Ma 2022a - Revision history

Rimni at 12:32, 7 February 2023

2023-02-07T12:32:13Z

Rimni at 12:30, 7 February 2023

2023-02-07T12:30:58Z

Rimni at 12:28, 7 February 2023

2023-02-07T12:28:48Z

Rimni at 12:28, 7 February 2023

2023-02-07T12:28:14Z

Rimni: /* References */

2023-02-07T11:53:45Z

‎References

Rimni at 11:30, 7 February 2023

2023-02-07T11:30:26Z

Rimni at 10:29, 7 February 2023

2023-02-07T10:29:03Z

Rimni at 10:08, 7 February 2023

2023-02-07T10:08:50Z

Rimni at 09:40, 7 February 2023

2023-02-07T09:40:17Z

Rimni: /* 4. Conclusions */

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‎4. Conclusions

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 ==2. Materials and methods==
-Off-axis specimens were cut at different orientations from a 24-ply Cetex® TC1200 PEEK/AS4 carbon/thermoplastic unidirectional laminate. The volume fraction of the resin is 34% and the nominal thickness of each layer is 0.14mm. Up to five off-axis angles <math>\theta = 15°</math>, 30°, 45°, 60°, 75°, along with two special angles 0° (longitudinal compression) and 90° (transverse compression) were selected to bring forth different failure modes and investigate their transition with each other. The sketch of the off-axis compression test specimen is shown in [[#img-1|Figure 1]]. Nominal dimensions of the specimens are 36mm(H)<math>\times</math>12mm(W)<math>\times</math>3mm (T). The area of the evaluation section is 12mm<math>\times</math>12mm. Parallelism tolerances of all opposing surfaces was strictly inspected, and the loading end surfaces were well polished before tests.
+Off-axis specimens were cut at different orientations from a 24-ply Cetex® TC1200 PEEK/AS4 carbon/thermoplastic unidirectional laminate. The volume fraction of the resin is 34% and the nominal thickness of each layer is 0.14mm. Up to five off-axis angles <math>\theta =</math> 15°, 30°, 45°, 60°, 75°, along with two special angles <math>\theta</math>° (longitudinal compression) and 90° (transverse compression) were selected to bring forth different failure modes and investigate their transition with each other. The sketch of the off-axis compression test specimen is shown in [[#img-1|Figure 1]]. Nominal dimensions of the specimens are 36mm(H)<math>\times</math>12mm(W)<math>\times</math>3mm (T). The area of the evaluation section is 12mm<math>\times</math>12mm. Parallelism tolerances of all opposing surfaces was strictly inspected, and the loading end surfaces were well polished before tests.
 <div id='img-1'></div>

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 ==2. Materials and methods==
-Off-axis specimens were cut at different orientations from a 24-ply Cetex® TC1200 PEEK/AS4 carbon/thermoplastic unidirectional laminate. The volume fraction of the resin is 34% and the nominal thickness of each layer is 0.14mm. Up to five off-axis angles θ = 15°, 30°, 45°, 60°, 75°, along with two special angles 0° (longitudinal compression) and 90° (transverse compression) were selected to bring forth different failure modes and investigate their transition with each other. The sketch of the off-axis compression test specimen is shown in [[#img-1|Figure 1]]. Nominal dimensions of the specimens are 36mm(H)<math>\times</math>12mm(W)<math>\times</math>3mm (T). The area of the evaluation section is 12mm<math>\times</math>12mm. Parallelism tolerances of all opposing surfaces was strictly inspected, and the loading end surfaces were well polished before tests.
+Off-axis specimens were cut at different orientations from a 24-ply Cetex® TC1200 PEEK/AS4 carbon/thermoplastic unidirectional laminate. The volume fraction of the resin is 34% and the nominal thickness of each layer is 0.14mm. Up to five off-axis angles <math>\theta = 15°</math>, 30°, 45°, 60°, 75°, along with two special angles 0° (longitudinal compression) and 90° (transverse compression) were selected to bring forth different failure modes and investigate their transition with each other. The sketch of the off-axis compression test specimen is shown in [[#img-1|Figure 1]]. Nominal dimensions of the specimens are 36mm(H)<math>\times</math>12mm(W)<math>\times</math>3mm (T). The area of the evaluation section is 12mm<math>\times</math>12mm. Parallelism tolerances of all opposing surfaces was strictly inspected, and the loading end surfaces were well polished before tests.
 <div id='img-1'></div>

