Munoz et al 2022a - Revision history

Xmartinez: Xmartinez moved page Review 992489870078 to Munoz et al 2022a

2022-06-20T17:59:39Z

Xmartinez moved page Review 992489870078 to Munoz et al 2022a

Kirsa at 10:41, 20 June 2022

2022-06-20T10:41:40Z

Kirsa at 10:37, 20 June 2022

2022-06-20T10:37:18Z

Kirsa at 12:21, 17 June 2022

2022-06-17T12:21:01Z

Kirsa at 12:13, 17 June 2022

2022-06-17T12:13:43Z

Kirsa at 12:05, 17 June 2022

2022-06-17T12:05:38Z

Kirsa at 12:04, 17 June 2022

2022-06-17T12:04:26Z

Kirsa at 12:02, 17 June 2022

2022-06-17T12:02:16Z

Kirsa at 11:39, 17 June 2022

2022-06-17T11:39:34Z

Kirsa at 15:26, 14 June 2022

2022-06-14T15:26:50Z

@@ Line 210: / Line 210: @@
 ==='''3.1''' Crippling tests===
-The figure 13 shows an example of the crippling specimens after failure and its corresponding image taken from the High-Speed camera recording (figure 14). Explosive failure mode is observed for all of the specimens.
+The Figure 13 shows an example of the crippling specimens after failure and its corresponding image taken from the High-Speed camera recording (Figure 14). Explosive failure mode is observed for all of the specimens.
 [[File:CR failure.jpg|thumb|Figure 13. Failure mode of crippling specimen #7 ]]
 <span id="cite-_Ref63853781"></span><span id="_Ref63853781"></span><span id="_Toc65153950"></span><span id="cite-_Ref65057415"></span>
@@ Line 240: / Line 240: @@
 <span id='_Ref65065410'></span><span id='_Toc65154109'></span><div id="_Toc84595086" class="center" style="width: auto; margin-left: auto; margin-right: auto;">
-<span style="text-align: center; font-size: 75%;">'''Figure ''' '''15''' '''. '''Evolution of the strain level in the specimen CR-4, measured through Digital Image Correlation, at (a) 0%; (b) 25%; (c) 50%; (d) 75%; (e) 100% of failure load.</span></div>
+<span style="text-align: center; font-size: 75%;">'''Figure''' '''15. '''Evolution of the strain level in the specimen CR-4, measured through Digital Image Correlation, at (a) 0%; (b) 25%; (c) 50%; (d) 75%; (e) 100% of failure load.</span></div>
-An example of load curve (expressed as percentage of failure load) correlated with the signal from sound-level meter is shown in the Figure 15. It can be observed that sound peaks match with small load drops before failure, which correspond to intermediate cracks in the specimen throughout the test.
+An example of load curve (expressed as percentage of failure load) correlated with the signal from sound-level meter is shown in the Figure 16. It can be observed that sound peaks match with small load drops before failure, which correspond to intermediate cracks in the specimen throughout the test.
 Higher failure loads are observed for specimens CR-6 and CR-7. This is due to the greater thickness of these specimens, which were extracted from a section of panel area with extra thickness. From the mechanical test results, it can be stated that influence of span is not significant for this test specimen geometry.  <span id="cite-_Ref100071140"></span><div id="_Ref100071140" class="center" style="width: auto; margin-left: auto; margin-right: auto;">[[File:CR graf.jpg|thumb|441x441px|Figure 16. Percentage of failure load and sound curves of the specimen CR-4.]]</div>
@@ Line 256: / Line 256: @@
 <span style="text-align: center; font-size: 75%;">'''Figure 17. '''Failure mode of the first unfolding specimen. Similar failure was found in the specimen #2.</span></div>
-For this purpose, fastener clamping was proposed for the following test. This configuration resulted in a significant skin flexure took place during the test, leading to skin delamination before the final unfolding failure. The specimen after failure is shown in the Figure 17. <span id='cite-_Ref97206344'></span>
+For this purpose, fastener clamping was proposed for the following test. This configuration resulted in a significant skin flexure took place during the test, leading to skin delamination before the final unfolding failure. The specimen after failure is shown in the Figure 18. <span id='cite-_Ref97206344'></span>
