Abstract
The electrification of aircraft is a well-established trend in recent years in order to achieve economic and environmental sustainability. In this framework, an application particularly interesting for hybrid electric power system is represented by urban air-mobility. For this application, the authors presented a parallel hybrid electric power system including a turboshaft engine and two electric motors and proposed a quasi-stationary simulation tool. As a further step, this paper deals with the dynamic modelling of the same turboshaft engine within the framework of a hybrid electric system where the pilot command is interpreted as a power request to be satisfied by the engine and the electric machine according to the selected energy management strategy. In this work, the dynamic behaviour of the turboshaft engine is analysed with and without the help of the electric motors to satisfy the power demand.
Highlights
The ever-increasing number of studies concerning electrification of aircraft attests the growing interest in this topic in the aerospace field
The final goal of this study is to develop a dynamic simulation tool for real-time simulation of the whole hybrid electric system and the development of advanced energy management strategies
The present investigation describes the implementation of a dynamic model for a two-spool turboshaft that takes into account the balance of work between the components on the same shafts, the mass balance between adjacent components and the fuel flow rate provided by the fuel control and delivery system
Summary
The ever-increasing number of studies concerning electrification of aircraft attests the growing interest in this topic in the aerospace field. The advantages of hybrid electric power systems for helicopters include separation of the propulsion of main and tail rotor, higher reliability, increased operational lifetime thanks to reduction in the number of devices (e.g., gear, transmission, etc.), improved maintenance workability and lower operational costs together with lower emissions, consumption, noise and vibration levels [1]- [2]. The power and energy required for different missions and emergency landings are estimated in order to size and compare the proposed hybridization schemes. This analysis shows that, with existing technologies for batteries and motors, the electrification of the tail rotor is the only scheme that can be achieved without a significant increase in the mass of the rotorcraft
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