Keywords
semi-monocoque structure
composite materials
numerical calculations
How to Cite
Abstract
During aircraft service, the skin is the component that first comes into contact with factors that can cause mechanical damage - that is why it is most often damaged during use. Semi-monocoque aircraft structures are made of a skin (usually aluminum alloy) and a frame. The skin is an element that significantly affects the safety of the structure, since it transfers loads between the elements of the frame. For this reason, the skin is subject to special supervision during technical maintenance, and any damage detected must be repaired. The research was carried out on specimens made of AW 2024-T3 plate sheet with a thickness of 1 mm. In the study, a comparative analysis of damaged, undamaged and repaired specimens loaded in tension and compression was performed. Different patches were used in repaired specimens, made of metallic as well as composite materials, connected to the structure with rivets or using adhesive materials. The study showed that the use of riveted as well as adhesively bonded overlays does not allow the original strength of the tensile-loaded skin to be restored, but does allow the strength of the compression-loaded skin to be restored (loss of stability). In addition, numerical simulations were performed to define the stress field occurring in the adhesive joint for different geometric dimensions of the plate (thickness, width). The results of the numerical analysis showed that the geometry of the plate model influences the values of reduced stresses in the adhesive weld and the patch. Regardless of the analyzed changes in the geometry of the plate model, the maximum values of reduced stresses are similar to each other. The smallest values of reduced stresses in the adhesive joint and composite patch were obtained for the case of a plate with a thickness of 1 mm and a width of 160 mm.
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