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13th EASN International Conference on Innovation in Aviation and Space...
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13th EASN International Conference on Innovation in Aviation and Space for Opening New Horizons

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

Deadline for manuscript submissions: closed (31 January 2024) | Viewed by 30469

Special Issue Editors

Prof. Dr. Spiros Pantelakis

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Guest Editor
Honorary Chairman of the European Aeronautics Science Network Association (EASN); Professor Emeritus at the University of Patras, Panepistimioupolis Rion, 26500 Patras, Greece
Interests: aeronautical materials and structures; sustainability and circularity in aviation; intelligent design of aircraft structures with regards to sustainability; fatigue of aircraft materials and structures; ageing aircraft; structural integrity; characterization and manufacturing processes of polymers, thermosetting and thermoplastic composites; nanocomposites and nanocrystalline alloys; multifunctional and self-healing materials
Special Issues, Collections and Topics in MDPI journals
Prof. Dr. Andreas Strohmayer

E-Mail Website
Guest Editor
Chairman of the European Aeronautics Science Network Association (EASN), Head of Department Aircraft Design, Institute of Aircraft Design (IFB), University of Stuttgart, Pfaffenwaldring 31, 70569 Stuttgart, Germany
Interests: aircraft design; conventional and unconventional configurations; aircraft systems; operational aspects; certification; electric and hybrid-electric flight; alternative propulsion systems; flight testing; unmanned aerial vehicles; scaled flight testing
Special Issues, Collections and Topics in MDPI journals
Prof. Dr. Liberata Guadagno

E-Mail Website
Guest Editor
Department of Industrial Engineering, University of Salerno, Via Giovanni Paolo II, 132, 84084 Fisciano, SA, Italy
Interests: smart materials; study of the correlations between chemical-physical properties, structure, morphology and durability of macromolecular systems with different types of organizational architectures; design and development of new materials and materials applicable in the field of sensors; carbon–carbon composites (CCCs); thermosetting resins; mechanical properties; supramolecular interactions
Special Issues, Collections and Topics in MDPI journals

Special Issue Information

Dear Colleagues,

This Special Issue is cooperating with the 13th EASN International Conference on "Innovation in Aviation and Space for Opening New Horizons", which will be held by the EASN Association and the University of Salerno, and will take place in Salerno, Italy from the 5th until the 8th of September 2023.

Like its predecessors, the 13th EASN International Conference will include several Plenary Talks by distinguished personalities of the European Aviation and Space sectors from the academia, industry, research community, and policymakers. The event will also give the opportunity to scientists and researchers from all over the world to present their recent achievements in a series of thematic sessions, organized by internationally recognized scientists.

Furthermore, the conference is expected to be a major European Dissemination and Exploitation event of Aviation and Space related research, as it will provide a forum for presenting their activities and achieved goals, discussing current trends and future needs of aviation and space-related research, and trying to identify possible synergies with each other. Additionally, several policy development projects will also find the floor to present the strategic priorities of the European aviation sector.

Authors of outstanding papers related to the topic of aviation and space are invited to submit extended versions of their work to this Special Issue for publication.

We are looking forward to welcoming you to Salerno and the 2023 EASN International Conference and invite submissions of extended conference papers to this Special Issue. We hope that the conference will be another successful, in-person gathering of the EASN Association.

Prof. Dr. Spiros Pantelakis
Prof. Dr. Andreas Strohmayer
Prof. Dr. Liberata Guadagno
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

  • aerostructures: materials, structures, manufacturing
  • Maintenance, Repair and Overhaul (MRO)
  • flight physics
  • UAS and scaled flight testing
  • propulsion
  • hybrid electric flight
  • hydrogen powered aircraft
  • fuels and energy storage
  • small air transport (SAT) technologies
  • avionics, systems and equipment
  • air traffic management and airports
  • human factors
  • innovative concepts and scenarios
  • from Industry 4.0 to Industry 5.0
  • ecoDESIGN and engineering for sustainability
  • space technologies
  • space applications and operations
  • space policies
  • safety, regulation and standards
  • synergies and technology transfer with the automotive industry
  • European policy actions in the field of aviation and space

