CONNECTION ANALYSIS AND LIGHTWEIGHT DESIGN OF THE LIGHT AIRCRAFT COMPOSITE FUSELAGE PANEL

Abstract

Abstract: The structural damage analysis was carried out on three types of composite fuselage panels (single rivet, multi-rivets and adhesive connection). Based on Hashin criterion, the initial damage of matrix and fiber was determined, and the failure mode under longitudinal tensile load was analyzed. Optistruct was used to conduct structural optimization analysis on the lightweight of fuselage panel. In order to meet the requirements of mechanical properties and technological manufacturing, the number, thickness and sequence of composite layers were optimized. The number of layings was determined by free dimensional optimization, the thickness of layings was determined by dimensional optimization, and the layering sequence was optimized to obtain the optimal material properties to achieve the goal of reducing the structural weight. The results show that the weight of the fuselage structure is greatly reduced while meeting the requirements of strength, stiffness and manufacturing process.

Key words: composite material, fuselage panel, connection damage, layer optimization

CLC Number:

TB332

SHAO Jia-ru, ZHANG Yue-yue, ZENG Xian-jun, LIU Niu. CONNECTION ANALYSIS AND LIGHTWEIGHT DESIGN OF THE LIGHT AIRCRAFT COMPOSITE FUSELAGE PANEL[J]. COMPOSITES SCIENCE AND ENGINEERING, 2021, 0(1): 28-34.

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