Evaluation of Laminated Composite Beam Theory Accuracy
Carbon fiber-reinforced polymer (CFRP) has been widely implemented in electric vehicle bodies and aircraft fuselage structures. The purpose of CFRP is to reduce the weight and impart rigidity in the final product. A beam structure is typically used to bear the structural load, and the rigidity of th...
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MDPI AG
2022-10-01
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| Series: | Materials |
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| Online Access: | https://www.mdpi.com/1996-1944/15/19/6941 |
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| author | Yu-Ting Lyu Tsung-Pin Hung Her-Chang Ay Hsiu-An Tsai Yih-Cherng Chiang |
| author_facet | Yu-Ting Lyu Tsung-Pin Hung Her-Chang Ay Hsiu-An Tsai Yih-Cherng Chiang |
| author_sort | Yu-Ting Lyu |
| collection | DOAJ |
| description | Carbon fiber-reinforced polymer (CFRP) has been widely implemented in electric vehicle bodies and aircraft fuselage structures. The purpose of CFRP is to reduce the weight and impart rigidity in the final product. A beam structure is typically used to bear the structural load, and the rigidity of the beam can be changed by arranging the laminated fibers at different angles. In this study, a composite I-beam is used as an example in engineering components. Because the theoretical model of the superimposed composite I-beam is established, the theoretical formula is based on the theoretical assumptions of the two-dimensional composite beam, and is combined with the traditional composite plate theory to analyze the maximum bending stress, strain, and deflection. During the theoretical derivation, it is assumed that the flanges of the I-beams are divided into narrow and wide flanges. The beams are considered as structures of beams and flatbeds. When a narrow flange is loaded in the side, the wide flange has no lateral deformation, and the lateral moments are neglected. Therefore, the accuracy of this formula needs to be verified. The purpose of this study is to verify the accuracy of theoretical solutions for the deflection and stress analysis of composite beams. A finite element analysis model is used as the basis for comparing the theoretical solutions. The results indicate that when the aspect ratio of the beam is >15, the theoretical solution will have better accuracy. Without the addition of the material, when 0° ply is placed on the outermost layer of the flange of the nonsymmetric beam, the effective rigidity of the beam is increased by 4–5% compared with the symmetrical beam. The accuracy range of the theoretical solution for the composite beams can be accurately defined based on the results of this study. |
| first_indexed | 2024-03-09T21:29:33Z |
| format | Article |
| id | doaj.art-6f5820649f654c10a3eb86f4cc657eab |
| institution | Directory Open Access Journal |
| issn | 1996-1944 |
| language | English |
| last_indexed | 2024-03-09T21:29:33Z |
| publishDate | 2022-10-01 |
| publisher | MDPI AG |
| record_format | Article |
| series | Materials |
| spelling | doaj.art-6f5820649f654c10a3eb86f4cc657eab2023-11-23T20:59:21ZengMDPI AGMaterials1996-19442022-10-011519694110.3390/ma15196941Evaluation of Laminated Composite Beam Theory AccuracyYu-Ting Lyu0Tsung-Pin Hung1Her-Chang Ay2Hsiu-An Tsai3Yih-Cherng Chiang4Department of Mold and Die Engineering, National Kaohsiung University of Science and Technology, Kaohsiung 807618, TaiwanDepartment of Mechanical Engineering, Cheng Shiu University, Kaohsiung 833301, TaiwanDepartment of Mold and Die Engineering, National Kaohsiung University of Science and Technology, Kaohsiung 807618, TaiwanMetal Industries Research and Development Centre (MIRDC), Kaohsiung 811020, TaiwanDepartment of Mechanical Engineering, Chinese Culture University, Taipei 11114, TaiwanCarbon fiber-reinforced polymer (CFRP) has been widely implemented in electric vehicle bodies and aircraft fuselage structures. The purpose of CFRP is to reduce the weight and impart rigidity in the final product. A beam structure is typically used to bear the structural load, and the rigidity of the beam can be changed by arranging the laminated fibers at different angles. In this study, a composite I-beam is used as an example in engineering components. Because the theoretical model of the superimposed composite I-beam is established, the theoretical formula is based on the theoretical assumptions of the two-dimensional composite beam, and is combined with the traditional composite plate theory to analyze the maximum bending stress, strain, and deflection. During the theoretical derivation, it is assumed that the flanges of the I-beams are divided into narrow and wide flanges. The beams are considered as structures of beams and flatbeds. When a narrow flange is loaded in the side, the wide flange has no lateral deformation, and the lateral moments are neglected. Therefore, the accuracy of this formula needs to be verified. The purpose of this study is to verify the accuracy of theoretical solutions for the deflection and stress analysis of composite beams. A finite element analysis model is used as the basis for comparing the theoretical solutions. The results indicate that when the aspect ratio of the beam is >15, the theoretical solution will have better accuracy. Without the addition of the material, when 0° ply is placed on the outermost layer of the flange of the nonsymmetric beam, the effective rigidity of the beam is increased by 4–5% compared with the symmetrical beam. The accuracy range of the theoretical solution for the composite beams can be accurately defined based on the results of this study.https://www.mdpi.com/1996-1944/15/19/6941CFRPUAVlaminated composite beamfinite element analysiseffective stiffness |
| spellingShingle | Yu-Ting Lyu Tsung-Pin Hung Her-Chang Ay Hsiu-An Tsai Yih-Cherng Chiang Evaluation of Laminated Composite Beam Theory Accuracy Materials CFRP UAV laminated composite beam finite element analysis effective stiffness |
| title | Evaluation of Laminated Composite Beam Theory Accuracy |
| title_full | Evaluation of Laminated Composite Beam Theory Accuracy |
| title_fullStr | Evaluation of Laminated Composite Beam Theory Accuracy |
| title_full_unstemmed | Evaluation of Laminated Composite Beam Theory Accuracy |
| title_short | Evaluation of Laminated Composite Beam Theory Accuracy |
| title_sort | evaluation of laminated composite beam theory accuracy |
| topic | CFRP UAV laminated composite beam finite element analysis effective stiffness |
| url | https://www.mdpi.com/1996-1944/15/19/6941 |
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