Review 185315623460 - Revision history

Palomaluna at 12:10, 2 June 2022

2022-06-02T12:10:30Z

Palomaluna at 12:04, 2 June 2022

2022-06-02T12:04:14Z

Palomaluna at 11:52, 2 June 2022

2022-06-02T11:52:50Z

Palomaluna at 11:45, 2 June 2022

2022-06-02T11:45:16Z

Palomaluna at 09:44, 2 June 2022

2022-06-02T09:44:08Z

Palomaluna at 11:45, 3 May 2022

2022-05-03T11:45:55Z

Palomaluna at 07:47, 3 May 2022

2022-05-03T07:47:55Z

Palomaluna: Palomaluna moved page Draft Luna 627311235 to Review 185315623460

2022-04-29T11:56:30Z

Palomaluna moved page Draft Luna 627311235 to Review 185315623460

Palomaluna at 11:38, 29 April 2022

2022-04-29T11:38:00Z

Palomaluna: Created page with "
P. Luna ^(1), K. Munoz ⁽¹⁾, M. Jiménez ⁽¹⁾, M. Iglesias
2022-04-29T11:31:24Z

Created page with " <div class="center" style="width: auto; margin-left: auto; margin-right: auto;"> P. Luna (1), K. Munoz (1), M. Jiménez (1), M. Iglesias <s..."
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 To execute this protection, a novel procedure was developed based on the application of non-porous silicone material with capability of adhesion to the area under protection, resistance of the environmental conditions, and debonding capacity after the process. So this material adheres perfectly to the specimens’ surface and it is also easily removable
+[[File:Review_185315623460_5894_Figure-02.JPG|center|350px]]
 <div class="center" style="width: auto; margin-left: auto; margin-right: auto;">
 <span style="text-align: center; font-size: 75%;">'''Figure 2.''' Specimen protection application process</span></div>
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 The typical failure observed for patch repair configurations clearly showed that the failure of the test specimen initiated as a result of an adhesive failure. <span id='cite-_Ref99440264'></span>[[#_Ref99440264|<span style="text-align: center; font-size: 75%;">Figure 6</span>]] illustrates the failure mode of the patched test specimens.
+[[File:Review_185315623460_6520_Figure-06.JPG|center|350px]]
 <div id="_Ref99440264" class="center" style="width: auto; margin-left: auto; margin-right: auto;">
 <span style="text-align: center; font-size: 75%;">'''Figure 6.''' Typical failure mode for patch repair test specimens</span></div>

