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This paper presented research regarding the design and manufacturing of a small sized UAV wing. An Unmanned Aerial Vehicle (U A V) is an aircraft without human operators onboard. The flight of such an aircraft can be operated with several degrees of automation. Such an aircraft has a wide range of applications: surveillance, research and development, logistics, civil-commercial and military applications. In this study are presented research related to designing, numerical analyzing and manufacturing of the wing, made with Glass Fiber Reinforced Polymer (GFRP), using Sandwich architecture. The wing is designed for a U A V with an electric powerplant. The paper includes studies regarding the choice for the airfoil, the wing shape and a structural static study using Finite Element Analysis (FEA). The two structure solutions (single composite shell and composite Sandwich) are analyzed using FEA methods. The wing is subjected to 5 g. The tip displacement (according to FEA) is 64,86 mm for the single shell structure. In the case of the Sandwich structure, the tip displacement is 0,3279 mm.
