First step of aircraft design is calculation of initial parameters, based on assumptions determining flight parameters which designed aircraft should meet. During these calculations, it is possible to pre-detect structure instability called a flutter. These calculations are made based on the geometric parameters assumed in the first conceptual drawings of the flying vehicle. Assumed masses and speeds allow for preliminary analysis of forces acting on the structure. The next step is to determine the displacements and deformations occurring in the structure of the aircraft in different phases of flight and under different conditions. The article presents all the stages of wing analysis for a proposed stratospheric drone with a highly flexible wing structure. This analysis, after integration with CAD software, will allow for the preparation of a comprehensive generative model. The basic assumptions of the designed aircraft are: flight altitude, wings area, very extended or unlimited flight time, approximate flight speed, climbing time, hull parameters, rudder size and placement, wing profile and mass of the structure. These assumptions made it possible to carry out a preliminary analysis of loads, wing pressure distribution, lift force and total resistance force. The goal of the research is to develop a methodology of preliminary flutter analysis which can be easily integrated in the form of calculation backgound for generative model. This methodology has been developed to determine displacements, structure stability and critical vibration frequencies. CAD software after integration with constantly optimizing calculation software will allow the generation of optimal shape and structure rigidity for given initial assumptions.

This article presents the results of work related to the design, analysis, and manufacturing of the shaft for an electric go-kart. Works considered the stiffness of the shaft for various conditions affecting the vehicle while driving. In the previous stage of the project, the electric motor and gear transmission were selected. The main goal of this case study was to design the shaft for 10 kW electric go-kart. The rear driving axle of the go-kart is not equipped with a differential. The equal rotational speed of two rear wheels causes that occurs skidding and greater forces acting on the vehicle and driver when cornering. We were considering two types of the shaft – full and drilled. The first one provides greater stiffness, the second one is “softer”. The analysis allowed for the selection of a more appropriate shaft, and then for its manufacture and assembly in the vehicle.

Fix-wings small aircraft or drones, for flight, must be equipped with a source of thrust. In most cases, it will be propulsion systems including engine and propeller that generate the necessary thrust force. Regardless of whether the system includes an electric motor, combustion, or hydrogen engine of torque moment, the most important element of the system is the propeller. It is the element responsible for generating thrust, which is the force necessary for the flight in each of its stages. The article presents all stages of the analysis and optimization of the propeller for the considered highly flexible structure stratospheric drone. Analysis, after integration with CAD software, allows for the preparation of a comprehensive generative model. The basic propeller parameters were selected on the basis of flight altitude, considered structure, flight time, flight speed, the weight of the structure, assumed location of the engine and propeller. These assumptions made it possible to conduct a preliminary analysis of loads, propeller blade pressure distribution, thrust, and the total level of vibrations. The goal of the research is to develop a methodology of designing and preliminary analysis of propeller, which can be integrated into the generative model.