 {| style="width: 100%;border-collapse: collapse;"
@@ Line 272: / Line 272: @@
 Debonding specimen failure mode was the same for all the specimens.
-As it is shown in the Figure 18, the frame was debonded from the skin. Figure 19 shows an example of the progression of the debonding along with the load-displacement curve (load is expressed as percentage of failure load). The failure load in unfolding test configuration was 7 times higher than the failure load obtained in the debonding test configuration. <span id='cite-_Ref75520920'></span><span id='cite-_Ref76117293'></span><div class="center" style="width: auto; margin-left: auto; margin-right: auto;">
+As it is shown in the Figure 19, the frame was debonded from the skin. Figure 20 shows an example of the progression of the debonding along with the load-displacement curve (load is expressed as percentage of failure load). The failure load in unfolding test configuration was 7 times higher than the failure load obtained in the debonding test configuration. <span id='cite-_Ref75520920'></span><span id='cite-_Ref76117293'></span><div class="center" style="width: auto; margin-left: auto; margin-right: auto;">
   [[Image:Draft_Sanchez_378758303-image40-c.png|318px]] </div><span id="_Ref75520920"></span><div id="_Toc84595136" class="center" style="width: auto; margin-left: auto; margin-right: auto;">
 <span style="text-align: center; font-size: 75%;">'''Figure ''' '''19''' '''. '''Failure mode of the first debonding specimen.</span></div>
@@ Line 282: / Line 282: @@
 ==='''3.3''' Mouse hole tests===
-The Figure 20 shows the first mouse hole specimen after failure. As it can be observed, clip-stringer bolted joint failed. Debonding of skin-frame joint was also noticed.
+The Figure 21 shows the first mouse hole specimen after failure. As it can be observed, clip-stringer bolted joint failed. Debonding of skin-frame joint was also noticed.
-No damage was observed in the lateral edges of the specimen after failure (Figure 21).
+No damage was observed in the lateral edges of the specimen after failure (Figure 22).
-[[File:17. Mouse hole 1.png|thumb|377x377px|<span style="text-align: center; font-size: 75%;">'''Figure 20.''' Mouse hole specimen 1 after failure.</span>]]
+[[File:17. Mouse hole 1.png|thumb|377x377px|<span style="text-align: center; font-size: 75%;">'''Figure 21.''' Mouse hole specimen 1 after failure.</span>]]
 <span id="cite-_Ref65145648"></span><span id="_Ref65145648"></span><span id="_Toc65154113"></span><span id="cite-_Ref65146159"></span>
 <div class="center" style="width: auto; margin-left: auto; margin-right: auto;">
-''' [[Image:Draft_Sanchez_378758303-image43.jpeg|498px]]'''<span style="text-align: center; font-size: 75%;">'''Figure 21. '''Lateral edges of the mouse hole specimen 1 after failure.</span>
+''' [[Image:Draft_Sanchez_378758303-image43.jpeg|498px]]'''<span style="text-align: center; font-size: 75%;">'''Figure 22. '''Lateral edges of the mouse hole specimen 1 after failure.</span>
 </div><span id="_Ref65146159"></span><span id="_Toc65154115"></span><div id="_Toc84595170" class="center" style="width: auto; margin-left: auto; margin-right: auto;"></div>
-Figure 22 shows the second mouse hole specimen after failure. As it can be observed, the specimen failed due to frame-skin joint debonding. <span id="cite-_Ref75514671"></span>
+Figure 23 shows the second mouse hole specimen after failure. As it can be observed, the specimen failed due to frame-skin joint debonding. <span id="cite-_Ref75514671"></span>
 <div class="center" style="width: auto; margin-left: auto; margin-right: auto;">
 <nowiki> </nowiki>[[Image:Draft_Sanchez_378758303-image44-c.png|474px]]
-<span id="_Ref75514671"></span><span style="text-align: center; font-size: 75%;">'''Figure 22.''' Mouse hole specimen 2 after failure.</span>
+<span id="_Ref75514671"></span><span style="text-align: center; font-size: 75%;">'''Figure 23.''' Mouse hole specimen 2 after failure.</span>
 </div>

