Optimization Design and Finite Element Analysis of an Aerofoil's Dominant Truss Structure
In order to further optimize the dominant truss structure inside the aerofoil of a certain aircraft type, an optimization model for the structure is proposed. Firstly, a traditional optimization model is established based on the nonlinear programming method, which regards the deflection of the aerof...
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| Vydané v: | 2022 4th International Conference on Artificial Intelligence and Advanced Manufacturing (AIAM) s. 857 - 864 |
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01.10.2022
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| Abstract | In order to further optimize the dominant truss structure inside the aerofoil of a certain aircraft type, an optimization model for the structure is proposed. Firstly, a traditional optimization model is established based on the nonlinear programming method, which regards the deflection of the aerofoil's end nodes as the objective function, and the size of the components, the constraint reaction force of the hinge supports, and the stress of the components as the constraints. Secondly, taking the existence of the complex internal geometrical angles and a large quantity of oblique components into consideration, an improved optimization model whose constraint conditions contain the length of a specific oblique component is proposed, and the results are verified by the finite element analysis results of ABAQUS software. The results show that when the length of the dominant truss structure inside the aerofoil is 12m, the height is 3m, the length of a specific component inside the wing is 2.8m, and the cross-sectional area of the component is 11200mm 2 , the deflection of the aerofoil's end node is the lowest, and the safety of the aerofoil's design scheme satisfies the requirement. The establishment of this model has an important guiding significance for the optimal design of other aerofoil's dominant truss structures. |
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| AbstractList | In order to further optimize the dominant truss structure inside the aerofoil of a certain aircraft type, an optimization model for the structure is proposed. Firstly, a traditional optimization model is established based on the nonlinear programming method, which regards the deflection of the aerofoil's end nodes as the objective function, and the size of the components, the constraint reaction force of the hinge supports, and the stress of the components as the constraints. Secondly, taking the existence of the complex internal geometrical angles and a large quantity of oblique components into consideration, an improved optimization model whose constraint conditions contain the length of a specific oblique component is proposed, and the results are verified by the finite element analysis results of ABAQUS software. The results show that when the length of the dominant truss structure inside the aerofoil is 12m, the height is 3m, the length of a specific component inside the wing is 2.8m, and the cross-sectional area of the component is 11200mm 2 , the deflection of the aerofoil's end node is the lowest, and the safety of the aerofoil's design scheme satisfies the requirement. The establishment of this model has an important guiding significance for the optimal design of other aerofoil's dominant truss structures. |
| Author | Chen, Bowei |
| Author_xml | – sequence: 1 givenname: Bowei surname: Chen fullname: Chen, Bowei email: 2019011295@student.cup.edu.cn organization: China University of Petroleum (Beijing),College of Safety and Ocean Engineering,Beijing,China,102249 |
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| Snippet | In order to further optimize the dominant truss structure inside the aerofoil of a certain aircraft type, an optimization model for the structure is proposed.... |
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| SubjectTerms | Aerofoil Atmospheric modeling Finite element analysis Force Geometry Linear programming Loading Non-linear programming method Programming Software Truss structure |
| Title | Optimization Design and Finite Element Analysis of an Aerofoil's Dominant Truss Structure |
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