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Published Papers (15 papers)

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Research

18 pages, 1223 KiB  
Article
An Event-Driven Link-Level Simulator for the Validation of AFDX and Ethernet Avionics Networks
by Pablo Vera-Soto, Javier Villegas, Sergio Fortes, José Pulido, Vicente Escaño, Rafael Ortiz and Raquel Barco
Aerospace 2024, 11(4), 247; https://doi.org/10.3390/aerospace11040247 - 22 Mar 2024
Viewed by 1451
Abstract
Aircraft are composed of many electronic systems: sensors, displays, navigation equipment, and communication elements. These elements require a reliable interconnection, which is a major challenge for communication networks since high reliability and predictability requirements must be verified for safe operation. In addition, their [...] Read more.
Aircraft are composed of many electronic systems: sensors, displays, navigation equipment, and communication elements. These elements require a reliable interconnection, which is a major challenge for communication networks since high reliability and predictability requirements must be verified for safe operation. In addition, their verification via hardware deployments is limited because these are costly and it is difficult to try different architectures and configurations, thus delaying design and development in this area. Therefore, verification at early stages in the design process is of great importance and must be supported with simulation. In this context, this work presents an event-driven link-level framework and simulator for the validation of avionics networks. The tool presented supports communication protocols commonly used in avionics, such as Avionics Full-Duplex Switched Ethernet (AFDX), as well as Ethernet, which is used with static routing. Also, the simulator provides accurate results by employing realistic models for various devices. The proposed platform was evaluated in the Clean Sky’s Disruptive Cockpit for Large Passenger Aircraft architecture scenario, showing the capabilities of the simulator. Verification speed is a key factor in its application, so the computational cost was analyzed, proving that the execution time is linearly dependent on the number of messages sent and that the increase in the number of nodes has few quadratic components. Full article
(This article belongs to the Special Issue 13th EASN International Conference on Innovation in Aviation and Space for Opening New Horizons)
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17 pages, 14367 KiB  
Article
Comparison of Flight Parameters in SIL Simulation Using Commercial Autopilots and X-Plane Simulator for Multi-Rotor Models
by Michal Welcer, Nezar Sahbon and Albert Zajdel
Aerospace 2024, 11(3), 205; https://doi.org/10.3390/aerospace11030205 - 5 Mar 2024
Viewed by 1613
Abstract
Modern aviation technology development heavily relies on computer simulations. SIL (Software-In-The-Loop) simulations are essential for evaluating autopilots and control algorithms for multi-rotors, including drones and other UAVs (Unmanned Aerial Vehicle). In such simulations, it is possible to compare the flight parameters achieved by [...] Read more.
Modern aviation technology development heavily relies on computer simulations. SIL (Software-In-The-Loop) simulations are essential for evaluating autopilots and control algorithms for multi-rotors, including drones and other UAVs (Unmanned Aerial Vehicle). In such simulations, it is possible to compare the flight parameters achieved by flying platforms using various commercial autopilots widely used in the UAV sector. This research aims to provide objective and comprehensive insights into the effectiveness of different autopilot systems This article examines the simulated flight test results of a drone performing the same mission using different autopilot systems. The X-Plane software was used as an environment to simulate the dynamics of the drone and its surroundings. Matlab/Simulink r2023a provided the interface between autopilot software and X-Plane models. Those methods allowed us to obtain an appropriate comparison of the autopilot systems and indicate the main differences between them. This research focused on analyzing UAV flight characteristics such as stability, trajectory tracking, response time to control changes, and the overall effectiveness of autopilots. Various flight scenarios including take-off, landing, flight at a constant altitude, dynamic manoeuvrers and, flight along a planned trajectory were also examined. In order to obtain the most accurate and realistic results, the tests were carried out in various weather conditions. The aim of this research is to provide objective data and analysis to compare the performance of commercial autopilots. This method offers several advantages, including cost-effective testing, the ability to test in diverse environmental conditions, and the evaluation of autopilot algorithms without the need for real hardware. The findings of this study may have a considerable impact on how autopilot designers and developers choose the best platforms and technologies for their projects. Future research on this topic will compare the obtained data with flight test data. Full article