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 For the tension tests, specimens were prepared by bonding of glass fiber tabs. For this process, an epoxy adhesive was used and a careful surface preparation was followed in order to avoid premature failure during the test execution.
-[[File:Review_185315623460_6009_Figura 1.PNG|center|350px]]]
+[[File:Review_185315623460_6009_Figura 1.PNG|center|350px]]<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 1.''' a) and b) Thermoset specimens, total and partial repair configurations. c) and d) Thermoplastic specimens, reconsolidation and total patch pre-cure configurations</span></div>
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 To execute this protection, a novel procedure was developed based on the application of non-porous silicone material with capability of adhesion to the area under protection, resistance of the environmental conditions, and debonding capacity after the process. So this material adheres perfectly to the specimens’ surface and it is also easily removable
 <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;">
-  [[Image:Draft_Luna_627311235-image13-c.png|600px]] </div>
+  [[Image:Draft_Luna_627311235-image13-c.png|500x500px]] </div>
 <span id='_Ref100133485'></span><div id="_Ref100133481" class="center" style="width: auto; margin-left: auto; margin-right: auto;">
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 {| class="formulaSCP" style="width: 100%; text-align: center;"
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-{| style="text-align: center; margin:auto;"
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-| <math display="inline">\left| \frac{{W}_{i}-{W}_{i-1}}{{W}_{b}}\right| <0.0003\,</math>
-|}
 | style="width: 5px;text-align: right;white-space: nowrap;" | (1)
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 The acquisition equipment for performing the measurement of the strain gauges, the load and the position during the test execution is a Hottinger Bladwin MGCPlus.
-Specific test tooling was designed for the development of this test campaign. The jaws used to fix the test specimen during the test execution are crucial to obtain accurate results, especially where test forces of over 50kN are required. Specimens are clamped directly by jaws prior to the start of the tests. <span id='cite-_Ref97711863'></span>[[#_Ref97711863|Figure 4]] shows the designed and manufactured jaws used for the tension tests.
+Specific test tooling was designed for the development of this test campaign. The jaws used to fix the test specimen during the test execution are crucial to obtain accurate results, especially where test forces of over 50kN are required. Specimens are clamped directly by jaws prior to the start of the tests. <span id='cite-_Ref97711863'></span>[[#_Ref97711863|Figure 4]] shows the designed and manufactured jaws used for the tension tests.<div id="_Ref97711863" class="center" style="width: auto; margin-left: auto; margin-right: auto;">[[File:Figure-04.jpg|centre]]<span style="text-align: center; font-size: 75%;">'''Figure 4.''' Clamping jaws for tension tests</span></div>
-−
-{| style="width: 100%;margin: 1em auto 0.1em auto;border-collapse: collapse;"
-|-
-|  style="text-align: center;vertical-align: top;width: 49%;"|[[Image:Draft_Luna_627311235-image14.jpeg|264px]]
-|  style="text-align: center;vertical-align: top;width: 50%;"|[[Image:Draft_Luna_627311235-image15.jpeg|264px]]
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 <div id="_Ref97711863" class="center" style="width: auto; margin-left: auto; margin-right: auto;">
 <span style="text-align: center; font-size: 75%;">'''Figure 4.''' Clamping jaws for tension tests</span></div>
 ====2.3.3.1 Innovative monitoring system====
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 In <span id='cite-_Ref97711563'></span>[[#_Ref97711563|Figure 5]], the laser displacement sensor position is displayed. The sensor is placed at the base surface of the test machine and the receptor (pictured in blue in the figure) is positioned at the surface of the upper jaw.
+[[File:Figure-05.jpg|centre]]
-{| style="width: 100%;border-collapse: collapse;"
-|-
-|  style="vertical-align: top;width: 53%;"|[[Image:Draft_Luna_627311235-image16.png|354px]]
-|  style="vertical-align: top;width: 46%;"|[[Image:Draft_Luna_627311235-image17.png|336px]]
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 <div id="_Ref97711563" class="center" style="width: auto; margin-left: auto; margin-right: auto;">
 <span style="text-align: center; font-size: 75%;">'''Figure 5.''' Laser displacement sensor configuration in tension test </span></div>
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 The typical failure observed for patch repair configurations clearly showed that the failure of the test specimen initiated as a result of an adhesive failure. <span id='cite-_Ref99440264'></span>[[#_Ref99440264|<span style="text-align: center; font-size: 75%;">Figure 6</span>]] illustrates the failure mode of the patched test specimens.
 <div id="_Ref99440264" class="center" style="width: auto; margin-left: auto; margin-right: auto;">
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 Nevertheless, on the reconsolidation specimens the failure occurred as a result of fiber breakage which started in the center of the test specimen where the reconsolidation took place during the repair process. In this area, the fibers were broken and repaired so a greater concentration of stresses enable the failure occurrence in this area.  Because of greater rigidity is attributed to the 0º layers of the laminate, the fibers orientated in this direction were the first to fail, producing a failure perpendicular to the 0º direction later reoriented to the layers at ± 45º direction. <span id='cite-_Ref99446224'></span>[[#_Ref99446224|Figure 7]] illustrates the failure mode of this type of test specimens.
+[[File:Figure-07.jpg|centre]]
-{| style="width: 100%;border-collapse: collapse;"
-|-
-|  style="vertical-align: top;width: 49%;"|[[Image:Draft_Luna_627311235-image20.png|222px]]
-|  style="vertical-align: top;width: 50%;"|[[Image:Draft_Luna_627311235-image21.png|354px]]
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 <div id="_Ref99446224" class="center" style="width: auto; margin-left: auto; margin-right: auto;">
 <span style="text-align: center; font-size: 75%;">'''Figure 7. '''Typical failure mode for reconsolidation specimens</span></div>
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-  [[Image:Draft_Luna_627311235-image22.png|600px]] </div>
+  [[Image:Draft_Luna_627311235-image22.png]] </div>
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 For these specimens, no damage progression was observed. <span id='cite-_Ref102120023'></span>[[#_Ref102120023|Figure 9]] depicts the obtained C-Scans for the ISC-TP2B-F-ReB test specimen.
+[[File:Draft_Luna_627311235-image23.png|centre]]
-[[Image:Draft_Luna_627311235-image23.png|600px]]
 <div id="_Ref102120023" class="center" style="width: auto; margin-left: auto; margin-right: auto;">

← Older revision		Revision as of 11:45, 2 June 2022
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	For the tension tests, specimens were prepared by bonding of glass fiber tabs. For this process, an epoxy adhesive was used and a careful surface preparation was followed in order to avoid premature failure during the test execution.		For the tension tests, specimens were prepared by bonding of glass fiber tabs. For this process, an epoxy adhesive was used and a careful surface preparation was followed in order to avoid premature failure during the test execution.

