Hybrid-Electric Distributed-Propulsion Aircraft

A special issue of Aerospace (ISSN 2226-4310).

Deadline for manuscript submissions: closed (31 May 2021) | Viewed by 6496

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Guest Editor
DIMEAS - Department of Mechanical and Aerospace Engineering, Politecnico di Torino, Turin, Italy
Interests: on-board systems electrification; systems architecture optimization; on-board systems integration
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Dear colleagues,

Hybrid-electric propulsion is growing increasingly relevant in the aeronautical segment. New propulsive concepts are developed with different levels of electrification up to full electric propulsion. These concepts will probably represent the future of aeronautics, giving  researchers new ways to optimize the aircraft, reducing polluting emissions and improving its environmental compatibility.

These new propulsion technologies have some important effects on the overall aircraft design. The electric propellers or fans can be designed and installed, enhancing the aerodynamic qualities of the aircraft, decreasing the induced drag of the wing and the fuselage drag and accelerating the boundary layer. Other concepts of distributed propulsion allow us to increase the wing lift, shorting the takeoff and landing distances.

The short takeoff and landing capability and the reduction of noise and polluting emissions allow this new aircraft capacities to operate outside congested airspaces. Being able to use small airports may reduce the passengers’ door to door time. New business strategies can be envisaged as well.

However, the hybrid-electric propulsion cannot be developed without the improvement of all aircraft systems and specific equipment. A lot of effort is spent to increase the battery energy density and electric motor power density to achieve the necessary mass reduction. All the aircraft systems are moving towards a deep electrification with increased voltage to simplify their architecture and improve their efficiency.

All your contributions will be very welcomed to improve this new and engaging branch of aerospace science.

Dr. Marco Fioriti
Guest Editor

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Keywords

  • Hybrid-electric propulsion
  • distributed propulsion
  • wing tip propellers
  • boundary layer ingestion
  • systems electrification
  • more electric aircraft
  • high voltage systems
  • high density battery
  • advanced electric motor
  • thermal management
  • aircraft operation
  • aircraft cost estimation

Published Papers (1 paper)

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Research

28 pages, 14790 KiB  
Article
Comparative Analysis and Optimization of Technical and Weight Parameters of Turbo-Electric Propulsion Systems
by Mykhaylo Filipenko, Stefan Biser, Martin Boll, Matthias Corduan, Mathias Noe and Peter Rostek
Aerospace 2020, 7(8), 107; https://doi.org/10.3390/aerospace7080107 - 27 Jul 2020
Cited by 16 | Viewed by 5876
Abstract
According to Flightpath 2050, the aviation industry is aiming to substantially reduce emissions over the coming decades. One possible solution to meet these ambitious goals is by moving to hybrid-electric drivetrain architectures which require the electric components to be extremely lightweight and efficient [...] Read more.
According to Flightpath 2050, the aviation industry is aiming to substantially reduce emissions over the coming decades. One possible solution to meet these ambitious goals is by moving to hybrid-electric drivetrain architectures which require the electric components to be extremely lightweight and efficient at the same time. It has been claimed in several publications that cryogenic and in particular superconducting components can help to fulfill such requirements that potentially cannot be achieved with non-cryogenic components. The purpose of this work was to make a fair comparison between a cryogenic turbo-electric propulsion system (CEPS) and a non-cryogenic turbo-electric propulsion system (TEPS) on a quantitative level. The results on the CEPS were presented in detail in a previous publication. The focus of this publication is to present the study on the TEPS, which in conclusion allows a direct comparison. For both systems the same top-level aircraft requirements were used that were derived within the project TELOS based on an exemplary mission profile and the physical measures of a 220-passenger aircraft. Our study concludes that a CEPS could be 10% to 40% lighter than a TEPS. Furthermore, a CEPS could have a total efficiency gain of up to 18% compared to a similar TEPS. Full article
(This article belongs to the Special Issue Hybrid-Electric Distributed-Propulsion Aircraft)
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