(This article belongs to the Special Issue 13th EASN International Conference on Innovation in Aviation and Space for Opening New Horizons)
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27 pages, 2432 KiB  
Article
Comparison of Two Aerodynamic Models for Projectile Trajectory Simulation
by Nezar Sahbon and Michał Welcer
Aerospace 2024, 11(3), 189; https://doi.org/10.3390/aerospace11030189 - 27 Feb 2024
Cited by 2 | Viewed by 2095
Abstract
The accuracy of aerodynamically controlled guided projectile simulations is largely determined by the aerodynamic model employed in flight simulations which impacts vehicle interaction with the surrounding air. In this work, the performance of projectile path following with two distinct aerodynamic models is examined [...] Read more.
The accuracy of aerodynamically controlled guided projectile simulations is largely determined by the aerodynamic model employed in flight simulations which impacts vehicle interaction with the surrounding air. In this work, the performance of projectile path following with two distinct aerodynamic models is examined for their possible influence on trajectory following accuracy. The study incorporates the path following guidance algorithm, which enables the object to navigate along a predefined path. The simulation mathematical model is developed in the MATLAB/Simulink environment. In addition, by integrating the path-following algorithm with the two aerodynamic models, the dynamic behaviour of the aerodynamically controlled projectile can be compared. This allows for a more comprehensive analysis of the trajectory and the effects of each model on the desired flight path. Further research can explore the differences between the two models in greater detail and quantify their impact on unmanned projectile trajectory predictions, in addition to further exploring the specific characteristics and limitations of each model. This will involve analysing their assumptions, computational methods, and inputs to identify potential sources of error or uncertainty in the simulations. Moreover, these results have important implications for the design of aerodynamically controlled projectiles as well as a deeper understanding of aerodynamic mathematical modelling in flight simulation. Full article
(This article belongs to the Special Issue 13th EASN International Conference on Innovation in Aviation and Space for Opening New Horizons)
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20 pages, 34877 KiB  
Article
Numerical Investigation of an Experimental Setup for Thermoplastic Fuselage Panel Testing in Combined Loading
by Panagiotis D. Kordas, George N. Lampeas and Konstantinos T. Fotopoulos
Aerospace 2024, 11(3), 175; https://doi.org/10.3390/aerospace11030175 - 22 Feb 2024
Viewed by 1293
Abstract
The main purpose of this study comprises the design and the development of a novel experimental configuration for carrying out tests on a full-scale stiffened panel manufactured of fiber-reinforced thermoplastic material. Two different test-bench design concepts were evaluated through a numerical modeling strategy, [...] Read more.
The main purpose of this study comprises the design and the development of a novel experimental configuration for carrying out tests on a full-scale stiffened panel manufactured of fiber-reinforced thermoplastic material. Two different test-bench design concepts were evaluated through a numerical modeling strategy, which will be validated at the next stage using a targeted series of mechanical tests. A baseline experimental setup was developed after a number of candidate configurations were numerically investigated. The supporting elements along with the load introduction systems were defined in such a way as to represent the stiffness of a fuselage barrel section and its representative loading scenarios. The test rig and the investigated thermoplastic panel were numerically simulated to acquire valuable data pertaining to deformations and stresses when subjected to different loading combinations. Two distinct load cases were numerically examined: the first case was the in-plane compression of the thermoplastic panel, while the second case consisted of an internally applied pressure load introduced via an inflatable airbag, installed under the panel. Both loading scenarios were recreated inside the numerical virtual environment in order to examine two distinct stiffening configurations as well as to determine the maximum/limit loads to be used in the planned future experimental campaign. It was concluded that the designed test rig could successfully be used for the structural evaluation of fuselage panels under representative loading conditions. Full article
