Herzog, Use of stochastic models for operational efficiency analysis of multi power source traction drives, in Proc. of 12th International Conference and Exhibition on Ecological Vehicles and Renewable Energies (EVER), Monaco, 11–13 April 2017, pp. Kammermann et al., The choice of an optimal structure and parameters of energy storage for an electrical helicopter traction drive, in Proc. Conference on Information and Digital Technologies (IDT), Žilina, Slovakia, 5–7 July 2017, pp. Kammermann et al., Comparison of the battery energy storage and fuel cell energy source for the safety-critical drives considering reliability and fault tolerance, in Proc. The feasibility of the realization of the electric version of the helicopter's propulsion system depends entirely on the optimal selection and placement of each component of the traction drive. The feasibility evaluation of helicopter's electric propulsion is provided based on comprehensive analysis, its weight, volume, efficiency, and reliability features. The chapter discusses the advantages and technological problems, which are associated with the thoroughgoing transformation of the conventional propulsion system of helicopter with two turbine engines to the novel non-conventional traction drive topologies. The chapter is concerned with the investigation of the actual feasibility and prospects of creating an innovative type of electrical helicopter’s propulsion system based on battery electric storage fuel cell electric energy source, ultracapacitors, and a superconducting electric motor for the conventional airbus helicopter EC135 with two gas turbine engines and a speed reducer. Currently, the developers of various companies in accordance with the program more electric aircraft (MEA) consider the electrification of aircraft of different types and purposes, such as the airplanes as well as the helicopters, as one of the most promising directions in the development of aviation technology.
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