Abstract
The damaged laminated composite structural strength and repair action due to functional material reinforcement is investigated mathematically in this research using a higher-order displacement field model. The effect of a crack on the frequency responses is predicted numerically using the finite element (FE) approach. The reduction in total structural strength due to the crack and elevated temperatures are computed using the proposed model. Further, the enhancement of parent structural strength/stiffness is achieved by reinforcing the shape memory alloy (SMA). Moreover, the damage repair and improved frequency are achieved through activated SMA under a temperature range. The numerical model efficacy is established by conducting the convergence and adequate comparison studies. The study of the cracked laminate is verified for different temperature ranges, with and without SMA fiber. Additionally, a few experimental frequencies of intact and damaged composite panels have been carried out for comparison to gain confidence in the proposed model. Finally, several numerical examples are solved by varying the important structural input parameters (material and geometry) and their influences discussed in detail.
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SERB India supports this research work under Teachers Associateship for Research Excellence (TARE) scheme. The authors are thankful to TARE (SERB India) for their constant support. File no TAR/2020/000168 dated 19th Dec 2020.
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Appendix
Appendix
Individual terms of matrix [B]:
[B]1,1 = \(\partial /\partial x\), [B]1,3 = \(1/R_{x}\), [B]2,2 = \(\partial /\partial y\), [B]2,3 = \(1/R_{y}\), [B]3,1 = \(\partial /\partial y\), [B]3,2 = \(\partial /\partial x\), [B]3,3 = \(2/R_{xy}\), [B]4,1 = \(- 1/R_{x}\), [B]4,3 = \(\partial /\partial x\), [B]4,4 = 1, [B]5,2 = \(- 1/R_{y}\), [B]5,3 = \(\partial /\partial x\), [B]5,5 = 1, [B]6,4 = \(\partial /\partial x\), [B]7,5 = \(\partial /\partial y\), [B]8,4 = \(\partial /\partial y\), [B]8,5 = \(\partial /\partial x\), [B]9,4 = \(- 1/R_{x}\), [B]9,6 = 2, [B]10,5 = \(- 1/R_{y}\), [B]10,7 = 2, [B]11,6 = \(\partial /\partial x\), [B]12,7 = \(\partial /\partial y\), [B]13,6 = \(\partial /\partial y\), [B]13,7 = \(\partial /\partial x\), [B]14,6 = \(- 1/R_{x}\), [B]14,8 = 2, [B]15,7 = \(- 1/R_{y}\), [B]15,9 = 2, [B]16,8 = \(\partial /\partial x\), [B]17,9 = \(\partial /\partial y\), [B]18,8 = \(\partial /\partial y\), [B]18,9 = \(\partial /\partial x\),[B]19,8 = \(- 1/R_{x}\), [B]20,9 = \(- 1/R_{y}\).
Individual terms of matrix [BG]:
[BG]1,1 = \(\partial /\partial x\), [BG]1,3 = \(1/R_{x}\), [BG]2,1 = \(\partial /\partial y\), [BG]3,2 = \(\partial /\partial x\), [BG]4,2 = \(\partial /\partial y\), [BG]4,3 = \(1/R_{y}\), [BG]5,1 = \(- 1/R_{x}\), [BG]5,3 = \(\partial /\partial x\), [BG]6,2 = \(- 1/R_{y}\), [BG]6,3 = \(\partial /\partial y\), [BG]7,4 = \(\partial /\partial x\), [BG]8,4 = \(\partial /\partial y\), [BG]9,5 = \(\partial /\partial x\), [BG]10,5 = \(\partial /\partial y\), [BG]11,4 = \(- 1/R_{x}\), [BG]12,5 = \(- 1/R_{y}\), [BG]13,6 = \(\partial /\partial x\), [BG]14,6 = \(\partial /\partial y\), [BG]15,7 = \(\partial /\partial x\), [BG]16,7 = \(\partial /\partial y\), [BG]17,6 = \(- 1/R_{x}\), [BG]18,7 = \(- 1/R_{y}\), [BG]19,8 = \(\partial /\partial x\), [BG]20,8 = \(\partial /\partial y\), [BG]21,9 = \(\partial /\partial x\), [BG]22,9 = \(\partial /\partial y\), [BG]23,8 = \(- 1/R_{x}\), [BG]24,9 = \(- 1/R_{y}\).
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Erukala, K.K., Mishra, P.K., Dewangan, H.C. et al. Damaged composite structural strength enhancement under elevated thermal environment using shape memory alloy fiber. Acta Mech 233, 3133–3155 (2022). https://doi.org/10.1007/s00707-022-03272-w
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DOI: https://doi.org/10.1007/s00707-022-03272-w