TY - GEN
T1 - MODAL ANALYSIS OF MULTI-CELL COMPOSITE WING STRUCTURES USING VARIABLE THICKNESS SANDWICH PLATE MODELS
AU - Hsieh, Meng Ling
AU - Hwu, Chyanbin
N1 - Funding Information:
The authors would like to thank the Ministry of Science and Technology, TAIWAN, R.O.C, for support through Grants MOST 110-2221-E-006-090-MY3.
Publisher Copyright:
© 2023 Proceedings of the International Congress on Sound and Vibration. All rights reserved.
PY - 2023
Y1 - 2023
N2 - The main goal of this paper is to develop a simple and accurate method to find the natural frequencies and vibration modes of a multi-cell composite wing structure. A typical wing structure, which consists of skins, stringers, spars, and ribs, is usually too complicated to be analyzed analytically, and preparing a detailed finite element model is also a tedious and time-consuming task. To simplify the analysis in early airplane design stages, a finite element method is developed for multi-cell composite wing structures. The wing is modelled as a moderately thick sand-wich plate of variable core thickness using the first order shear deformation theory. By introducing a pseudolamina, the stringers are integrated into the laminated skins, and the compound of stringers and skins comprise facesheets, which bear the in-plane loading, of the sandwich plate model. The ribs and spar webs are designed to bear the transverse shear loadings and maintain the shape of an airfoil. Therefore, they are represented by an equivalent anti-plane core, whose thickness varies according to the airfoil. After setting up a sandwich plate model for the wing structure, we derive the finite element formulation for a sandwich plate of variable thickness with Hamilton's principle. Using this formulation, we perform modal analysis on the equivalent sandwich plate of the wing structure. A numerical example is presented to demonstrate the method developed in this paper.
AB - The main goal of this paper is to develop a simple and accurate method to find the natural frequencies and vibration modes of a multi-cell composite wing structure. A typical wing structure, which consists of skins, stringers, spars, and ribs, is usually too complicated to be analyzed analytically, and preparing a detailed finite element model is also a tedious and time-consuming task. To simplify the analysis in early airplane design stages, a finite element method is developed for multi-cell composite wing structures. The wing is modelled as a moderately thick sand-wich plate of variable core thickness using the first order shear deformation theory. By introducing a pseudolamina, the stringers are integrated into the laminated skins, and the compound of stringers and skins comprise facesheets, which bear the in-plane loading, of the sandwich plate model. The ribs and spar webs are designed to bear the transverse shear loadings and maintain the shape of an airfoil. Therefore, they are represented by an equivalent anti-plane core, whose thickness varies according to the airfoil. After setting up a sandwich plate model for the wing structure, we derive the finite element formulation for a sandwich plate of variable thickness with Hamilton's principle. Using this formulation, we perform modal analysis on the equivalent sandwich plate of the wing structure. A numerical example is presented to demonstrate the method developed in this paper.
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M3 - Conference contribution
AN - SCOPUS:85170647176
T3 - Proceedings of the International Congress on Sound and Vibration
BT - Proceedings of the 29th International Congress on Sound and Vibration, ICSV 2023
A2 - Carletti, Eleonora
PB - Society of Acoustics
T2 - 29th International Congress on Sound and Vibration, ICSV 2023
Y2 - 9 July 2023 through 13 July 2023
ER -