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Aerospace
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Revolutionizing Aerospace Mobility: Green Hydrogen As the Sustainable Fuel of...
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Revolutionizing Aerospace Mobility: Green Hydrogen As the Sustainable Fuel of the Future

A special issue of Aerospace (ISSN 2226-4310).

Deadline for manuscript submissions: 28 February 2025 | Viewed by 7156

Special Issue Editors

Dr. Giacomo Silvagni

E-Mail Website
Guest Editor
Department of Industrial Engineering, University of Bologna, 47121 Forli, Italy
Interests: internal combustion engines; low tempearture combustions; sustainable aeronautical and space propulsion systems; rapid control prototyping; sustainable mobility; hydrogen based-solutions for aeronautics; sustainable hydrogen-based energy plants
Special Issues, Collections and Topics in MDPI journals
Prof. Dr. Vittorio Ravaglioli

E-Mail Website
Guest Editor
Department of Industrial Engineering, University of Bologna, 47121 Forli, Italy
Interests: internal combustion engines; combustion control; testing; hybrid systems; hydrogen combustion
Special Issues, Collections and Topics in MDPI journals

Special Issue Information

Dear Colleagues,

Green hydrogen, produced through renewable energy sources, offers a promising alternative to traditional fossil fuels for propulsion systems in the aerospace mobility sector. Thanks to the chemical composition of the fuel itself, hydrogen holds the key to achieving the ambitious environmental targets of moving toward zero-carbon air mobility and mitigating the impact of aviation on climate change. By embracing green hydrogen technologies, aerospace industry stakeholders can pave the way for a cleaner and sustainable future for air travel and space exploration. From fuel cell technologies to optimized conventional propulsion systems, the integration of green hydrogen in aerospace not only promises enhanced efficiency and performance but also contributes to global efforts in sustainability and environmental stewardship. This Special Issue aims to explore the transformative potential of green hydrogen as a sustainable fuel for both aviation and the space transportation sector. The scope of the Special Issue encompasses a wide range of topics, including the production and distribution of green hydrogen, innovation in hydrogen storage technologies, advances in hydrogen fuel cell technology for propulsion and power generation, the management of high-power-to-weight-ratio renewable-fueled propulsion systems, the optimization and design of hydrogen propulsion systems, the environmental impact assessment of hydrogen technology, policy and regulatory aspects, and case studies on its applications in aerospace mobility.

The scope of the Special Issue will include, but is not limited to, the following topics:

  • An overview of green hydrogen technologies for aerospace mobility, encompassing both aviation and space segment.
  • Advances in hydrogen fuel cell technology and materials for aerospace applications.
  • The optimization and design of green hydrogen propulsion systems for aerospace applications.
  • Comparisons of experimental data and case studies on the use of green hydrogen propulsion systems.
  • The management of high power-to-weight ratio renewable-fueled propulsion systems.
  • The integration of green hydrogen propulsion systems with aircraft and subsystems.
  • The environmental impact assessment of green hydrogen propulsion in the atmosphere and in commercial space missions, including emission reduction and planetary protection.
  • The production, storage, and distribution of green hydrogen for air and space applications.
  • The policy, regulatory, and economic aspects of green hydrogen adoption in the aerospace industry.
  • Case studies and demonstrations of green hydrogen applications in aerospace mobility, including both the aviation and commercial space markets. 

We welcome original research articles and review articles that address any of the above topics or related areas. We look forward to receiving high-quality submissions that contribute to the advancement of the field of green hydrogen technologies and sustainable aerospace mobility.

Dr. Giacomo Silvagni
Dr. Vittorio Ravaglioli
Guest Editors

Manuscript Submission Information

Manuscripts should be submitted online at www.mdpi.com by registering and logging in to this website. Once you are registered, click here to go to the submission form. Manuscripts can be submitted until the deadline. All submissions that pass pre-check are peer-reviewed. Accepted papers will be published continuously in the journal (as soon as accepted) and will be listed together on the special issue website. Research articles, review articles as well as short communications are invited. For planned papers, a title and short abstract (about 100 words) can be sent to the Editorial Office for announcement on this website.

Submitted manuscripts should not have been published previously, nor be under consideration for publication elsewhere (except conference proceedings papers). All manuscripts are thoroughly refereed through a single-blind peer-review process. A guide for authors and other relevant information for submission of manuscripts is available on the Instructions for Authors page. Aerospace is an international peer-reviewed open access monthly journal published by MDPI.

