scholarly journals Acoustic Impact of Hybrid-Electric DEP Aircraft Configuration at Airport Level

2021 ◽  
Vol 11 (20) ◽  
pp. 9664
Author(s):  
Adolfo Sollazzo ◽  
Francesco Petrosino ◽  
Luciano De Vivo ◽  
Antonio Visingardi ◽  
Mattia Barbarino
Keyword(s):  
Environmental Impact ◽  
Energy Sources ◽  
Chemical Pollution ◽  
Surrounding Area ◽  
Propulsion Systems ◽  
Electric Aircraft ◽  
Acoustic Impact ◽  
Hybrid Electric ◽  
Aircraft Configurations ◽  
Rotary Wing

The Italian research project PROSIB (PROpulsione e Sistemi IBridi per velivoli ad ala fissa e rotante), is a 30-month initiative funded by the Italian Ministry of University and Scientific Research (MIUR) and coordinated by the Leonardo company. The project is aimed to investigate configurations for regional aircraft and rotary wing platforms and architectures for propulsion systems, and is dedicated to the identification of the best strategy for their use, given different on-board energy sources. The reduced environmental impact is the key for the success of the new hybrid/electric aircraft configurations. This not only considers the chemical pollution introduced in the atmosphere, but also the noise produced on the surrounding area of airports. The present paper describes the acoustic impact assessment resulting from the inclusion of new propulsion technologies and new configurations of regional aircraft (ATR42 pax) in a reference airport area.

Conceptual Design and Energy Storage Positioning Aspects for a Hybrid-Electric Light Aircraft

2021 ◽  
Author(s):  
Vasilis Gkoutzamanis ◽  
Mavroudis D. Kavvalos ◽  
Arjun Srinivas ◽  
Doukaini Mavroudi ◽  
George Korbetis ◽  
...  
Keyword(s):  
Energy Storage ◽  
Conceptual Design ◽  
Electric Propulsion ◽  
Co2 Reduction ◽  
Requirements Definition ◽  
Electric Aircraft ◽  
Design Requirements ◽  
Hybrid Electric ◽  
Battery Technology ◽  
Aircraft Configurations

Abstract This work focuses on the feasibility of a 19-passenger hybrid-electric aircraft, to serve the short-haul segment within the 200-600 nautical miles. Its ambition is to answer to research questions, during the evaluation and design of aircraft based on electric propulsion architectures. The potential entry into service of such aircraft is foreseen in 2030. A literature review is performed, to identify similar concepts developed globally. After the requirements' definition, the first level of conceptual design is employed. Following a set of assumptions, a methodology for the sizing of the hybrid-electric aircraft is described, to explore the basis of the design space. Additionally, a methodology for the energy storage positioning is provided, highlighting the multidisciplinary aspects between the sizing of an aircraft, the selected architecture (series/parallel partial hybrid) and the energy storage specifications. The design choices are driven by the aim to reduce CO2 emissions and accommodate boundary layer ingestion engines, with aircraft electrification. The results show that it is not possible to fulfil the initial design requirements (600 nmi) with a fully-electric aircraft configuration, due to the far-fetched battery necessities. It is also highlighted that compliance with airworthiness certifications is favored by switching to hybrid-electric aircraft configurations and relaxing the design requirements (range, payload, battery technology). Finally, the lower degree of hybridization (40%) is observed to have higher energy efficiency (12% lower energy consumption and larger CO2 reduction), compared to the higher degree of hybridization (50%), with respect to the conventional configuration.

scholarly journals Environmental life cycle assessment and operating cost analysis of a conceptual battery hybrid-electric transport aircraft

2021 ◽  
Author(s):  
Anna Elena Scholz ◽  
Dimitar Trifonov ◽  
Mirko Hornung
Keyword(s):  
Life Cycle Assessment ◽  
Life Cycle ◽  
Environmental Impact ◽  
Greenhouse Gas ◽  
Reduction Potential ◽  
Operating Costs ◽  
Transport Aircraft ◽  
Electric Aircraft ◽  
Environmental Life Cycle Assessment ◽  
Hybrid Electric

AbstractNoise and greenhouse gas emission targets set by e.g., the EU commission, NASA, and ICAO oblige the aviation industry to reduce its environmental footprint. Battery-powered hybrid-electric aircraft are currently being investigated in this regard as they can potentially reduce in-flight greenhouse gas emissions and noise. However, most studies to date have focused on the CO2 emission reduction potential instead of considering the total life cycle environmental impact. Hence, within this study an environmental life cycle assessment method for a hybrid-electric aircraft is developed and applied, supplemented by a direct operating costs analysis. This allows the simultaneous evaluation of the environmental impact reduction potential and the economic consequences for aircraft operators. This demonstrates the faced trade-off and contributes to a meaningful review process. A single-aisle transport aircraft (A320 class) serves as a use case for the established methodology. It consists of the conceptual aircraft design, the environmental life cycle assessment, and the direct operating costs analysis for a conventional reference aircraft and a hybrid-electric aircraft with a discrete parallel powertrain architecture. It should be noticed that the focus of this study is the comparison of conceptual aircraft designs of the same fidelity on system level, in lieu of the detailed modeling of a hybrid-electric aircraft. Results show that for a degree of hybridization of 0.3, the environmental impact of the hybrid-electric configuration increased by $$15.1\%$$ 15.1 % , while the operating costs increased by $$41.0\%$$ 41.0 % compared to a conventional reference aircraft. For a future scenario, favourable for hybrid-electric aircraft with i.a. renewable electricity production, the environmental impact could be reduced by $$7.0\%$$ 7.0 % compared to the reference aircraft. At the same time, the operating costs gap between both configurations decreases to $$+ 26.8\%$$ + 26.8 % . Hybrid-electric aircraft should therefore be investigated further as a potential solution to reduce the environmental impact of aviation, if simultaneously to developing them the expansion of renewable energies is fostered. Nevertheless, this reduction in environmental impact involves a high direct operating costs penalty.

Electric/Hybrid-Electric Aircraft Propulsion Systems

2021 ◽  
pp. 1-13
Author(s):  
Patrick Wheeler ◽  
Thusara Samith Sirimanna ◽  
Serhiy Bozhko ◽  
Kiruba S. Haran
Keyword(s):  
Propulsion Systems ◽  
Electric Aircraft ◽  
Hybrid Electric ◽  
Aircraft Propulsion
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