Power Distribution and Propulsion System for an All-Electric Regional Aircraft

Ebersberger, Janine; Keuter, Ralf Johannes; Ponick, Bernd; Mertens, Axel

doi:10.1109/esars-itec57127.2023.10114868

Cited by 2 publications

(1 citation statement)

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“…For practical purposes, the flow velocity is set to 20 m/s as described in [21]. Since the trade-off in the electric motor's power density and efficiency is dependent on the energy storage density, a comparable system architecture as presented in [22] is set up. The energy storage density hereby corresponds to 700 Wh/kg.…”

Section: Boundary Conditions Of the Investigationmentioning

confidence: 99%

Design of a Direct-Liquid-Cooled Motor and Operation Strategy for the Cooling System

Keuter,

Niebuhr,

Nozinski

et al. 2023

Energies

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To make an all-electric aircraft possible, both high power densities and efficiencies are needed. However, particularly high demands are also placed on the thermal management system. Often, the electric motor and cooling system are considered without co-optimization. Particularly in the case of electric motors with conductors directly cooled by a liquid, there is great potential for optimization, since the temperature-dependent Joule losses determine the largest part of the losses. This publication shows the main influencing parameters for the electric motor and cooling system: coolant speed and winding temperature. In addition, the influence of the cooling system control during a flight mission is demonstrated and its potential in mass reduction is quantified. It could be shown that with a low utilized electric motor the maximum winding temperature of 130 °C is beneficial, the cooling system should work in almost all operation points in its sized operation and the mass of the heat exchanger and pump is negligible compared to the mass of the electric motor and energy storage.

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Section: Boundary Conditions Of the Investigationmentioning

confidence: 99%