In this paper, the weight optimizing of an unmanned aerial vehicle wing spar was designed by using composite material. The optimization parameters were considered, respectively: the wing mass, the location of the spars and ribs, and the spars mass. Determined the selecting of wing spars locations for optimizing spars design based on the minimum weight of the wing. Layer optimizing was used to reduce the weight of composite wing spars. The thickness of front spar and rear spar element such as web and flange were optimized by criterion of allowable normal stress and deflection. The analysis of stress-strain state for all variants were carried out in the FEMAP software package. As the result of analysis, the total weights of composite wing spars reduced 18.17% than the original spars.

This paper presents the results of structural optimization of a two-spar composite wing for a light aircraft. Different lay-up structures of power components such as spars, ribs and skin panels was considered. The problem of optimization was solved using Pareto optimization method with two criteria: minimal wing weight and minimal wing deflection under aerodynamic load. The angle of ply orientation and power components thicknesses were considered as the optimization parameters. It was shown that the use of the optimized wing from carbon composite could reduce up to 60% of the wing weight comparing with aluminium one. The stress-strain and buckling analysis of the wing and its power components were carried out in FEMAP software package.

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This paper describes an approach to optimization of composite aircraft wing structure basing on multi-criterion method. Two types of composite wing structures such as two-spar and three-spar ones were considered. The optimal layout of a wing frame was determined by Pareto optimization method basing on three criteria: minimal wing deflection, maximal safety factor and minimal weight. Positions of internal wing frame parts (spars and ribs) were considered as optimization parameters. As a result, an optimal design of a composite spar-type wing was proposed.

This paper describes the optimizing results of structural elements of the composite wing of an unmanned aerial vehicle. The thickness and composite lay-up structure of load-bearing elements and wing skin are determined using the ANSYS software package. The optimal structure is presented using the Pareto set method of the “ideal center” basing on four criteria: minimum mass, deflection, normal stress, and maximum safety factor of the wing. Verification calculations were carried out to determine the safety factor of the load-bearing wing structure using a geometrically nonlinear model in FEMAP software.