The goal of this study was the intention to demonstrate the expediency of utilization of bamboo composites in manufacturing of aircrafts. The research and testing of the material were conducted in the laboratories of the Institute of Aerospace Technolgies (IAT) of the National Technical University of Ukraine “Igor Sikorsky Kyiv Polytechnic Institute”. To determine the expediency of using bamboo composite, it is necessary to conduct tests of the material for external effects and analyse economic feasibility. The main advantages of such a material are its environmental friendliness and cheapness of both raw materials and processing. This article is dedicated to analysing the results of the research on the mechanical characteristics and economic aspects. Bars of different sizes, different materials, and different degrees of processing were used for the analysis. The results of the testing conducted have showed that the strength characteristics of a bamboo composite are higher than that of the majority of wood species. At the same time, bamboo elements are lighter judging by weight characteristics. The undisputable advantage of their usage is a powerful and widespread structure of existing manufacturing which does not require creation of new processing machinery.

Fan wing concept increased the efficiency of using the kinetic energy of the movement of air that flows around the wing. It allow generate thrust and lifting forces. But this scheme also has drawbacks. The most important associated with the significant drag force. The large diameter of the cross-flow fan, in case of failure of the power plant, the aerodynamic quality will be approximately 1: 3. To improve parameters and increase the feasibility of using this scheme, we need to review the existing concepts and change the basic geometric parameters of the cross-flow fan and try to reduce the diameter. It is advisable to increase the speed of its rotation. This work performed calculation and compare lift force and thrust force generated by the system. Compare various positions of the blades, and airflow rate at the outlet of the engine by numerical simulation. Also studied the effect of the profile shape of the blades and their amounts on the performance. As a result, analysis of the interaction of all these parameters to determine the model with the best aerodynamic performance. Numerical modeling turned out to be very resource-intensive. So the main focus on a series of physical experiments with real models. The results show that this scheme has more benefits when compared with before use. So, the proposed idea has good prospects for development and application.

The subject of the study is the optimization of aerodynamic characteristics by improving the wing profile shape for the fan-wing configuration. The aim of this work is to find a more universal wing shape suitable for various aircraft. The task is to compare the characteristics of three wings with the same rotor engine installed in the nose section, including the base wing used in most previous studies by scientists. Sources suggested that this profile is not well-suited for rotor engines with a large aspect ratio. Experimental methods were used to measure the dynamic characteristics of three wing profiles: a flat curved profile with a cut-out in the rear wing section, a flat lower surface profile, an S-shaped profile with a lower surface bend in the rotor area, and a two-bend contour with a cut-out in the rear wing section on top and bottom. The results showed an improvement in characteristics compared with wing-rotor engine schemes used in previous cases. Specifically, an increase in the flow velocity at the wing exit of 3...8 % depending on the power plant operating mode was found, which led to an increase in lift up to 20 % depending on the flight mode, and an increase in thrust up to 16 %. Conclusions. The proposed S-shaped profile with a lower surface bend in the area of the rotor hub, and a profile with two bends in the contour with a cut in the rear part of the wing from the top and bottom contours have the most optimal and balanced characteristics. In the future, it is planned to manufacture these profiles using composite materials to reduce weight and install them on the aircraft prototype, replacing the rotor structure with a more flexible one using more flexible materials such as PETG plastic for the synchronization of the installed rotor motors, which is necessary to increase reliability and backup the rotor drive. Additionally, several sections with independent engines are planned to be made on each wing console to counteract rotor rupture in the event of engine failure. Due to significant advantages over the standard profile shape and minor structural complexity, the manufacture of more complex profile shapes can find wide applications in aircraft designed according to the fan-wing scheme.

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