Comparison of Output Characteristics for Various Designs of a 260 kW Fault-Tolerant Aircraft Electric Motor Based On Electromagnetic and Thermal Calculation

Strict requirements that imposed to the characteristics of aviation devices, designed both to reduce the weight and size indicators and to increase the efficiency of the designed devices. In addition, special requirements for safety and reliability are put forward for aviation devices. Designing a device within the established rigid framework is a complex engineering problem, which requires multidisciplinary calculations. This article presents the results of a comparison of output characteristics for various designs of a 260 kW aircraft electric motor for a hybrid electric propulsion system based on electromagnetic and thermal calculation. The results show that the most optimal design in the considered problem is the design with an internal rotor.