−	[[File:Review_185315623460_6009_Figura 1.PNG]]	+	[[File:Review_185315623460_6009_Figura 1.PNG\|center\|350px]]]

← Older revision		Revision as of 09:44, 2 June 2022
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−
−
−	~~<div class="center" style="width: auto; margin-left: auto; margin-right: auto;">~~
−	P. Luna <sup>(1)*</sup>, K. Munoz <sup>(1)</sup>, M. Jiménez <sup>(1)</sup>, M. Iglesias <sup>(2)</sup>, B. De Nicolás <sup>(2)</sup>, B. Fantina <sup>(3)</sup>, E. Lorenzo-Villafranca <sup>(3)</sup></div>
−
−	~~<div class="center" style="width: auto; margin-left: auto; margin-right: auto;">~~
−	~~<span style="text-align: center; font-size: 75%;"><sup>(1)</sup> Element Materials Technology Seville</span></div>~~
−
−	~~<div class="center" style="width: auto; margin-left: auto; margin-right: auto;">~~
−	~~<span style="text-align: center; font-size: 75%;"><sup>(2)</sup> Airbus Defence and Space</span></div>~~
−
−	~~<div class="center" style="width: auto; margin-left: auto; margin-right: auto;">~~
−	~~<span style="text-align: center; font-size: 75%;"><sup>(3)</sup> FIDAMC, Fundación para la Investigación, Desarrollo y Aplicación de Materiales Compuestos</span></div>~~
−
−	~~{\| style="width: 87%;border-collapse: collapse;"~~
−	\|-
−	~~\| colspan='2' style="vertical-align: top;"\|<big>Evaluación mecánica de diferentes conceptos de reparación en materiales termoplásticos y termoestables</big>~~
−	\|-
−	~~\| style="border-bottom: 1pt solid black;vertical-align: top;"\|<span style="text-align: center; font-size: 75%;"> [[Image:Draft_Luna_627311235-image1.png\|54px]] </span>~~
−	\| rowspan='5' style="vertical-align: top;"\|<span style="text-align: center; font-size: 75%;">La reparación de materiales compuestos de matriz polimérica de naturaleza termoplástica y termoestable es cada vez más demandada en la industria aeronáutica por sus necesidad de conocer, en función de la aproximación realizada, la resistencia residual recuperada. Para garantizar la seguridad y viabilidad de los procesos de reparación, así como su durabilidad a lo largo de su ciclo de vida, es necesario validar las propiedades mecánicas de elementos estructurales tras </span><span style="text-align: center; font-size: 75%;">realizar reparaciones para eliminar los defectos o daños.</span>
−
−	<span style="text-align: center; font-size: 75%;">Este trabajo tiene como principal objetivo la validación tras envejecimiento de probetas reparadas de material compuesto que se han sometido a diferentes procesos de reparación.</span>
−
−	<span style="text-align: center; font-size: 75%;">Los conceptos de reparación analizados son denominados como “Prepreg”, “Seco” e “Híbrido” para el caso de material termoestable, y “Reconsolidación” y “parche preconsolidado” bajo distintas técnicas de integración para materiales de resina termoplástica. </span>
−
−	<span style="text-align: center; font-size: 75%;">Las probetas se han llevado a condiciones H/W de acuerdo a las especificaciones correspondientes. Adicionalmente, se han realizado protecciones y sellados sobre las mismas para simular lo más fielmente las posible condiciones de envejecimiento.</span>
−
−	<span style="text-align: center; font-size: 75%;">Asimismo, para cada tipo de material y configuración, se ha ensayado probetas utilizadas como referencia, es decir, sin daño y sin reparación, que permite monitorizar en cada caso el nivel de capacidad estructural recuperado. </span>
−
