Abstract
The schemes for joining of Glass Laminate Aluminium Reinforced Epoxy by the splicing method and the choice of the optimal scheme for the manufacture of large-sized panels are considered. The structure, mechanical and fatigue characteristics of a large-sized panel manufactured according to the optimal scheme are studied. The use of the splicing method makes it possible to reduce the weight of the structure by 10¸15 % as a result of reducing rivet joints and eliminating stress concentrators (holes), as well as increasing the reliability and damage tolerance of the aircraft. Keywords: Glass Laminate Aluminium Reinforced Epoxy, joint, splicing method, large panel, fuselage skin, fuselage, metalpolymer composite materials. org80@viam.ru, nefedovajuls@inbox.ru
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