Design and verification of composite wing based on composite beam structure

doi:10.19936/j.cnki.2096-8000.20230728.007

Abstract

Abstract: Taking the composite wing with a given shape and size as the research object, the structure design of the wing and the overall forming scheme are studied. The 3D model of the wing is established by CATIA , and the model is set as an isotropic material, and the finite element analysis is carried out with the loading method of three-point bending. Based on the finite element results of COMSOL, the main stress areas of the wing are individually designed. Combining the beam structure buckling and stiffness efficiency criteria, a skeleton scheme of “double C+I-shaped composite beam” is proposed. Then through the displacement response analysis of the central wing box with equal thickness ply, the design scheme of the central wing box ladder ply is proposed. The finite element analysis of the laminated central wing box was carried out by ABAQUS, and the central wing box was further designed by comparing the test results to improve the stiffness of the central wing box. The distribution curing+co-bonding molding process is adopted to avoid filling foam processing and improve the overall load-ratio of the wing. Finally, a composite wing design scheme with high buckling and stiffness efficiency is proposed, in which the total weight of the wing is 316.18 g and the load/weight ratio is 34.85 N/g, which proves the rationality and effectiveness of the design scheme.

Key words: composite material wing, central wing box, ply design, composite beam, step curing

CLC Number:

TB332

WANG Jing, LU Chang, WU Panpan, LI Chuang. Design and verification of composite wing based on composite beam structure[J]. COMPOSITES SCIENCE AND ENGINEERING, 2023, 0(7): 50-56.

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