−	<span style="text-align: center; font-size: 75%;">La actividad de ensayos llevada a cabo se inscribe dentro del proyecto CERES (Advanced Rear End Structural test program – low level tests), bajo el marco de Clean Sky 2 JU.</span>
−	\|-
−	~~\| style="border-top: 1pt solid black;border-bottom: 1pt solid black;vertical-align: top;"\|~~
−	\|-
−	~~\| style="border-top: 1pt solid black;vertical-align: top;"\|<span style="text-align: center; font-size: 75%;">Keywords:</span>~~
−
−	~~<span style="text-align: center; font-size: 75%;">Materiales compuestos</span>~~
−
−	~~<span style="text-align: center; font-size: 75%;">Reparaciones</span>~~
−
−	~~<span style="text-align: center; font-size: 75%;">Caracterización mecánica</span>~~
−	\|-
−	~~\| style="border-top: 1pt solid black;vertical-align: top;"\|~~
−	\|-
−	~~\| colspan="2" style="vertical-align: top;" \|~~
−	\|-
−	~~\| colspan="2" \|<big>Mechanical evaluation of different repair concepts in thermoplastic and thermoset materials</big>~~
−	\|-
−	~~\| style="border-bottom: 1pt solid black;vertical-align: top;"\|<span style="text-align: center; font-size: 75%;"> [[Image:Draft_Luna_627311235-image2.png\|54px]] </span>~~
−	\| rowspan='3' style="vertical-align: top;"\|<span style="text-align: center; font-size: 75%;">The repair process of thermoplastic and thermoset polymeric matrix composite materials is being increasingly demanded in the aeronautic industry for the need to know, in relation to the performed approximation, the recovery of residual strenght. To ensure the security and the viability of the repair processes, as well as its durability throughout its life cycle, it is necessary to perform the validation of the mechanical properties of structural elements after the repair process to eliminate defects and damages</span><span style="text-align: center; font-size: 75%;">.</span>
−
−	~~<span style="text-align: center; font-size: 75%;">The aim of this work is to validate, after aging, different damaged composite repaired coupons that have undergone different repair processes.</span>~~
−
−	<span style="text-align: center; font-size: 75%;">The analyzed repair concepts are named as “Prepreg”, “Dry” and “Hybrid” for the thermoset material, and “Reconsolidation” and “Pre-consolidated patch” for different integration techniques of thermoplastic materials.</span>
−
−	<span style="text-align: center; font-size: 75%;">Test coupons have reached H/W conditions according to applicable specifications. Additionally, different protections have been performed on the specimens to faithfully simulate ageing conditions.</span>
−
−	<span style="text-align: center; font-size: 75%;">Furthermore, for each type of material and configuration, a reference test series meaning undamaged and unrepaired specimens has been tested to monitore in each case the level of recovered structural capacity.</span>
−
−	<span style="text-align: center; font-size: 75%;">This activity is part of the CERES (Advanced Rear End Structural test program – low level tests) project, which is framed under Clean Sky 2 JU.</span>
−	\|-
−	~~\| 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%;">Composite materials</span>~~
−
−	~~<span style="text-align: center; font-size: 75%;">Repairs</span>~~
−
−	~~<span style="text-align: center; font-size: 75%;">Mechanical characterization</span>~~
−	\|-
−	~~\| style="border-top: 1pt solid black;vertical-align: top;"\|~~
−	\|}
−
−
	==1 Introduction==		==1 Introduction==

