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Aircraft Electrical Propulsion The Next Chapter of Aviation 2017

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Aircraft Electrical Propulsion The Next Chapter of Aviation 2017 ( aircraft-electrical-propulsion-the-next-chapter-aviation-201 )

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by the Boeing 777 in 1994. This technology significantly reduced weight and provided additional space for other aircraft components by enabling the electrical transmis- sion of instructions from the cockpit to the flight control surfaces, eliminating the need for mechanical linkages. The next big step came with the A380 and the imple- mentation of an electrically actuated thrust reverser, along with hybrid electro-hydraulic actuation systems for wing and tail flight control surfaces. Finally, the 787 was the first Large Commercial Aircraft to have an electrically-powered environmental control (air-conditioning) system, and to employ electrically actuated brakes, as well as electrical de-icing. Furthermore, although the 787 has a relatively conventional hydraulic system, the pressure within the sys- tem is generated by electrically-powered hydraulic pumps. In the military sphere the F-35 Joint Strike Fighter (JSF) A Think:Act 5 Aircraft Electrical Propulsion employs a fully hybrid electro-hydraulic actuation sys- tem, a high voltage direct current electrical distribution system that minimises weight, and has significantly higher electrical power generation capacity than previous generations of fast jets in order to power the aircraft sen- sors and other systems. B The electrical generating capacity of each succes- sive generation of aircraft has increased, with the Boeing 787 and Lockheed Martin F-35 representing significant step changes. Another trend has been the switch from constant frequency generation derived from a constant speed gearbox and generator, to variable frequency generation with power electron- ics to convert the electrical output to the various fre- quencies and voltages required by different types of electrical equipment. C ENGINE POWER OUTPUT FOR A330-SIZED AIRCRAFT [MW] With Electrical Propulsion, the thrust equivalent to that of the engine would be provided electrically – a c. 25 times step up in power. Electric generator Electrical 200 kW High pressure bleed air Pneumatic 1.2 MW Hydraulic pump Hydraulic 240 kW Fuel & oil pumps Mechanical 100 kW Thrust power c. 40 MW Total non-thrust power c. 1.7 MW Potential scope of More Electric Aircraft Source: University of Nottingham "Electrical Machines for Aerospace Applications", Roland Berger Fuel

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