Sustainable Aviation Electrification: A Comprehensive Review of Electric Propulsion System Architectures, Energy Management, and Control

Zhang, Jinning; Roumeliotis, Ioannis; Zolotas, Argyrios

doi:10.3390/su14105880

Cited by 5 publications

(1 citation statement)

References 109 publications

(135 reference statements)

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“…Thus, the civil aviation sector plays an increasingly significant role in transport sustainability with regard to environmental, economic, and social dimensions. In order to decarbonize the traditionally carbon-intensive aviation sector, electrified aircraft propulsion (EAP) have been identified and emerged as a promising technology, with advantages of on-board generating, distributing, and utilising electric power to eliminate direct combustion emissions in flight, as well as to improve the vehicle efficiency and performance [2]. In addition, the indirect CO 2 emissions from on-board electricity can be further alleviated on the ground energy infrastructure with the integration of renewable and sustainable energy sources, such as solar, wind and hydrogen [3].…”

Section: Introductionmentioning

confidence: 99%

Techno-economic-environmental evaluation of aircraft propulsion electrification: Surrogate-based multi-mission optimal design approach

Zhang¹,

Roumeliotis²,

Zhang³

et al. 2023

Renewable and Sustainable Energy Reviews

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Section: Introductionmentioning

confidence: 99%

Techno-economic-environmental evaluation of aircraft propulsion electrification: Surrogate-based multi-mission optimal design approach

Zhang¹,

Roumeliotis²,

Zhang³

et al. 2023

Renewable and Sustainable Energy Reviews

Self Cite

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Integrated Hybrid Engine Cycle Design and Power Management Optimization

Ghelani,

Roumeliotis,

Saias

et al. 2024

Journal of Engineering for Gas Turbines and Power

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An integrated gas turbine cycle design and power management optimization methodology for parallel hybrid electric architectures is shown in this article. The gas turbine cycle design method is extended to both turboprop and turbofan architectures with trade studies performed initially at cycle level. It is shown that the degree of electrification is limited by the surge margin levels of booster for turbofan configuration. An aircraft mission level assessment is then performed using the integrated method initially for an A320 Neo style aircraft case. The results indicate that optimal cycle redesigned hybrid electric propulsion system (HEPS) favor take-off and climb power on-takes while optimal retrofit HEPS favor cruise power on-takes. It is shown that for current battery energy density (250 Wh/Kg), there is no fuel burn benefit. Furthermore, even for optimistic values (750 Wh/kg), the maximum fuel burn benefit for 500 nm mission is 5.5% and 4% for redesigned and retrofit HEPS, respectively. The power management strategies for HEPS configurations also differ based on gas turbine technology with improvement in gas turbine technology showing greater scope for electrification. The method is then extended to ATR 72 style aircraft case, showing greater fuel burn benefits across the flight mission envelope. The power management strategies also change depending on the objective function, and optimum strategies are reported for direct operating cost or fuel burn. Finally, a novel multi-mission approach is shown to highlight the overall fuel burn and direct operating cost benefit across the mission cluster.

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Analysis of landing noise from Airbus A321neo using long term noise measurements and flight recorder data

Johansson

Bolin

2023

The Journal of the Acoustical Society of America

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This article analyzes aircraft noise measurements from the Airbus A321neo at 7.5 and 5 nautical miles from the runway threshold. Using correlation, analysis of variance, and hierarchical regression analysis, we assessed the influence of flight data recorder variables and meteorological parameters on the measured sound level variations. A combination of aircraft speed and configuration of the high lift devices can predict approximately 60% of the sound level variations. Sound level dependence on speed ranges between 0.5 and 1.5 dB/10 kn for different configurations and landing gear deployment had a +3 dB impact on sound levels. At the same time, weather and wind conditions accounted for a relatively small proportion of the variation. Overall, this study sheds light on the factors contributing to aircraft noise during the final approach and provides insights into potential noise reduction strategies.

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Sustainable Aviation Electrification: A Comprehensive Review of Electric Propulsion System Architectures, Energy Management, and Control

Cited by 5 publications

References 109 publications

Techno-economic-environmental evaluation of aircraft propulsion electrification: Surrogate-based multi-mission optimal design approach

Techno-economic-environmental evaluation of aircraft propulsion electrification: Surrogate-based multi-mission optimal design approach

Integrated Hybrid Engine Cycle Design and Power Management Optimization

Analysis of landing noise from Airbus A321neo using long term noise measurements and flight recorder data

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