Kubit Andrzej, Trzepieciński Tomasz, Krasowski Bogdan, Slota Ján, Spišák Emil
Department of Manufacturing and Production Engineering, Rzeszow University of Technology, al. Powst. Warszawy 8, 35-959 Rzeszów, Poland.
Department of Materials Forming and Processing, Rzeszow University of Technology, al. Powst. Warszawy 8, 35-959 Rzeszów, Poland.
Materials (Basel). 2020 Jun 30;13(13):2929. doi: 10.3390/ma13132929.
This paper presents a new product, a glass laminate aluminium-reinforced epoxy (GLARE)-based thin-walled structure with a stiffener in the form of a longitudinal rib. The stiffening rib in an outer metallic layer of a GLARE-based panel was fabricated by the incremental sheet forming technique and Alclad 2024-T3 aluminium alloy sheets were used as adherends. The strength properties of the adhesive joint between the layers of the fibre metal laminates (FMLs) were determined in a uniaxial tensile test, peel drum test, tensile/shear test and short-beam three-point-bending test. Two variants of FMLs were considered, with an adhesive film and without an adhesive film between the adherends and the epoxy/glass prepreg. The FMLs were tested at three different temperatures that corresponded to those found under real aircraft operating conditions, i.e. -60 °C, room temperature and +80 °C. It was found that the temperatures do not affect the tensile strength and shear strength of the FMLs tested. However, there was a noticeable increase in the stiffness of samples stretched at reduced temperature. An additional adhesive film layer between the adherends and the glass/epoxy prepreg significantly improves the static peeling strength of the joint both at reduced and at elevated temperatures. A clear increase in the critical force at which buckling occurs has been clearly demonstrated in the uniaxial compression test of GLARE-based rib-stiffened panels. In the case of GLARE-based rib-stiffened panels, the critical force averaged 15,370 N, while for the non-embossed variant, it was 11,430 N, which translates into a 34.5% increase in critical force.
本文介绍了一种新产品，即一种基于玻璃层压铝增强环氧树脂（GLARE）的薄壁结构，其带有纵向肋形式的加强筋。基于GLARE的面板外层金属层中的加强肋采用渐进式板材成型技术制造，并使用包铝2024 - T3铝合金板材作为被粘物。在单轴拉伸试验、剥离鼓试验、拉伸/剪切试验和短梁三点弯曲试验中测定了纤维金属层压板（FML）各层之间粘接接头的强度性能。考虑了两种FML变体，即在被粘物与环氧/玻璃预浸料之间有粘结膜和没有粘结膜的情况。在与实际飞机运行条件下对应的三种不同温度下对FML进行了测试，即 - 60°C、室温及 + 80°C。结果发现，温度不会影响所测试FML的拉伸强度和剪切强度。然而，在低温下拉伸的样品刚度有明显增加。在被粘物与玻璃/环氧预浸料之间增加一层粘结膜层，在低温和高温下均能显著提高接头的静态剥离强度。在基于GLARE的肋加强面板的单轴压缩试验中，已清楚地证明了发生屈曲时的临界力有明显增加。对于基于GLARE的肋加强面板，临界力平均为15370 N，而对于非压花变体，临界力为11430 N，这意味着临界力增加了34.5%。
