A Route to Sustainable Aviation: A Roadmap for the Realization of Aircraft Components With Electrical and Structural Multifunctionality

Jones, C. E.; Norman, Patrick; Burt, Graeme; Hill, Callum; Allegri, Giuliano; Yon, Jason; Hamerton, Ian; Trask, Richard S.

doi:10.1109/tte.2021.3078118

Cited by 24 publications

(11 citation statements)

References 82 publications

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“…1) Improved gravimetric energy density of battery technology [15]; and, 2) Novel aircraft design from scratch with lower structural weight, higher aerodynamic efficiency, and use of multifunctional materials [32]- [34].…”

Section: B Key Solutions To Battery-electric Challengesmentioning

confidence: 99%

Potential and Limitations of Battery-Powered All-Electric Regional Flights—A Norwegian Case Study

Baerheim

Lamb

Nøland

et al. 2023

IEEE Trans. Transp. Electrific.

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The purpose of this study is to look at both the potential and the limitations of first-generation electric aviation technology while emphasizing Norway's geographical opportunities and unique regional network. Electric flight distances up to 400 km would cover around 77 % of all flights within Norway. Currently, there is limited research into the suitability of battery-powered all-electric aviation in such scenarios, where Norway is an ideal case study location. In this work, the key factors, including battery technologies, propulsion systems, aircraft designs, and important aspects of the flight profile, are investigated to determine the suitability of specific routes in terms of the required power, energy, and battery size. A case study of five different flight distances in Norway (77 −392 km) and two different aircraft bodies (one retrofitted with an electric powertrain and one completely designed around the electric drivetrain) are presented. While the completely redesigned aircraft is observed to fulfill the power requirements of the routes, the results suggest that modest energy density improvements in batteries would facilitate retrofitting pre-existing aircraft. Finally, the study shows that it will be feasible to operate small (9 −39 passenger) electric aircraft on short-haul flights in Norway through either new aircraft designs or retrofitting shortly.

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Section: B Key Solutions To Battery-electric Challengesmentioning

confidence: 99%

Potential and Limitations of Battery-Powered All-Electric Regional Flights—A Norwegian Case Study

Baerheim

Lamb

Nøland

et al. 2023

IEEE Trans. Transp. Electrific.

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“…Due to the cryogenic temperature of the LH 2 , the electrical machine and power transmission systems can be made superconducting, which is projected to dramatically reduce the size of the propulsion system [7], without the need to add weight-intensive cryocoolers. Another way to cut aircraft weight is to pursue multi-functional (MF) materials, integrating both mechanical and electrical properties [8].…”

Section: Airmentioning

confidence: 99%

Dual Use of Liquid Hydrogen in a Next-Generation PEMFC-Powered Regional Aircraft With Superconducting Propulsion

Hartmann

Nøland

Nilssen

et al. 2022

IEEE Trans. Transp. Electrific.

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In this paper, we present a comprehensive model framework for a disruptive cryo-electric propulsion system intended for a hydrogen-powered regional aircraft. The main innovation lies in the systematic treatment of all the electrical and thermal components to model the overall system performance. One of the main objectives is to study the feasibility of using the liquid hydrogen (LH 2 ) fuel to provide cryogenic cooling to the cryo-electric propulsion system, and thereby enable ultracompact designs. Another aim has been to identify the optimal working point of the fuel cell to minimize the overall propulsion system's mass. The full mission profile is evaluated to make the analysis as realistic as possible. Analyses are done for three different 2035 scenarios, where available data from the literature are projected to a baseline, conservative, and optimistic scenario. The results show that the total propulsion system's power density can be as high as 1.63 kW/kg in the optimistic scenario and 0.79 kW/kg in the baseline scenario. In the optimistic scenario, there is also sufficient cryogenic cooling capacity in the hydrogen to secure proper conditions for all components, whereas the DC/DC converter falls outside the defined limit of 110 K in the baseline scenario.

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“…8, while the fault current will be too low to detect the fault based on conventional over-current based protection (20 % change in current) if the fault resistance is more than 9.75 Ω (for topology (a)) or 19.5 Ω (for topology (b)), the power dissipated through the CFRP will be ~ 7.5 kW for topology (a) and ~ 14.5 kW for topology (b). More than 18 W of power dissipation through CFRP will lead to thermal degradation of the resin matrix, as the glass transition temperature (Tg) will be reached [23].…”

Section: Selection Of Grounding Topology To Support Fm Approachmentioning

confidence: 99%

A Modelling Design Framework for Integrated Electrical Power and Non-Electrical Systems Design on Electrical Propulsion Aircraft

Jones

Millar

Fong

et al. 2022

2022 IEEE Transportation Electrification Conference &Amp; Expo (ITEC)

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The electrification of power and propulsion systems on aircraft is a key enabler for the decarbonisation of aviation. A significant challenge for the design of these electrical power systems is that electrical propulsion is a disruptive technology, with neither the associated electrical power system (EPS) architectures nor industry standards established. Compared to conventional, state-of-the-art aircraft, these next-generation aircraft necessitate much more interdependent design of different systems and sub-systems. As such, the efficient design and downselection of an EPS which meets both performance (e.g. weight) and dynamic functionality requirements is challenging. This paper builds on a pre-existing, hierarchical-based EPS modelling framework developed by the authors to present a new design methodology which also incorporates bi-directional interfaces between EPS performance and dynamic functionality, and EPS and non-electrical systems design. The methodology is demonstrated for interdependent electrical power and nonelectrical power systems design, through a case study focussing on the development of a fault management strategy for an EPS integrated with a carbon fibre reinforced polymer structure on a concept electrical vertical take-off and land aircraft.

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A Route to Sustainable Aviation: A Roadmap for the Realization of Aircraft Components With Electrical and Structural Multifunctionality

Cited by 24 publications

References 82 publications

Potential and Limitations of Battery-Powered All-Electric Regional Flights—A Norwegian Case Study

Potential and Limitations of Battery-Powered All-Electric Regional Flights—A Norwegian Case Study

Dual Use of Liquid Hydrogen in a Next-Generation PEMFC-Powered Regional Aircraft With Superconducting Propulsion

A Modelling Design Framework for Integrated Electrical Power and Non-Electrical Systems Design on Electrical Propulsion Aircraft

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