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Item type:Publication, Access status: with files , Results of the H2Avia project: potential of hydrogen for global aviation(Multidisciplinary Digital Publishing Institute (MDPI), 2026-06-12); ; ; ; Moser, LeonardThis paper presents an integrated assessment of liquid hydrogen as an aviation energy carrier, covering fuel production, aircraft performance, and fleet-level climate impacts. The results, based on the H2Avia research project, indicate substantial potential for reducing life-cycle global warming impacts compared to conventional kerosene. The analyses conducted for the interdisciplinary assessment are presented. The analysis shows that the use of liquid hydrogen eliminates CO<sub>2</sub> emissions during fuel burn, resulting in a significant reduction in global warming potential compared to conventional kerosene, despite remaining upstream emissions from production and transport. The aircraft application cases and the applied technologies assessment scenario are described. The modeled technologies essential for the hydrogen aircraft are discussed, and exemplary values are given. Integrated overall aircraft performance results are given and discussed. At the aircraft level, hydrogen-based aircraft require an 8–18% increase in design mission block energy compared to a 2040 kerosene baseline yet still achieve a reduction in effective global warming potential of 55–86% comparing a representative pair route between Europe and North America (6730 km). An overview of the fleet modeling approach and the applied scenarios is given. For a scenario with energy cost and climate impact as equally weighted minimization goals, the global fleet analysis yields a global warming potential reduction of 60% compared to the non-liquid hydrogen baseline scenario. Overall, the results suggest that liquid hydrogen-powered aircraft can deliver significant mission- and fleet-level reductions in global warming potential and thus represent a promising pathway for achieving long-term aviation climate targets.Publicationtype: Journal Article40 12 - Some of the metrics are blocked by yourconsent settings
Item type:Publication, Access status: with files , A modular life cycle assessment framework for novel aircraft configurations and sustainable aviation fuels(Association of American Publishers, 2026); ; 19 6 - Some of the metrics are blocked by yourconsent settings
Item type:Publication, Access status: without files , Methodology for design and evaluation of more electric aircraft systems architectures within the AVACON project(Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V. (DGLR), 2019-01-11); ; ; ; Within the research project AdVanced Aircraft CONfiguration (AVACON) a collaborative conceptual design of a mid-range aircraft with ultra high bypass ratio (UHBR) engines and an envisioned entry-into-service in the year 2028 is conducted. In this paper, the approach for overall architecting, sizing, and evaluation of aircraft on-board systems in AVACON is presented. To this end, important contributions to conceptual system design methods proposed in the literature are reviewed to identify directions for methodological improvements. The role allocation of contributing partners and their methodologies for system design activities is described. Having different contributors guarantees, that tasks from overall aircraft to detailed subsystem design with a successive increase in the fidelity of system models is covered. In addition, a state-of-the-art baseline architecture is defined, which will serve as a starting point to conduct trade-off studies for investigation of the potential of system architecture concepts and innovative technologies. Substantial system design requirements and novel boundary conditions, implied by the advanced aircraft configuration, are derived to give an outlook for planned technology studies.Publicationtype: Journal Article49 - Some of the metrics are blocked by yourconsent settings
Item type:Publication, Access status: without files , Feasibility study of a hybrid ice protection systemAkey design factor impacting the use of electrical power to drive aircraft systems and subsystems is energy efficiency. With the design of an all-electric, hybrid ice protection system, energy consumption can be reduced to a large extent. The hybridization is achieved through an intentional partitioning of the ice at the stagnation line by melting via surface heating and ice shedding in the unheated regions of the airfoil surface via an electromechanical deicing systembased on piezoelectric multilayer actuators. To further reduce energy consumption, the adhesion forces between the ice and the airfoil surface can be reduced using an ultrasmooth,nanostructured surfacewithwater-and ice-repellent properties that encourages ice shedding. Experimental investigations, performed in a laboratory-scale icing wind tunnel for a smallscale configuration, reveal that the hybrid approach for ice protection reliably sheds the ice accreted on the airfoil surface.Comparedwith an all-thermoelectric systemfor ice protection investigated in the same icingwind tunnel facility using identical test conditions, the hybrid approachwas demonstrated to reduce power consumption up to 91%. Beyond the laboratory tests, numerical simulations of the hybrid strategy analogous to the one used for the experiments are performed. The time history of the residual ice shapes aft of the heated region is simulated using the ice accretion prediction software LEWICE2D for a wet-running anti-icing subsystem. Finite element analyses of the effects of the piezoelectric actuators are then performed using Abaqus to investigate the ice-shedding capability in the unheated regions of the airfoil surface. The numerical results show that the variation in the different ice shapes affects the stiffness of themodel. It becomes obvious that the critical threshold for ice shedding, that is, the stiffness that determineswhether residual ice delaminates fromthe airfoil surface, is affected to aminor extent by the interfacial area and predominantly by the thickness of the ice layer. Further, the simulation results correlate well with experimental results obtained in the icing wind tunnel. It can be concluded that reliable operation of the hybrid system for ice shedding can be guaranteed when using a harmonic sweep excitation able to excite the structure at its resonance.Publicationtype: Conference Paper91