Materiales.Compuestos at 14:25, 11 December 2022

2022-12-11T14:25:13Z

Materiales.Compuestos at 14:24, 11 December 2022

2022-12-11T14:24:30Z

Scipediacontent at 17:01, 7 May 2022

2022-05-07T17:01:08Z

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Scipediacontent: Scipediacontent moved page Draft Content 940347436 to Sasikumar et al 2021b

2022-03-31T19:34:16Z

Scipediacontent moved page Draft Content 940347436 to Sasikumar et al 2021b

Scipediacontent: Created page with "== Abstract == With thin structures used in the aircrafts, aeronautical manufacturers are worried about the response of these thin laminates towards impact and post impact lo..."

2022-03-31T19:34:13Z

Created page with "== Abstract == With thin structures used in the aircrafts, aeronautical manufacturers are worried about the response of these thin laminates towards impact and post impact lo..."

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== Abstract ==

With thin structures used in the aircrafts, aeronautical manufacturers are worried about the response of these thin laminates towards impact and post impact loads. Thin laminates studied to show reduced compression after impact strengths with thin plies and hence continues to be a primary concern to the aeronautical industries. In this work, we aim to use ply grade hybridization (mixing different ply grades) and unsymmetrical laminate designs as an effort to improve the low velocity impact response and compression after impact strength of thin laminates. Using different materials, uni-directional and non-crimp fabrics, through experimental, numerical and optimization methods, we demonstrate that hybridization along with unsymmetrical designs can improve the CAI strength by upto 40% over the thin ply baseline laminates.

== Full document ==
<pdf>Media:Draft_Content_940347436native-articles-512.pdf</pdf>

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 In this study, we used two different material systems: uni-directional prepreg tapes and non-crimp fabric (NCF), both of the same T700/M21 carbon-epoxy. We used three ply grades of the UD plies namely thick (268 gsm), intermediate (134 gsm) and thin plies (75 gsm). NCF come in bi-axial blankets of [0/45] and [0/-45]. Similarly, for the NCF: intermediate (134 gsm) and thin plies (67 gsm).
-<span id='_Ref84259127'></span><span style="text-align: center; font-size: 75%;">'''Table 1.''' Different laminates studied</span>
+<div class="center" style="width: auto; margin-left: auto; margin-right: auto;">
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 ==1 Introduction==
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 Laminate L1, L8 and L9 were selected through optimization followed by virtual testing through finite element simulations. We used Abaqus/Explicit conventional shell elements (S4R) to model the plies, and zero thickness cohesive elements (COH3D8) to model the interface between the plies. Progressive intraply damage was accounted using continuum damage model proposed by Maimi et al.[7]. The cohesive constitute model for the interface was proposed by Gonzalez et al. [8] and both these models are implemented in a VUMAT user-written subroutine.
+[[File:Sasikumar_et_al_2021b-image5.jpeg|centre|600x600px]]
-[[Image:Sasikumar_et_al_2021b-image5.jpeg|600px]]
 <div class="center" style="width: auto; margin-left: auto; margin-right: auto;">
-<span style="text-align: center; font-size: 75%;">'''Figure 1.'''  Virtual impact setup with the modelling strategy followed [4]</span></div>
+<span style="text-align: center; font-size: 75%;">'''Figure 1.'''  Virtual impact setup with the modelling strategy followed [4].</span></div>
 The CAI simulation was performed using a RESTART option in Abaqus/Explicit, where apart from the standard, a non-standard anti-buckling fixture was accounted in the model. Reader is referred to [4] for more details on the numerical model.
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 <span id='cite-_Ref84276076'></span>[[#_Ref84276076|Figure 2]] presents the impact curves of the baseline laminate H-134 from both experimental and numerical results of 8.9 and 10.5 J. The force-deflection and energy curves show that the numerical model I in very good agreement with the experimental curves. The load drops seen in the force-deflection curves are attributed to the fibre damage at the non-impacted side of the laminate.
+[[File:Sasikumar_et_al_2021b-image6.jpeg|centre|600x600px]]
-[[Image:Sasikumar_et_al_2021b-image6.jpeg|600px]]
 <div id="_Ref84276076" class="center" style="width: auto; margin-left: auto; margin-right: auto;">
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 <span id='cite-_Ref84318142'></span>[[#_Ref84318142|<span style="text-align: center; font-size: 75%;">Figure 4</span>]] compares the baseline laminates and the proposed hybrid laminates with UD plies (a) and NCF(b). Both the proposed hybrid laminates (H-75-H2 and NCF-UHB) mitigated the fiber failure compared to the thin ply counterparts as seen in the curves. Addition of thicker plies to thin plies helped to dissipate energy through matrix cracks and delaminations and thereby reducing the fiber damage.
+[[File:Sasikumar_et_al_2021b-image9.png|centre|600x600px]]
-[[Image:Sasikumar_et_al_2021b-image9.png|600px]]
 <div id="_Ref84318142" class="center" style="width: auto; margin-left: auto; margin-right: auto;">
-<span style="text-align: center; font-size: 75%;">'''Figure 4.''' Comparing force-deflection impact curves of hybrid laminates with their thin ply counterpart laminates</span></div>
+<span style="text-align: center; font-size: 75%;">'''Figure 4.''' Comparing force-deflection impact curves of hybrid laminates with their thin ply counterpart laminates.</span></div>
 <span id='cite-_Ref84319435'></span>[[#_Ref84319435|Figure 5]] presents the different impact damage resistance parameters and the CAI strength from the 10.5 J impact. Thin ply laminates exhibit low resistance to impact and a low CAI strength when compared to the proposed hybrid laminates.
+[[File:Sasikumar_et_al_2021b-image10.png|centre|600x600px]]
-[[Image:Sasikumar_et_al_2021b-image10.png|600px]]
 <div id="_Ref84319435" class="center" style="width: auto; margin-left: auto; margin-right: auto;">
-<span style="text-align: center; font-size: 75%;">'''Figure 5.''' Comparison of impact damage resistance parameters and CAI strength of proposed hybrid laminates and their corresponding thin-ply counterparts</span></div>
+<span style="text-align: center; font-size: 75%;">'''Figure 5.''' Comparison of impact damage resistance parameters and CAI strength of proposed hybrid laminates and their corresponding thin-ply counterparts.</span></div>
 Compared to the UD hybrid laminates, the NCF proposed hybrid laminates possessed better CAI strength.

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Sasikumar et al 2021b - Revision history

Materiales.Compuestos at 14:25, 11 December 2022

Materiales.Compuestos at 14:24, 11 December 2022

Scipediacontent at 17:01, 7 May 2022

Scipediacontent: Scipediacontent moved page Draft Content 940347436 to Sasikumar et al 2021b

Scipediacontent: Created page with "== Abstract == With thin structures used in the aircrafts, aeronautical manufacturers are worried about the response of these thin laminates towards impact and post impact lo..."