Version 1
: Received: 20 September 2023 / Approved: 21 September 2023 / Online: 22 September 2023 (09:07:46 CEST)
How to cite:
Torres Arellano, M.; Burgos Vergara, A.; Piedra-Gonzalez, S.; Herrera, E.; Franco-Urquiza, E.A. Optimal Design of Laminates Orientation in a Composite Material by Genetics Algorithm and Simulated Annealing. Preprints2023, 2023091515. https://doi.org/10.20944/preprints202309.1515.v1
Torres Arellano, M.; Burgos Vergara, A.; Piedra-Gonzalez, S.; Herrera, E.; Franco-Urquiza, E.A. Optimal Design of Laminates Orientation in a Composite Material by Genetics Algorithm and Simulated Annealing. Preprints 2023, 2023091515. https://doi.org/10.20944/preprints202309.1515.v1
Torres Arellano, M.; Burgos Vergara, A.; Piedra-Gonzalez, S.; Herrera, E.; Franco-Urquiza, E.A. Optimal Design of Laminates Orientation in a Composite Material by Genetics Algorithm and Simulated Annealing. Preprints2023, 2023091515. https://doi.org/10.20944/preprints202309.1515.v1
APA Style
Torres Arellano, M., Burgos Vergara, A., Piedra-Gonzalez, S., Herrera, E., & Franco-Urquiza, E.A. (2023). Optimal Design of Laminates Orientation in a Composite Material by Genetics Algorithm and Simulated Annealing. Preprints. https://doi.org/10.20944/preprints202309.1515.v1
Chicago/Turabian Style
Torres Arellano, M., Erik Herrera and Edgar Adrian Franco-Urquiza. 2023 "Optimal Design of Laminates Orientation in a Composite Material by Genetics Algorithm and Simulated Annealing" Preprints. https://doi.org/10.20944/preprints202309.1515.v1
Abstract
The present work sets out the evaluation of composite laminates through optimization objective functions. Genetic Algorithms (GA), as well as Simulated Annealing (SA), were performed in order to determine the optimal ply orientations of a fiber-reinforced polymer laminate for three given load cases: 1) in-plane loads, 2) combined moments, and 3) in-plane loads and combined moments. It searches the optimal orientation layup, which fulfills at the same time both the maximum strain criterion and the Tsai-Wu failure criterion. Construction of an objective function based on the strains and the stresses involves a minimization process to deformations and a maximization of the safety factor. For the first load case, the initial solution is [±45/0/90/±45]s, and the best solution is [(45/135)2/452]s. For the second load case, [-45/45/45/-45/0/90]s is the initial layup sequence, then the best solution obtained is [(45/-45)2/452]s, where plies at 0° and 90º are not necessary even when axial loads are applied. For the third study case, the original layup sequence is [0/45/-45/45/0/90]s; meanwhile, the best solution calculated is [21/24/145/140/45/49]s. An interesting observation is that each pair of layers has a 5º gap. The simulations show that the qualitative results from the GA are better than the SA, but with a significantly higher computational cost. These kinds of computational tools are expected to be used as a reference guide for an optimal fiber configuration with respect to the common orientations used when composite laminates are designed for a structural application.
Copyright:
This is an open access article distributed under the Creative Commons Attribution License which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited.