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 For the tension tests, specimens were prepared by bonding of glass fiber tabs. For this process, an epoxy adhesive was used and a careful surface preparation was followed in order to avoid premature failure during the test execution.
-{| style="width: 100%;margin: 1em auto 0.1em auto;border-collapse: collapse;"
+[[File:Review_185315623460_6009_Figura 1.PNG]]
-|-
-|  style="text-align: center;vertical-align: top;width: 0%;"|[[Image:Draft_Luna_627311235-image5-c.jpeg|468px]]
-|  style="text-align: center;vertical-align: top;width: 45%;"|[[Image:Draft_Luna_627311235-image6.png|384x384px]]
-|  style="text-align: center;vertical-align: top;width: 54%;"|[[Image:Draft_Luna_627311235-image7-c.jpeg|462px]]
-|  style="text-align: center;vertical-align: top;width: 0%;"|[[Image:Draft_Luna_627311235-image8.png|462px]]
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 Because of composite structural characteristics, damage occurrence is a major topic in the use of this type of materials [2]. As its use has rapidly increased in industry, the need of a reliable repair technology has arisen.  For this reason, an intensive research is being carried out as a response to the industry demand.
-As part of this research, it is important to take into account in service conditions because the adhesives that constitutes the composite patch matrix and bond the repaired structure, are susceptible to degradation providing subsequent subsequent repair failure during operational life. Humidity and temperature are the most challenging threats in terms of environmental conditions, and their levels can be quite variable depending on many factors such as the location or the season. In order to validate the developed repair technologies it is important to take environmental influence into account, and reproduce these conditions by ageing the structures under controlled humidity and temperature conditions simulating the worst case scenario.
+As part of this research, it is important to take into account in service conditions because the adhesives that constitutes the composite patch matrix and bond the repaired structure, are susceptible to degradation providing subsequent repair failure during operational life. Humidity and temperature are the most challenging threats in terms of environmental conditions, and their levels can be quite variable depending on many factors such as the location or the season. In order to validate the developed repair technologies it is important to take environmental influence into account, and reproduce these conditions by ageing the structures under controlled humidity and temperature conditions simulating the worst case scenario.
 There are different types of repair solutions currently being applied into the repair process of composite materials. Moreover, the sector is devoting great efforts in the research of new or improved repair concepts that could be applicable into existing structures.
@@ Line 647: / Line 647: @@
 Being noted that the paper has been focused to provide some enhancements in different techniques around methodologies to be applied on coupon testing, results regarding repair test program are used to substantiate testing methodology.
 To complement the overall view, results on repairs conceptual studies carried on different types of substrate materials have been presented.
-First, in relation with the conditioning process of the test specimens, it was noted that the protection stage that was performed, successfully achieved its preliminary objective of avoiding humidity from entering through the edges. The protection that resulted from the newly developed method remained intact throughout the entire conditioning process, and was easily removable prior to the execution of the tests.
+The full set of results that has been presented is pending on deeper assessment. Therefore, the overview that has been provided should be considered as a good trend although provisional in regard to the final conclusion of the research to be carried on.
-Third, regarding the test results, the following conclusions have been found:
+In relation with the conditioning process of the test specimens, it was noted that the protection stage that was performed, successfully achieved its preliminary objective of avoiding humidity from entering through the edges. The protection that resulted from the newly developed method remained intact throughout the entire conditioning process, and was easily removable prior to the execution of the tests.
 For the thermoplastic test specimens it is noted that the behavior of patched and reconsolidated test specimens strongly varies for the static and fatigue tests. Meanwhile patched elements show a better strength performance, reconsolidated repairs evidence much better fatigue behavior under tension loads keeping the residual strength at the end of the life within a very good percentage with the average strength capability.
@@ Line 657: / Line 659: @@
 Thermoset overall repair behavior show much less performance that thermoplastics for all the repairs concepts being tested.
-Finally, this study is focused on the selection of the most efficient method regarding the repair con thermoplastic and thermoset specimens, and an up-scaling of the technology at component and structural level of higher geometrical complexity will be performed in light of the obtained results.
+Finally, this study is focused on the selection of the most efficient method regarding the repair of thermoplastic and thermoset specimens, and an up-scaling of the technology at component and structural level of higher geometrical complexity will be performed in light of the obtained results.
 ==Acknowledgments==

← Older revision	Revision as of 11:56, 29 April 2022
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-|  colspan='2'  style="vertical-align: top;"|<big>Mechanical evaluation of different repair concepts in thermoplastic and thermoset materials</big>
+| colspan="2" style="vertical-align: top;" |
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 |  style="border-bottom: 1pt solid black;vertical-align: top;"|<span style="text-align: center; font-size: 75%;"> [[Image:Draft_Luna_627311235-image2.png|54px]] </span>
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-|  style="text-align: center;vertical-align: top;width: 45%;"|[[Image:Draft_Luna_627311235-image6.png|468px]]
+|  style="text-align: center;vertical-align: top;width: 45%;"|[[Image:Draft_Luna_627311235-image6.png|384x384px]]
 |  style="text-align: center;vertical-align: top;width: 54%;"|[[Image:Draft_Luna_627311235-image7-c.jpeg|462px]]
 |  style="text-align: center;vertical-align: top;width: 0%;"|[[Image:Draft_Luna_627311235-image8.png|462px]]