@@ Line 210: / Line 210: @@
 ==='''3.1''' Crippling tests===
-The figure 13 shows an example of the crippling specimens after failure and its corresponding image taken from the High-Speed camera recording (figure 14). Explosive failure mode is observed for all of the specimens.<span id='cite-_Ref63853781'></span><span id="_Ref63853781"></span><span id="_Toc65153950"></span><span id='cite-_Ref65057415'></span>
+The figure 13 shows an example of the crippling specimens after failure and its corresponding image taken from the High-Speed camera recording (figure 14). Explosive failure mode is observed for all of the specimens.
-[[File:Crippling test.jpg|thumb|Figure 13. Crippling test set-up.]]
+[[File:CR failure.jpg|thumb|Figure 13. Failure mode of crippling specimen #7 ]]
 [[File:HSC image.jpg|thumb|369x369px|Figure 14. High-Speed Camera image of crippling specimen #7.]]<span id="_Ref65057415"></span><span id="_Toc65154111"></span>Figure 15 shows the evolution of the strain level in the specimen CR-4, measured through Digital Image Correlation, at (a) 0% load; (b) 25% load; (c) 50% load; (d) 75% load; (e) 100% load. It is observed a uniform deformation of the skin side of the specimen.<span id='cite-_Ref65065410'></span>

@@ Line 274: / Line 274: @@
   [[Image:Draft_Sanchez_378758303-image40-c.png|318px]] </div><span id="_Ref75520920"></span><div id="_Toc84595136" class="center" style="width: auto; margin-left: auto; margin-right: auto;">
 <span style="text-align: center; font-size: 75%;">'''Figure ''' '''19''' '''. '''Failure mode of the first debonding specimen.</span></div>
+[[File:Debonding.jpg|thumb|Figure 20. Load-displacement curve of debonding test (specimen 2).]]
-<span id='_Ref76117293'></span><div id="_Toc84595137" class="center" style="width: auto; margin-left: auto; margin-right: auto;">
+<span id="_Ref76117293"></span><div id="_Toc84595137" class="center" style="width: auto; margin-left: auto; margin-right: auto;"></div>
-<span style="text-align: center; font-size: 75%;">'''Figure ''' '''20''' '''. '''Load-displacement curve of debonding test (specimen 2).</span></div>
 As a result of this campaign, a set of failure loads was obtained for the different failure modes along with useful information for the structural joint design solution that is to be applied on the thermoplastic fuselage panel design.

