Abstract
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.
Highlights
An unmanned aerial vehicle (UAV) is defined as a type of aircraft with an engine that does not carry a human pilot, uses aerodynamic force to create a lift, can fly autonomously or remotely, and can carry a payload
Aerodynamic pressure load was distributed on the surface of the lower skin of the UAV wing
The optimization of the laying up structure of the optimal composite material was considered: CFRP fibric, considering the existing aerodynamic loads
Summary
An unmanned aerial vehicle (UAV) is defined as a type of aircraft with an engine that does not carry a human pilot, uses aerodynamic force to create a lift, can fly autonomously or remotely, and can carry a payload. The weight of the vehicle is always an important parameter, characterizing the technical perfection of the UAV, as this characteristic depends on the maximum altitude and range of flight, as well as the handling of the aircraft and its maneuverability. This study looked at the two-spars straight wing structure with a wingspan of 10.5 m and a chord length of 0.78 m. The position of the front and rear spars was fixed at a relative distance of 30% and 60% of the chord from the edge of the wing. The purpose of this work was to determine the optimal design and structural parameters of the composite wing of an unmanned aerial vehicle
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