Lamination design and performance analysis of composite aircraft auxiliary fuel tank structure

doi:10.19936/j.cnki.2096-8000.20250228.010

Abstract

Abstract: In order to reduce the weight of the aircraft and improve its maneuverability, it is crucial to apply composite materials to the lightweight design of the aircraft drop tank structure. The longitudinal tensile test results verified the accuracy of the simulation model for predicting the mechanical properties of the specimen with lightning protection function, and established a finite element model of the auxiliary fuel tank by analogy. For composite skin reinforced structures, a layup sequence optimization method is proposed. Based on the mechanical response of the skin in different layup plans of the auxiliary fuel tank under static load and impact conditions, the best layup plan is determined. The basic cycle unit of the ply angle combines each ply angle to optimize the ply sequence of the skin and complete the strength check. The results show that the maximum strain of the auxiliary fuel tank skin under static load conditions is reduced by 4.95% after optimization, and it is reduced by 12.6% under impact conditions. At the same time, the strength and stiffness of the skin are also improved, which verifies the effectiveness of this optimization method. The results of this research can provide guidance for the design and manufacture of composite shell reinforcement structures such as aircraft auxiliary fuel tanks.

Key words: aircraft auxiliary fuel tank, layer design, composites, static analysis, impact analysis

CLC Number:

TB332

GAO Wenming, LIU Chen, NIE Haiping, YANG Mingguang, WANG Xianfeng. Lamination design and performance analysis of composite aircraft auxiliary fuel tank structure[J]. COMPOSITES SCIENCE AND ENGINEERING, 2025, 0(2): 70-81.

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