@@ Line 210: / Line 210: @@
 ==='''3.1''' Crippling tests===
-The figure 13 shows an example of the crippling specimens after failure and its corresponding image taken from the High-Speed camera recording (figure 14). Explosive failure mode is observed for all of the specimens. <span id='cite-_Ref63853781'></span><span id="_Ref63853781"></span><span id="_Toc65153950"></span><span id='cite-_Ref65057415'></span>
+The figure 13 shows an example of the crippling specimens after failure and its corresponding image taken from the High-Speed camera recording (figure 14). Explosive failure mode is observed for all of the specimens.<span id='cite-_Ref63853781'></span><span id="_Ref63853781"></span><span id="_Toc65153950"></span><span id='cite-_Ref65057415'></span>
 [[File:Crippling test.jpg|thumb|Figure 13. Crippling test set-up.]]
-[[File:HSC image.jpg|thumb|369x369px|Figure 14. High-Speed Camera image of crippling specimen #7.]]
+[[File:HSC image.jpg|thumb|369x369px|Figure 14. High-Speed Camera image of crippling specimen #7.]]<span id="_Ref65057415"></span><span id="_Toc65154111"></span>Figure 15 shows the evolution of the strain level in the specimen CR-4, measured through Digital Image Correlation, at (a) 0% load; (b) 25% load; (c) 50% load; (d) 75% load; (e) 100% load. It is observed a uniform deformation of the skin side of the specimen.<span id='cite-_Ref65065410'></span>
-<span id='_Ref65057415'></span><span id='_Toc65154111'></span><div id="_Toc84595088" class="center" style="width: auto; margin-left: auto; margin-right: auto;">
-<span style="text-align: center; font-size: 75%;">'''Figure 14. '''Failure mode of crippling specimen #7 and its image from High-Speed Camera recording.</span></div>
-−
 Figure 15 shows the evolution of the strain level in the specimen CR-4, measured through Digital Image Correlation, at (a) 0% load; (b) 25% load; (c) 50% load; (d) 75% load; (e) 100% load. It is observed a uniform deformation of the skin side of the specimen.<span id='cite-_Ref65065410'></span>
 {| style="width: 83%;border-collapse: collapse;"
@@ Line 247: / Line 243: @@
 An example of load curve (expressed as percentage of failure load) correlated with the signal from sound-level meter is shown in the Figure 15. It can be observed that sound peaks match with small load drops before failure, which correspond to intermediate cracks in the specimen throughout the test.
-Higher failure loads are observed for specimens CR-6 and CR-7. This is due to the greater thickness of these specimens, which were extracted from a section of panel area with extra thickness. From the mechanical test results, it can be stated that influence of span is not significant for this test specimen geometry.  <span id="cite-_Ref100071140"></span><div class="center" style="width: auto; margin-left: auto; margin-right: auto;"> </div>
+Higher failure loads are observed for specimens CR-6 and CR-7. This is due to the greater thickness of these specimens, which were extracted from a section of panel area with extra thickness. From the mechanical test results, it can be stated that influence of span is not significant for this test specimen geometry.  <span id="cite-_Ref100071140"></span><div id="_Ref100071140" class="center" style="width: auto; margin-left: auto; margin-right: auto;">[[File:CR graf.jpg|thumb|441x441px|Figure 16. Percentage of failure load and sound curves of the specimen CR-4.]]</div>
-−
 <div id="_Ref100071140" class="center" style="width: auto; margin-left: auto; margin-right: auto;">
-<span style="text-align: center; font-size: 75%;">'''Figure 16. '''Percentage of failure load and sound curves of the specimen CR-4.</span></div>
 ==='''3.2''' Unfolding and debonding tests===

@@ Line 210: / Line 210: @@
 ==='''3.1''' Crippling tests===
-The Figure 13 shows an example of the crippling specimens after failure and its corresponding image taken from the High-Speed camera recording. Explosive failure mode is observed for all of the specimens. <span id='cite-_Ref63853781'></span><span id="_Ref63853781"></span><span id="_Toc65153950"></span><span id='cite-_Ref65057415'></span>
+The figure 13 shows an example of the crippling specimens after failure and its corresponding image taken from the High-Speed camera recording (figure 14). Explosive failure mode is observed for all of the specimens. <span id='cite-_Ref63853781'></span><span id="_Ref63853781"></span><span id="_Toc65153950"></span><span id='cite-_Ref65057415'></span>
 [[File:Crippling test.jpg|thumb|Figure 13. Crippling test set-up.]]
 [[File:HSC image.jpg|thumb|369x369px|Figure 14. High-Speed Camera image of crippling specimen #7.]]
@@ Line 216: / Line 216: @@
 <span style="text-align: center; font-size: 75%;">'''Figure 14. '''Failure mode of crippling specimen #7 and its image from High-Speed Camera recording.</span></div>
-Figure 14 shows the evolution of the strain level in the specimen CR-4, measured through Digital Image Correlation, at (a) 0% load; (b) 25% load; (c) 50% load; (d) 75% load; (e) 100% load. It is observed a uniform deformation of the skin side of the specimen.<span id='cite-_Ref65065410'></span>
+Figure 15 shows the evolution of the strain level in the specimen CR-4, measured through Digital Image Correlation, at (a) 0% load; (b) 25% load; (c) 50% load; (d) 75% load; (e) 100% load. It is observed a uniform deformation of the skin side of the specimen.<span id='cite-_Ref65065410'></span>
 {| style="width: 83%;border-collapse: collapse;"

