Development of the design of an experimental long-range fixed wing uav

Abstract

The goal of the article is the design and assembly of a flight-capable platform for testing an experimental hybrid drive developed within the grant project. The input for the entire work is designed for the highest take-off weight of 10 Kg and a pair of driving electric motors with a thrust of 5 Kg each (49,05 N). The content of the article includes basic theory, analyses, simple structural calculations and design methods, the design itself, construction methodology and work results. Analyzes in the article include analyzes of currently used types for the design and construction of hybrid unmanned aerial vehicles and analyzes of materials used for UAV structures with a piston propulsion unit, on the basis of which the design and construction of the UAV was proposed. As part of the design, the construction and design are recalculated and simulated both aerodynamically and strength-wise. Several software were used in the design and simulations: AutoCAD Inventor for modeling and strength analyses, Autodesk CFD for airfoil simulations and XFLR5 for the aerodynamics simulation of the UAV design. In the practical part, the production methodology is described in detail and illustrated with original photographs.