To reduce emissions of air traffic, future aircraft will install hybrid-electric propulsion systems. We require the load conditions over the time in service, to design these aircraft. In this paper, we propose a mission profile for a regional aircraft with a hybrid-electric propulsion system. We focused on regional aircraft, which are in service in Ireland and the United Kingdom (UK). The reference aircraft ATR 72-600 is a turboprop aircraft with a capacity of 70 passengers. To propose a mission profile, we have analyzed more than 6000 flights of four different aircraft of the same type. Input data is provided by online databases, which collect flight data. We are able to show that the maximum available power is needed for about 52 seconds during takeoff and climb phase of the flight. The median flight time is 59 minutes and 30 seconds. The average required power is 53 % of the maximum power. The average traveled distance is 407 km, which is less than one third of the aircraft's maximum reach. These findings are needed for calculating the lifetime of drivetrain components of a hybrid or all electric aircraft. In our further work, we will design an electric machine for regional aircraft. This mission profile will be used to design different power train components.

This paper presents an extended dq0-model for small delta-connected Permanent Magnet Synchronous Machines (PMSM), the design of a prototype and the parameterization of the model parameters by testbench measurement. The familiar dq-fundamental equations are thereby extended to consider harmonic effects. This allows the inclusion of the zero-sequence flux-linkage. The model, based on the dq0-flux-linkages and the stator resistance, enables the calculation of the zero-sequence current and a more precise inner torque estimation compared to state of the art fundamental models. The rotor position dependent dq-flux-linkage estimation is based on the measured dq-voltages and the solution of the simplified differential system equation. Detection of the zerosequence current yields to the zero-sequence flux-linkage. In this paper, we also present a prototype design of a PMSM machine with additional zero-sequence current sensing. Testbench measurement at constant controlled currents enables the parameter identification. For validation, the identified parameters are compared with existing Finite Element Analysis.

Stator winding faults are one of the major limitations of the lifetime and reliability of electrical machines. Interturn faults are for that matter often the origin of more severe faults, which can lead to complete system failures. This paper presents an analytical machine model, to investigate the behavior of PMSMs with dynamic stator winding faults on turn level. In order to keep the model compact, the levels of abstraction can be adapted within the machine model. The acausal implementation of the electric domain allows the simulation of one model with different operating modes. This paper compares the simulation results of the analytical model with FEA simulation results. The average torque differs in case of two inter-turn faults at nominal load operation by 2 % and the amplitude of the fault currents differs by 5 %. There is no difference in the frequencies and phase angles of the fault currents and the torque. In our future work, we will use the presented model to develop a fault management system, allowing fault tolerant operation of safety critical applications.

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