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为减轻重量的飞机托盘底板纤维增强塑料复合夹层结构的优化设计

Optimal Design of a Fiber-Reinforced Plastic Composite Sandwich Structure for the Base Plate of Aircraft Pallets In Order to Reduce Weight.

作者信息

Al-Fatlawi Alaa, Jármai Károly, Kovács György

机构信息

Faculty of Mechanical Engineering and Informatics, University of Miskolc, Egyetemváros, H-3515 Miskolc, Hungary.

Faculty of Mechanical Engineering, University of Kufa, Al-Najaf 54001, Iraq.

出版信息

Polymers (Basel). 2021 Mar 9;13(5):834. doi: 10.3390/polym13050834.

DOI:10.3390/polym13050834
PMID:33803260
原文链接:https://pmc.ncbi.nlm.nih.gov/articles/PMC7967186/
Abstract

The application of fiber-reinforced plastic (FRP) composite materials instead of metals, due to the low density of FRP materials, results in weight savings in the base plates of aircraft pallets. Lower weight leads to lower fuel consumption of the aircraft and thereby less environmental damage. The study aimed to investigate replacing the currently used aluminum base plates of aircraft pallets with composite sandwich plates to reduce the weight of the pallets, thereby the weight of the unit loads transported by aircraft. The newly constructed sandwich base plate consists of an aluminum honeycomb core and FRP composite face-sheets. First, we made experimental tests and numerical calculations for the investigated FRP sandwich panel to validate the applicability of the calculation method. Next, the mechanical properties of 40 different layer-combinations of 4 different FRP face-sheet materials (phenolic woven glass fiber; epoxy woven glass fiber; epoxy woven carbon fiber; and hybrid layers) were investigated using the Digimat-HC modeling program in order to find the appropriate face-sheet construction. Face-sheets were built up in 1, 2, 4, 6 or 8 layers with sets of fiber orientations including cross-ply (0°, 90°) and/or angle-ply (±45°). The weight optimization method was elaborated considering 9 design constraints: stiffness, deflection, skin stress, core shear stress, facing stress, overall buckling, shear crimping, skin wrinkling, and intracell buckling. A case study for the base plate of an aircraft pallet was introduced to validate the optimization procedure carried out using the Matlab (Interior Point Algorithm) and Excel Solver (Generalized Reduced Gradient Nonlinear Algorithm) programs. In the case study, the weight of the optimal structure (epoxy woven carbon fiber face-sheets) was 27 kg, which provides weight savings of 66% compared to the standard aluminum pallet. The article's main added value is the elaboration and implementation of an optimization method that results in significant weight savings and thus lower fuel consumption of aircraft.

摘要

由于纤维增强塑料（FRP）材料密度低，用其复合材料代替金属可减轻飞机货盘底板的重量。重量减轻会降低飞机的燃油消耗，从而减少对环境的破坏。该研究旨在探讨用复合夹芯板取代飞机货盘目前使用的铝制底板，以减轻货盘重量，进而减轻飞机运输的单位货物重量。新构建的夹芯底板由铝蜂窝芯和FRP复合面板组成。首先，我们对所研究的FRP夹芯板进行了实验测试和数值计算，以验证计算方法的适用性。接下来，使用Digimat-HC建模程序研究了4种不同FRP面板材料（酚醛玻璃纤维织物；环氧玻璃纤维织物；环氧碳纤维织物；以及混合层）的40种不同层组合的力学性能，以找到合适的面板结构。面板由1、2、4、6或8层组成，纤维取向包括正交铺层（0°，90°）和/或斜交铺层（±45°）。考虑9个设计约束条件详细阐述了重量优化方法：刚度、挠度、蒙皮应力、芯材剪应力、面板应力、整体屈曲、剪切卷曲、蒙皮起皱和胞内屈曲。引入了一个飞机货盘底板的案例研究，以验证使用Matlab（内点算法）和Excel Solver（广义简约梯度非线性算法）程序进行的优化过程。在案例研究中，最优结构（环氧碳纤维织物面板）的重量为27千克，与标准铝制货盘相比，重量减轻了66%。本文的主要附加值在于详细阐述并实施了一种优化方法，该方法可显著减轻重量，从而降低飞机的燃油消耗。

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