← Older revision	Revision as of 17:59, 20 June 2022
(No difference)

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 Crippling tests were performed by means of a SCHENCK 2.5 MN Universal Testing Machine. The set-up for crippling test is shown in the <span id='cite-_Ref97200546'></span>[[#_Ref97200546|Figure 4]]. First, a pre-test up to 15% of predicted failure load was executed. Then, the specimen was subjected to monotonic compression loading up to failure. The displacement rate was 0.5 mm/min. Data acquisition was performed using MGCPlus system, which allows high frequency data acquisition (100 Hz), real-time monitoring of the results (loads, displacements, strains), and synchronization of all the measurements.
-[[File:Crippling set-up.jpg|thumb|Crippling test set-up.]]
+[[File:Crippling set-up.jpg|thumb|Figure 4. Crippling test set-up.]]
 In addition to traditional strain gauges, digital image correlation (ARAMIS system) was included to obtain the strain field in the central area of some of the specimens (skin surface). To this end, the specimen was white-painted and this surface was then prepared to monitor strain level. Likewise, laser displacement sensor with 8 µm accuracy was used to obtain actual displacement of the specimen, and avoid the error coming from the adjustments of the test machine in displacement recording. Additionally, High-Speed Camera was used to study failure mode of these specimens.  Crack events were also recorded by means of a sound-level meter.
@@ Line 211: / Line 211: @@
 The Figure 13 shows an example of the crippling specimens after failure and its corresponding image taken from the High-Speed camera recording. Explosive failure mode is observed for all of the specimens. <span id='cite-_Ref63853781'></span><span id="_Ref63853781"></span><span id="_Toc65153950"></span><span id='cite-_Ref65057415'></span>
+[[File:Crippling test.jpg|thumb|Figure 13. Crippling test set-up.]]
 <span id='_Ref65057415'></span><span id='_Toc65154111'></span><div id="_Toc84595088" class="center" style="width: auto; margin-left: auto; margin-right: auto;">
 <span style="text-align: center; font-size: 75%;">'''Figure 14. '''Failure mode of crippling specimen #7 and its image from High-Speed Camera recording.</span></div>

← Older revision		Revision as of 15:26, 14 June 2022
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	The execution of this test campaign has allowed to obtain valuable information about the mechanical behaviour of the fuselage panel components. This knowledge will be applied in the final design of the curved thermoplastic panel. Future validation of this aerostructure as part of DELTA will finally have a positive environmental impact. Due to its re-usability and recyclability advantages, usage of thermoplastic resin based carbon fibre polymers will mainly contribute to the reduction of Greenhouse Gas (GHG) emissions.		The execution of this test campaign has allowed to obtain valuable information about the mechanical behaviour of the fuselage panel components. This knowledge will be applied in the final design of the curved thermoplastic panel. Future validation of this aerostructure as part of DELTA will finally have a positive environmental impact. Due to its re-usability and recyclability advantages, usage of thermoplastic resin based carbon fibre polymers will mainly contribute to the reduction of Greenhouse Gas (GHG) emissions.

		+	== 5 Acknowledgements ==
	The research leading to these results has gratefully received funding from the European JTI- CleanSky2 program under the Grant Agreement nº 831862 (DELTA). This project is coordinated by Element Seville, and lead by AERNNOVA, as Topic Manager. Likewise, the authors wish to thank the collaboration with FIDAMC, as manufacturer of panel specimen.		The research leading to these results has gratefully received funding from the European JTI- CleanSky2 program under the Grant Agreement nº 831862 (DELTA). This project is coordinated by Element Seville, and lead by AERNNOVA, as Topic Manager. Likewise, the authors wish to thank the collaboration with FIDAMC, as manufacturer of panel specimen.