy-time diagram [(0/90)n]s (n=2, 3, 6), (30 J).</span></div>
 b) If there is no penetration in the material, the energy decreases until it becomes stable. The value of energy at the end of the test corresponds to the permanent absorbed energy through various damage mechanisms as delamination, matrix cracking or fiber breakage [9]. The difference between the impact energy and the absorbed energy is named excessive energy and it is the responsible for the impactor rebound [10]. In other words, the excessive energy produces elastic deformation in the laminate. This is the case for the 16-ply and 24-ply laminates in Fig. 3.
 In the case that penetration occurs, the curve of energy performs in a different way. The penetration energy is located at the point where the curve remains almost constant in the force-time diagram but the energy increases with a constant rate as a result of the friction between the impactor and the perforation edges. A typical absorbed energy-time curve with penetration for a [0/90]<sub>2s</sub> laminate is presented in Fig. 4.
-<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 2022-09-05 195553.png|centre|453x453px]]<span style="text-align: center; font-size: 75%;">'''Figure 4.''' Abs. energy-time diagram with perforation [(0/90)2]s (50 J).</span> </div>
- [[Image:Garcia-Moreno_et_al_2017a-chart3.svg|456px]] </div>
-−
-<div class="center" style="width: auto; margin-left: auto; margin-right: auto;">
 <span style="text-align: center; font-size: 75%;">'''Figure 4.''' Abs. energy-time diagram with perforation [(0/90)2]s (50 J)</span></div>
  Force-displacement diagram.
@@ Line 142: / Line 130: @@
 The force-displacement diagram shows the laminate’s stiffness through the slope of the curve. Thereby a higher rigidity implies a steeper slope and a minor displacement of the material during the test [11].
 Fig. 5 represents three typical force-displacement curves encountered in an impact event. The first part of the curve is linear and represents the stiffness of the non-damaged laminate. The second part of the curve can perform in two different ways resulting in closed and open type curves, respectively. Open type force-displacement curves have a horizontal section at the end due to damage perforation in the specimens. 8-ply laminate in Fig. 5 shows an open force-displacement curve. In contrast, for specimens having rebounding there is an elastic recovery because the impact energy is unable to cause perforation and both, force and displacement decrease resulting in closed curves in which the enclosed areas represent the absorbed energy [12]. 16-ply and 24-ply laminates in Fig. 5 show closed force-displacement curve.

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