Please visit the Instructions for Authors page before submitting a manuscript. The Article Processing Charge (APC) for publication in this open access journal is 2400 CHF (Swiss Francs). Submitted papers should be well formatted and use good English. Authors may use MDPI's English editing service prior to publication or during author revisions.

Keywords

  • green hydrogen
  • aerospace mobility
  • sustainable fuel
  • aviation
  • space
  • hydrogen fuel cell
  • propulsion systems
  • environmental impact
  • production and distribution
  • policy and regulation

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Published Papers (4 papers)

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Research

26 pages, 5286 KiB  
Article
0-D Dynamic Performance Simulation of Hydrogen-Fueled Turboshaft Engine
by Mattia Magnani, Giacomo Silvagni, Vittorio Ravaglioli and Fabrizio Ponti
Aerospace 2024, 11(10), 816; https://doi.org/10.3390/aerospace11100816 - 6 Oct 2024
Viewed by 852
Abstract
In the last few decades, the problem of pollution resulting from human activities has pushed research toward zero or net-zero carbon solutions for transportation. The main objective of this paper is to perform a preliminary performance assessment of the use of hydrogen in [...] Read more.
In the last few decades, the problem of pollution resulting from human activities has pushed research toward zero or net-zero carbon solutions for transportation. The main objective of this paper is to perform a preliminary performance assessment of the use of hydrogen in conventional turbine engines for aeronautical applications. A 0-D dynamic model of the Allison 250 C-18 turboshaft engine was designed and validated using conventional aviation fuel (kerosene Jet A-1). A dedicated, experimental campaign covering the whole engine operating range was conducted to obtain the thermodynamic data for the main engine components: the compressor, lateral ducts, combustion chamber, high- and low-pressure turbines, and exhaust nozzle. A theoretical chemical combustion model based on the NASA-CEA database was used to account for the energy conversion process in the combustor and to obtain quantitative feedback from the model in terms of fuel consumption. Once the engine and the turbomachinery of the engine were characterized, the work focused on designing a 0-D dynamic engine model based on the engine’s characteristics and the experimental data using the MATLAB/Simulink environment, which is capable of replicating the real engine behavior. Then, the 0-D dynamic model was validated by the acquired data and used to predict the engine’s performance with a different throttle profile (close to realistic request profiles during flight). Finally, the 0-D dynamic engine model was used to predict the performance of the engine using hydrogen as the input of the theoretical combustion model. The outputs of simulations running conventional kerosene Jet A-1 and hydrogen using different throttle profiles were compared, showing up to a 64% reduction in fuel mass flow rate and a 3% increase in thermal efficiency using hydrogen in flight-like conditions. The results confirm the potential of hydrogen as a suitable alternative fuel for small turbine engines and aircraft. Full article
(This article belongs to the Special Issue Revolutionizing Aerospace Mobility: Green Hydrogen As the Sustainable Fuel of the Future)
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31 pages, 25814 KiB  
Article
Experimental Pressure Gain Analysis of Pulsed Detonation Engine
by Alina Bogoi, Tudor Cuciuc, Andrei Vlad Cojocea, Mihnea Gall, Ionuț Porumbel and Constantin Eusebiu Hrițcu
Aerospace 2024, 11(6), 465; https://doi.org/10.3390/aerospace11060465 - 11 Jun 2024
Cited by 2 | Viewed by 1126
Abstract
A pulsed detonation chamber (PDC) equipped with Hartmann–Sprenger resonators has been designed and tested for both Hydrogen/air and Hydrogen/Oxygen mixtures. A full-factorial experimental campaign employing four factors with four levels each has been carried out for both mixtures. Instantaneous static pressure has been [...] Read more.
A pulsed detonation chamber (PDC) equipped with Hartmann–Sprenger resonators has been designed and tested for both Hydrogen/air and Hydrogen/Oxygen mixtures. A full-factorial experimental campaign employing four factors with four levels each has been carried out for both mixtures. Instantaneous static pressure has been measured at two locations on the exhaust pipe of the PDC, and the signal has been processed to extract the average and maximum cycle pressures and the operating frequency of the spark plug. The PDC has been shown to be able to reach sustained detonation cycles over a length below 200 mm, measured from the spark plug to the first pressure sensor. The optimal regimes for both air and Oxygen operation have been determined, and the influence of the four factors on the responses is discussed. Full article
(This article belongs to the Special Issue Revolutionizing Aerospace Mobility: Green Hydrogen As the Sustainable Fuel of the Future)