@@ Line 268: / Line 268: @@
-The displacement and strain fields of a 60° off-axis specimen is shown in [[#img-10|Figure 10]] . High strain gradients along the fibre direction were captured prior to failure. Although some strain concentration areas are coincident with matrix cracking failure position, specimen surface with no fracture also exhibits strain concentration.
+The displacement and strain fields of a 60° off-axis specimen is shown in [[#img-10|Figure 10]]. High strain gradients along the fibre direction were captured prior to failure. Although some strain concentration areas are coincident with matrix cracking failure position, specimen surface with no fracture also exhibits strain concentration.
 <div id='img-10'></div>
@@ Line 320: / Line 320: @@
-The displacement and strain fields of a 90° on-axis transverse compression specimen is shown in [[#img-12|Figure 12]] . The specimen exhibits consistent displacement arrangement. Apparent strain concentrations of <math display="inline">{\epsilon }_{y}</math> appeared in accordance with final fracture site. Cracks would be originated from these peaks of strain values to form the fracture surface.
+The displacement and strain fields of a 90° on-axis transverse compression specimen is shown in [[#img-12|Figure 12]]. The specimen exhibits consistent displacement arrangement. Apparent strain concentrations of <math display="inline">{\epsilon }_{y}</math> appeared in accordance with final fracture site. Cracks would be originated from these peaks of strain values to form the fracture surface.
 <div id='img-12'></div>
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 Although vast amount of fractography investigations were carried out for thermoset composites [25], few research was emphasised on thermoplastic composites [26,27]. Some researchers have conducted fractography studies of thermoplastic composites under mode I and II fractures. The plastic behaviour of the thermoplastic matrix and its interaction with fibres during compressive/shear combined loadings still need fractographical analysis to reveal its failure mechanism.
-SEM observations were conducted on all tested specimens at the in-plane direction, which is perpendicular to the thickness direction. Due to the different scales of the fracture surface, SEM images were taken in vary magnifications and were shown in [[#img-13|Figure 13]] .
+SEM observations were conducted on all tested specimens at the in-plane direction, which is perpendicular to the thickness direction. Due to the different scales of the fracture surface, SEM images were taken in vary magnifications and were shown in [[#img-13|Figure 13]].
 <div id='img-13'></div>

@@ Line 216: / Line 216: @@
-The illustrated displacement fields in [[#img-8|Figures 8]]  (a) and (b) indicates that the displacement gradients were inerratic. However, the strain was not evenly distributed. Extreme strain concentrations are presented along the cracking route. The highest level of strain concentration indicates the matrix damage initiation site.
+The illustrated displacement fields in [[#img-8|Figures 8]](a) and (b) indicates that the displacement gradients were inerratic. However, the strain was not evenly distributed. Extreme strain concentrations are presented along the cracking route. The highest level of strain concentration indicates the matrix damage initiation site.
 <div id='img-8'></div>
@@ Line 385: / Line 385: @@
-Clear fibre kink-band can be identified for 0° and 15° off-axis specimens, indicating thoroughly developed fibre kinking failure mechanism. From the 15° off-axis specimen graphic, severe fibre buckling without fibre fracture at the boundary of the kink-band can be seen. Fibre kinking in both in-plane and out-of-plane directions were observed, indicates a three-dimensional failure mode. The kink-bands of 0° and 15° specimens share the same pattern. Generally, with sufficient lateral support from the matrix, fibres will fracture under shear stress instead of micro-buckling [1]. The ductile behaviour of the thermoplastic matrix often exhibits large plastic deformation and reduces lateral support to the fibres, micro-buckling was then triggered. Therefore, the scale of the kink band can be related to the mechanical parameters of the matrix. Compared to thermoset composites, the longer kink band length implies a relatively ductile matrix. The parameters that control the fibre kinking formation can be measured, which are the kink-band width <math display="inline">d</math> and kink-band incline angle <math display="inline">\alpha</math>  as shown in [[#img-14|Figure 14]] . The measured average kink-band width and incline angle are 911.96 μm and 27.28°, respectively.
+Clear fibre kink-band can be identified for 0° and 15° off-axis specimens, indicating thoroughly developed fibre kinking failure mechanism. From the 15° off-axis specimen graphic, severe fibre buckling without fibre fracture at the boundary of the kink-band can be seen. Fibre kinking in both in-plane and out-of-plane directions were observed, indicates a three-dimensional failure mode. The kink-bands of 0° and 15° specimens share the same pattern. Generally, with sufficient lateral support from the matrix, fibres will fracture under shear stress instead of micro-buckling [1]. The ductile behaviour of the thermoplastic matrix often exhibits large plastic deformation and reduces lateral support to the fibres, micro-buckling was then triggered. Therefore, the scale of the kink band can be related to the mechanical parameters of the matrix. Compared to thermoset composites, the longer kink band length implies a relatively ductile matrix. The parameters that control the fibre kinking formation can be measured, which are the kink-band width <math display="inline">d</math> and kink-band incline angle <math display="inline">\alpha</math>  as shown in [[#img-14|Figure 14]]. The measured average kink-band width and incline angle are 911.96 μm and 27.28°, respectively.
 <div id='img-14'></div>