(This article belongs to the Special Issue 13th EASN International Conference on Innovation in Aviation and Space for Opening New Horizons)
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26 pages, 18984 KiB  
Article
Electric Aircraft Operations: An Interisland Mobility Case Study
by Asteris Apostolidis, Stijn Donckers, Dave Peijnenburg and Konstantinos P. Stamoulis
Aerospace 2024, 11(3), 170; https://doi.org/10.3390/aerospace11030170 - 20 Feb 2024
Cited by 2 | Viewed by 2127
Abstract
This study focuses on the feasibility of electric aircraft operations between the Caribbean islands of Aruba, Bonaire, and Curaçao. It explores the technical characteristics of two different future electric aircraft types (i.e., Alice and ES-19) and compares their operational requirements with those of [...] Read more.
This study focuses on the feasibility of electric aircraft operations between the Caribbean islands of Aruba, Bonaire, and Curaçao. It explores the technical characteristics of two different future electric aircraft types (i.e., Alice and ES-19) and compares their operational requirements with those of three conventional types currently in operation in the region. Flight operations are investigated from the standpoint of battery performance, capacity, and consumption, while their operational viability is verified. In addition, the CO2 emissions of electric operations are calculated based on the present energy mix, revealing moderate improvements. The payload and capacity are also studied, revealing a feasible transition to the new types. The impact of the local climate is discussed for several critical components, while the required legislation for safe operations is explored. Moreover, the maintenance requirements and costs of electric aircraft are explored per component, while charging infrastructure in the hub airport of Aruba is proposed and discussed. Overall, this study offers a thorough overview of the opportunities and challenges that electric aircraft operations can offer within the context of this specific islandic topology. Full article
(This article belongs to the Special Issue 13th EASN International Conference on Innovation in Aviation and Space for Opening New Horizons)
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32 pages, 31805 KiB  
Article
Multi-Physics Digital Model of an Aluminum 2219 Liquid Hydrogen Aircraft Tank
by George Tzoumakis, Konstantinos Fotopoulos and George Lampeas
Aerospace 2024, 11(2), 161; https://doi.org/10.3390/aerospace11020161 - 16 Feb 2024
Cited by 2 | Viewed by 1729
Abstract
Future liquid hydrogen-powered aircraft requires the design and optimization of a large number of systems and subsystems, with cryogenic tanks being one of the largest and most critical. Considering previous space applications, these tanks are usually stiffened by internal members such as stringers, [...] Read more.
Future liquid hydrogen-powered aircraft requires the design and optimization of a large number of systems and subsystems, with cryogenic tanks being one of the largest and most critical. Considering previous space applications, these tanks are usually stiffened by internal members such as stringers, frames, and stiffeners resulting in a complex geometry that leads to an eventual reduction in weight. Cryogenic tanks experience a variety of mechanical and thermal loading conditions and are usually constructed out of several different materials. The complexity of the geometry and the loads highlights the necessity for a computational tool in order to conduct analysis. In this direction, the present work describes the development of a multi-physics finite element digital simulation, conducting heat transfer and structural analysis in a fully parametric manner in order to be able to support the investigation of different design concepts, materials, geometries, etc. The capabilities of the developed model are demonstrated by the design process of an independent-type aluminum 2219 cryogenic tank for commuter aircraft applications. The designed tank indicates a potential maximum take-off weight reduction of about 8% for the commuter category and demonstrates that aluminum alloys are serious candidate materials for future aircraft. Full article
(This article belongs to the Special Issue 13th EASN International Conference on Innovation in Aviation and Space for Opening New Horizons)
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18 pages, 4401 KiB  
Article
Shape Morphing of 4D-Printed Polylactic Acid Structures under Thermal Stimuli: An Experimental and Finite Element Analysis
by Grigorios Kostopoulos, Konstantinos Stamoulis, Vaios Lappas and Stelios K. Georgantzinos
Aerospace 2024, 11(2), 134; https://doi.org/10.3390/aerospace11020134 - 3 Feb 2024
Cited by 1 | Viewed by 2018
Abstract