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21 pages, 7552 KiB  
Article
Studies Concerning Electrical Repowering of a Training Airplane Using Hydrogen Fuel Cells
by Jenica-Ileana Corcau, Liviu Dinca, Grigore Cican, Adriana Ionescu, Mihai Negru, Radu Bogateanu and Andra-Adelina Cucu
Aerospace 2024, 11(3), 218; https://doi.org/10.3390/aerospace11030218 - 11 Mar 2024
Viewed by 1921
Abstract
The increase in greenhouse gas emissions, as well as the risk of fossil fuel depletion, has prompted a transition to electric transportation. The European Union aims to substantially reduce pollutant emissions by 2035 through the use of renewable energies. In aviation, this transition [...] Read more.
The increase in greenhouse gas emissions, as well as the risk of fossil fuel depletion, has prompted a transition to electric transportation. The European Union aims to substantially reduce pollutant emissions by 2035 through the use of renewable energies. In aviation, this transition is particularly challenging, mainly due to the weight of onboard equipment. Traditional electric motors with radial magnetic flux have been replaced by axial magnetic flux motors with reduced weight and volume, high efficiency, power, and torque. These motors were initially developed for electric vehicles with in-wheel motors but have been adapted for aviation without modifications. Worldwide, there are already companies developing propulsion systems for various aircraft categories using such electric motors. One category of aircraft that could benefit from this electric motor development is traditionally constructed training aircraft with significant remaining flight resource. Electric repowering would allow their continued use for pilot training, preparing them for future electrically powered aircraft. This article presents a study on the feasibility of repowering a classic training aircraft with an electric propulsion system. The possibilities of using either a battery or a hybrid source composed of a battery and a fuel cell as an energy source are explored. The goal is to utilize components already in production to eliminate the research phase for specific aircraft components. Full article
(This article belongs to the Special Issue Revolutionizing Aerospace Mobility: Green Hydrogen As the Sustainable Fuel of the Future)
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25 pages, 8491 KiB  
Article
Design of a Hydrogen Aircraft for Zero Persistent Contrails
by David I. Barton, Cesare A. Hall and Matthew K. Oldfield
Aerospace 2023, 10(8), 688; https://doi.org/10.3390/aerospace10080688 - 31 Jul 2023
Cited by 6 | Viewed by 2509
Abstract
Contrails are responsible for a significant proportion of aviation’s climate impact. This paper uses data from the European Centre for Medium-Range Weather Forecasts to identify the altitudes and latitudes where formed contrails will not persist. This reveals that long-lived contrails may be prevented [...] Read more.
Contrails are responsible for a significant proportion of aviation’s climate impact. This paper uses data from the European Centre for Medium-Range Weather Forecasts to identify the altitudes and latitudes where formed contrails will not persist. This reveals that long-lived contrails may be prevented by flying lower in equatorial regions and higher in non-equatorial regions. Subsequently, it is found that the lighter fuel and reduced seating capacity of hydrogen-powered aircraft lead to a reduced aircraft weight, which increases the optimal operating altitude by about 2 km. In non-equatorial regions, this would lift the aircraft’s cruise point into the region where long-lived contrails do not persist, unlocking hydrogen-powered, low-contrails operation. The baseline aircraft considered is an A320 retrofitted with in-fuselage hydrogen tanks. The impacts of the higher-altitude cruise on fuel burn and the benefits unlocked by optimizing the wing geometry for this altitude are estimated using a drag model based on theory proposed by Cavcar, Lock, and Mason, and verified against existing aircraft. The weight penalty associated with optimizing wing geometry for this altitude is estimated using Torenbeek’s correlation. It is found that thinner wings with higher aspect ratios are particularly suited to this high-altitude operation and are enabled by the relaxation of the requirement to store fuel in the wings. An example aircraft design for the non-equatorial region is provided, which cruises at a 14 km altitude at Mach 0.75 with a less than 1% average probability of generating long-lived contrails when operating at latitudes more than 35° from the equator. Compared to the A320, this concept design is estimated to have a 20% greater cruise lift–drag ratio, due to the 33% thinner wings with a 50% larger aspect ratio, enabling just 5% more energy use per passenger-km, despite fitting 40% fewer seats. Full article
(This article belongs to the Special Issue Revolutionizing Aerospace Mobility: Green Hydrogen As the Sustainable Fuel of the Future)
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