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+[8]  Ueda M.,  Mimura K.,  Jeong T.-K. In situ observation of kink-band formation in a unidirectional carbon fiber reinforced plastic by X-ray computed tomography imaging. Adv. Compos. Mater., 25:1–13, 2014. [https://doi.org/10.1080/09243046.2014.973173. https://doi.org/10.1080/09243046.2014.973173.]
 [9] S.T. Pinho, L. Iannucci, P. Robinson, Physically-based failure models and criteria for laminated fibre-reinforced composites with emphasis on fibre kinking: Part I: Development, Compos. Part Appl. Sci. Manuf. 37 (2006) 63–73. [https://doi.org/10.1016/j.compositesa.2005.04.016. https://doi.org/10.1016/j.compositesa.2005.04.016.]

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+[1]  Jelf P.M.,  Fleck N.A. Compression failure mechanisms in unidirectional composites. J. Compos. Mater., 26:2706–2726, 1992. [https://doi.org/10.1177/002199839202601804. https://doi.org/10.1177/002199839202601804.]
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← Older revision		Revision as of 09:40, 7 February 2023
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	==References==		==References==
		+
		+	<div class="auto" style="text-align: left;width: auto; margin-left: auto; margin-right: auto;font-size: 85%;">

	[1] P.M. Jelf, N.A. Fleck, Compression Failure Mechanisms in Unidirectional Composites, J. Compos. Mater. 26 (1992) 2706–2726. [https://doi.org/10.1177/002199839202601804. https://doi.org/10.1177/002199839202601804.]		[1] P.M. Jelf, N.A. Fleck, Compression Failure Mechanisms in Unidirectional Composites, J. Compos. Mater. 26 (1992) 2706–2726. [https://doi.org/10.1177/002199839202601804. https://doi.org/10.1177/002199839202601804.]

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 ==4. Conclusions==
-An experimental investigation of unidirectional carbon fibre reinforced thermoplastic composites AS4/PEEK under off-axis compression was conducted using DIC technique. Conclusions can be drawn as the following.
+An experimental investigation of unidirectional carbon fibre reinforced thermoplastic composites AS4/PEEK under off-axis compression was conducted using DIC technique. Conclusions can be drawn as the following:
 (1) With a new designed off-axis compression test fixture, fibre splitting and end collapsing can be avoided during the off-axis compression tests;
@@ Line 645: / Line 645: @@
 (4) The compression failure envelope for different shear-compression combinations predicted based on Hashin criterion is too conservative compared to experimental results, while the LaRC05 criterion made excellent predictions when the off-axis angle is larger than 15°.
-'''Author Contributions:''' Conceptualization, Y.M., Y.L. and L.L.; methodology, Y.M.; software, Y.M.; validation, Y.L.; formal analysis, L.L.; investigation, Y.M., L.L.; resources, Y.L.; data curation, Y.M.; writing—original draft preparation, Y.M.; writing—review and editing, Y.L.; visualization, L.L.; supervision, Y.L.; project administration, Y.L.. All authors have read and agreed to the published version of the manuscript.
+'''Author contributions''': Conceptualization: Y. Ma, Y. Li and L.Liu; methodology: Y. Ma; software: Y. Ma; validation: Y. Li; formal analysis: L. Liu; investigation: Y. Ma, L. Liu; resources: Y. Li; data curation: Y. Ma; writing—original draft preparation: Y. Ma; writing—review and editing: Y. Li; visualization: L. Liu; supervision: Y. Li; project administration: Y. Li. All authors have read and agreed to the published version of the manuscript.
-−
-<span id='_Hlk89945590'></span><span id='_Hlk60054323'></span><span style="text-align: center; font-size: 75%;">'''Institutional Review Board Statement: '''Not applicable.</span>
-−
-'''Informed Consent Statement: '''Not applicable.
-−
-'''Data Availability Statement: '''Data available in a publicly accessible repository.
-−
-'''Conflicts of Interest:''' The authors declare no conflict of interest.
 ==References==