Article: A steady-state model-based evaluation of performance characteristics and feasibility analysis of retrofit hydrogen-powered aircraft configurations Journal: International Journal of Sustainable Aviation (IJSA) 2024 Vol.10 No.2 pp.99 - 123 Abstract: In the current study, in light of the zero-carbon emissions targets, the potential of hydrogen-powered propulsion aircraft is evaluated. The analysis of the aircraft power performance is carried out based on a comparison of jet-fuelled propulsion against the characteristics of that powered by hydrogen. A regional aircraft type ATR 72-600 was chosen for the study. It was configured with three propulsive retrofits: jet-fuelled, direct hydrogen combustion, and hydrogen fuel cell. A computational environment was created in Simulink to model the aircraft's power requirements, fuel consumption, propulsion efficiencies and emissions. Both direct combustion and fuel cell hydrogen propulsions demonstrated performance capabilities within key operational parameters with the benefit of reduced fuel consumption in terms of mass, and, thus, better thrust specific fuel consumption. A fuel mass drop of 50% and 80% were obtained for the hydrogen fuel cell and direct combustion, respectively. A weight penalty, however, remains a major drawback in the implementation of hydrogen technology. Inderscience Publishers - linking academia, business and industry through research

Title: A steady-state model-based evaluation of performance characteristics and feasibility analysis of retrofit hydrogen-powered aircraft configurations

Authors: Bassam Rakhshani; Alexandru Stan; Tony Leslie

Addresses: School of Computing, Engineering and Physical Sciences (CEPS), University of the West of Scotland (UWS), Paisley, PA1 2BE, UK ' Engineering Centre Brasov, Premium Aerotec Ghimbav (Airbus), 507075, Romania ' School of Computing, Engineering and Physical Sciences (CEPS), University of the West of Scotland (UWS), Paisley, PA1 2BE, UK

Abstract: In the current study, in light of the zero-carbon emissions targets, the potential of hydrogen-powered propulsion aircraft is evaluated. The analysis of the aircraft power performance is carried out based on a comparison of jet-fuelled propulsion against the characteristics of that powered by hydrogen. A regional aircraft type ATR 72-600 was chosen for the study. It was configured with three propulsive retrofits: jet-fuelled, direct hydrogen combustion, and hydrogen fuel cell. A computational environment was created in Simulink to model the aircraft's power requirements, fuel consumption, propulsion efficiencies and emissions. Both direct combustion and fuel cell hydrogen propulsions demonstrated performance capabilities within key operational parameters with the benefit of reduced fuel consumption in terms of mass, and, thus, better thrust specific fuel consumption. A fuel mass drop of 50% and 80% were obtained for the hydrogen fuel cell and direct combustion, respectively. A weight penalty, however, remains a major drawback in the implementation of hydrogen technology.

Keywords: aircraft design; aircraft performance; aircraft weight; hydrogen; fuel cell; propulsion; fuel combustion; propulsive efficiency.

DOI: 10.1504/IJSA.2024.138699

International Journal of Sustainable Aviation, 2024 Vol.10 No.2, pp.99 - 123

Received: 11 Jul 2023
Accepted: 23 Dec 2023
Published online: 24 May 2024 *

Title: A steady-state model-based evaluation of performance characteristics and feasibility analysis of retrofit hydrogen-powered aircraft configurations

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