Abstract
The paper presents a multidisciplinary methodology for designing a power generation system for an aircraft. The presented design sequence corresponds to the proposed methodology; the design of the aircraft power generation system was created. Based on this project, a prototype of the power generation system was implemented; stand tests showed good convergence (an inaccuracy of no more than 3%) with the calculation results. During the design, we solved a number of optimization problems that made it possible to obtain an optimal power generation system in all, rather than components with optimal characteristics, as is usually done. The proposed methodology can be used to create power supply systems for aircraft with different voltage levels, including 270 VDC and 200 VAC. Developed power generation system will be used for future aircraft and helicopters, as it turned out to be 25-40% better in weight and efficiency than serial solutions. In addition, suggested power generation system has a higher reliability than industrial systems.
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