This study explores the shape-morphing behavior of 4D-printed structures made from Polylactic Acid (PLA), a prominent bio-sourced shape-memory polymer. Focusing on the response of these structures to thermal stimuli, this research investigates how various printing parameters influence their morphing capabilities. The experimental approach [...] Read more.
This study explores the shape-morphing behavior of 4D-printed structures made from Polylactic Acid (PLA), a prominent bio-sourced shape-memory polymer. Focusing on the response of these structures to thermal stimuli, this research investigates how various printing parameters influence their morphing capabilities. The experimental approach integrates design and slicing, printing using fused deposition modeling (FDM), and a post-printing activation phase in a controlled laboratory environment. This process aims to replicate the external stimuli that induce shape morphing, highlighting the dynamic potential of 4D printing. Utilizing Taguchi’s Design of Experiments (DoE), this study examines the effects of printing speed, layer height, layer width, nozzle temperature, bed temperature, and activation temperature on the morphing behavior. The analysis includes precise measurements of deformation parameters, providing a comprehensive understanding of the morphing process. Regression models demonstrate strong correlations with observed data, suggesting their effectiveness in predicting responses based on control parameters. Additionally, finite element analysis (FEA) modeling successfully predicts the performance of these structures, validating its application as a design tool in 4D printing. This research contributes to the understanding of 4D printing dynamics and offers insights for optimizing printing processes to harness the full potential of shape-morphing materials. It sets a foundation for future research, particularly in exploring the relationship between printing parameters and the functional capabilities of 4D-printed structures. Full article
(This article belongs to the Special Issue 13th EASN International Conference on Innovation in Aviation and Space for Opening New Horizons)
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33 pages, 1738 KiB  
Article
A Multidisciplinary Optimization Framework for Ecodesign of Reusable Microsatellite Launchers
by Girolamo Musso, Iara Figueiras, Héléna Goubel, Afonso Gonçalves, Ana Laura Costa, Bruna Ferreira, Lara Azeitona, Simão Barata, Alain Souza, Frederico Afonso, Inês Ribeiro and Fernando Lau
Aerospace 2024, 11(2), 126; https://doi.org/10.3390/aerospace11020126 - 31 Jan 2024
Cited by 2 | Viewed by 2642
Abstract
The commercial space launch sector is currently undergoing a significant shift, with increasing competition and demand for launch services, as well as growing concerns about the environmental impact of rocket launches. To address these challenges, within the New Space Portugal project scope, a [...] Read more.
The commercial space launch sector is currently undergoing a significant shift, with increasing competition and demand for launch services, as well as growing concerns about the environmental impact of rocket launches. To address these challenges, within the New Space Portugal project scope, a multidisciplinary framework for designing and optimizing new launch vehicles is proposed. Creating a more resilient and responsible space industry can be achieved by combining technological innovation and environmental sustainability, as emphasized by the framework. The main scope of the framework was to couple all the disciplines relevant to the space vehicle design in a modular way. Significant emphasis was placed on the infusion of ecodesign principles, including Life Cycle Assessment (LCA) considerations. Optimization techniques were employed to enhance the design and help designers conduct trade-off studies. In general, this multidisciplinary framework aims to provide a comprehensive approach to designing next-generation launch vehicles that meet the demands of a rapidly changing market while also minimizing their environmental impact. A methodology that leverages the strengths of both genetic and gradient-based algorithms is employed for optimizations with the objectives of maximizing the apogee altitude and minimizing the Global Warming Potential (GWP). Despite only being tested at the moment for sounding rockets, the framework has demonstrated promising results. It has illuminated the potential of this approach, leading to the identification of three optimal designs: one for maximizing the apogee, another for minimizing GWP, and a compromise design that strikes a balance between the two objectives. The outcomes yielded a maximum apogee of 6.41 km, a minimum GWP of 9.06 kg CO2eq, and a balanced compromise design featuring an apogee of 5.75 km and a GWP of 25.64 kg CO2eq. Full article
(This article belongs to the Special Issue 13th EASN International Conference on Innovation in Aviation and Space for Opening New Horizons)
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26 pages, 3423 KiB  
