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An alternative way of looking at the limitations of cur- rent technology is to consider replacing the engines on an existing aircraft with an all Electrical Propulsion sys- tem, and seeing what characteristics that system would need to have in order to generate a comparable level of aircraft performance. For example, replacing the exist- ing turbo-prop engines on a Dornier 328 regional air- craft with electric motors and batteries of 180 Wh/kg capacity would reduce the range from 1,200 km to just over 200 km. J In order to restore the range to the baseline figure of 1,200 km, the following changes would also be required: Drag coefficient reduction of 20% through aerodynamics Increase in wing span of 50% to reduce induced drag Reduction in structural mass of 20% Increase in battery capacity to 500 Wh/kg J RANGE OF DORNIER 328 AIRCRAFT UNDER DIFFERENT CONFIGURATIONS [KM] Current battery technology for an all-electric aircraft in today's configurations would result in a drastic fall in range. Think:Act 21 Aircraft Electrical Propulsion In addition to the technical barriers directly related to the electrical system, two other technical barriers related to proposed applications also need to be overcome: AUTONOMOUS FLIGHT Many of the proposed Urban Air Taxis rely on automated, autonomous aircraft that operate with no human inter- vention from the occupants. While highly capable autopi- lot systems already exists in many platforms, these cur- rently remain largely limited to applications without passengers, or operate with pilot supervision. Further developments in autonomous flight – enabled by im- proved sensor technology (both more capable and higher numbers of sensors) and better autonomous flight soft- ware – will be required in the age of commuter air taxis. BOUNDARY LAYER INGESTION One of the potential improvements offered by Electrical Propulsion is the benefit of boundary layer ingestion. Baseline aircraft with turbo-prop engines 1. Turbo-props replaced with electric motors and batteries (180 Wh/kg) 2. As 1. plus drag coefficient reduced by 20% 3. As 2. plus wing span increased by 50% 4. As 3. plus mass reduced by 20% 5. As 4. plus battery capacity doubled to 360 Wh/kg 6. As 5. plus battery capacity doulbed again to 720 Wh/kg Baseline aircraft with electric propulsion at 720 Wh/kg 1,200 202 223 302 329 711 1,455 800 Approximate range with battery capacity at 500 Wh/kg Source: DLR, Roland BergerPDF Image | Aircraft Electrical Propulsion The Next Chapter of Aviation 2017
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