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...

Celý popis

Uloženo v:
Podrobná bibliografie
Vydáno v:2022 4th International Conference on Artificial Intelligence and Advanced Manufacturing (AIAM) s. 857 - 864
Hlavní autor: Chen, Bowei
Médium: Konferenční příspěvek
Jazyk:angličtina
Vydáno: IEEE 01.10.2022
Témata:
Aerofoil
Atmospheric modeling
Finite element analysis
Force
Geometry
Linear programming
Loading
Non-linear programming method
Programming
Software
Truss structure
On-line přístup:Získat plný text
Tagy: Přidat tag
Žádné tagy, Buďte první, kdo vytvoří štítek k tomuto záznamu!
Popis
Shrnutí: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.
DOI:10.1109/AIAM57466.2022.00174