Design Factors of High-Speed Turbo-Electric Distributed Propulsion System

Abstract Turbo-electric Distributed Propulsion (TeDP) is a promising concept to achieve the operational goals of more electric aircraft. The application TeDP architecture can desired weight reduction an aircraft power system. use superconducting machine expected provide workaround for issue, but its current state technology has not yet been extensively tested applications. Another practical option directly couple aircraft's propeller system high-speed permanent magnet (PM) electrical machine, eliminating gear part that also contributes total weight. A critical design PM choosing optimum configurations. This study used finite element modelling analyze impact scaling PM’s parameters on and speed. prototype testing 2-KW suitable Remotely Piloted Aircraft System (RPAS), was developed tested. results confirmed following should be carefully designed output, such as (a) number winding turns, (b) stack length, (c) sleeve thickness, (d) terminal voltage.