Lightweight prepreg composite wing design and finite element analysis

doi:10.19936/j.cnki.2096-8000.20260928.014

Abstract

Abstract: As aerospace technology advances towardlightweight and low-cost solutions,the performancerequirements forcomposite materials have become increasingly demanding. In this paper, a certain type of low-speed fixed-wing UAV airfoil NACA2415 was selected as the research object, and three different forms of wings were designed, including pure carbon fiber material structure, PMI foam sandwich structure and lightweight prepreg sandwich structure, and then the static loading test was carried out, and the finite element analysis was used to check the wing, and the stress, deformation and Tsai-Wu index results of the wing were given, and the optimal composite structure design form was compared. Finally, the accuracy of the finite element analysis results is verified by a static test. The results show that the lightweight prepreg sandwich structure meets the mechanical bearing requirements of the wing, and reduces the overall weight of the wing by 36.9%, achieving the purpose of light weight and low cost.

Key words: composite, wing design, lightweight, finite element, static test

CLC Number:

TB332

TANG He, YU Qiyong, XU Junxiang, LI Mingming, LIU Guangya, LU Xiaobin, LIU Mengen. Lightweight prepreg composite wing design and finite element analysis[J]. COMPOSITES SCIENCE AND ENGINEERING, 2026, 0(9): 122-130.

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