International Scientific Journals
of Scientific Technical Union of Mechanical Engineering "Industry 4.0"

The use of aircraft-type unmanned aerial vehicles (UAVs) is considered. The advantages, disadvantages and limitations of specific configurations of the UAV body are described. The requirements for simultaneous assessment of materials are described, with an emphasis on modern composite materials forming structurally reinforced or three-layer structures of some UAV elements. It is proposed to take the mass efficiency coefficient of the model as a basis for comparison of aircraft-type UAVs, which determines what part of the mass of the considered design corresponds to the requirements of users. A static analysis of the fuselage and wings of aircraft-type UAVs, made with new materials, was carried out, determining the parameters and their shapes in order to reduce the bending moment acting on the structural elements of the wing, which would reduce its weight. Safety coefficients for the operation of aircraft-type UAVs with certain materials and the financial situation in their design based on forecasting time series of changes in the requirements for the use of UAVs are proposed.

The use of aircraft-type unmanned aerial vehicles (UAVaircraft type) in modern combat operations is considered. Basic temporary criteria for the production and operation of aircraft-type UAVs are defined. Using the similarity method, a determination of the mass of aircraft-type UAVs is proposed. A variant is proposed related to the calculation of the mass of the fuselage of certain aircraft-type UAV models. The difference in the use of retractable or fixed landing gear of aircraft-type UAV types in their operation is determined. Recommendations are made for noise reduction during UAV operation. The economic aspects of aircraft-type UAV design are touched upon.