Article
Conceptual Design of a Hydrogen-Hybrid Dual-Fuel Regional Aircraft Retrofit
by Ulrich Carsten Johannes Rischmüller, Alexandros Lessis, Patrick Egerer and Mirko Hornung
Aerospace 2024, 11(2), 123; https://doi.org/10.3390/aerospace11020123 - 31 Jan 2024
Cited by 2 | Viewed by 2888
Abstract
A wide range of aircraft propulsion technologies is being investigated in current research to reduce the environmental impact of commercial aviation. As the implementation of purely hydrogen-powered aircraft may encounter various challenges on the airport and vehicle side, combined hydrogen and kerosene energy [...] Read more.
A wide range of aircraft propulsion technologies is being investigated in current research to reduce the environmental impact of commercial aviation. As the implementation of purely hydrogen-powered aircraft may encounter various challenges on the airport and vehicle side, combined hydrogen and kerosene energy sources may act as an enabler for the first operations with liquid hydrogen propulsion technologies. The presented studies describe the conceptual design of such a dual-fuel regional aircraft featuring a retrofit derived from the D328eco under development by Deutsche Aircraft. By electrically assisting the sustainable aviation fuel (SAF) burning conventional turboprop engines with the power of high-temperature polymer-electrolyte fuel cells, the powertrain architecture enables a reduction of SAF consumption. All aircraft were modeled and investigated using the Bauhaus Luftfahrt Aircraft Design Environment. A description of this design platform and the incorporated methods to model the hydrogen-hybrid powertrain is given. Special emphasis was laid on the implications of the hydrogen and SAF dual-fuel system design to be able to assess the potential benefits and drawbacks of various configurations with the required level of detail. Retrofit assumptions were applied, particularly retaining the maximum takeoff mass while reducing payload to account for the propulsion system mass increase. A fuel cell power allocation of 20% led to a substantial 12.9% SAF consumption decrease. Nonetheless, this enhancement necessitated an 18.1% payload reduction, accompanied by a 34.5% increment in propulsion system mass. Various additional studies were performed to assess the influence of the power split. Under the given assumptions, the design of such a retrofit was deemed viable. Full article
(This article belongs to the Special Issue 13th EASN International Conference on Innovation in Aviation and Space for Opening New Horizons)
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20 pages, 3336 KiB  
Article
Sustainability-Driven Design of Aircraft Composite Components
by Angelos Filippatos, Dionysios Markatos, Georgios Tzortzinis, Kaushik Abhyankar, Sonia Malefaki, Maik Gude and Spiros Pantelakis
Aerospace 2024, 11(1), 86; https://doi.org/10.3390/aerospace11010086 - 18 Jan 2024
Cited by 2 | Viewed by 2131
Abstract
The current prevailing trend in design across key sectors prioritizes eco-design, emphasizing considerations of environmental aspects in the design process. The present work aims to take a significant leap forward by proposing a design process where sustainability serves as the primary driving force. [...] Read more.
The current prevailing trend in design across key sectors prioritizes eco-design, emphasizing considerations of environmental aspects in the design process. The present work aims to take a significant leap forward by proposing a design process where sustainability serves as the primary driving force. In this context, sustainability is positioned as a fundamental component to be integrated into the initial stages of design, introducing innovative multidisciplinary criteria that redefine the design paradigm. Within this framework, sustainability is characterized using a comprehensive and quantifiable index encompassing technological, environmental, economic, and circular economy dimensions. To demonstrate the practical application of sustainability as the primary criterion in designing mechanical components, a parametrized finite element model of a composite plate is utilized, integrating both pristine and recycled fibers. Subsequently, a demonstrator derived from the aviation industry—specifically, a hat stiffener—is employed as a validation platform for the proposed methodology, ensuring alignment with the demonstrator’s specific requirements. Various representative trade-off scenarios are implemented to guide engineers’ decision-making during the conceptual design phase. Additionally, the robustness of the aforementioned methodology is thoroughly assessed concerning changes in the priority assigned to each sustainability criterion and its sensitivity to variations in the initial data. The significance of the proposed design methodology lies in its effectiveness in addressing the complex challenges presented by conflicting sustainability objectives. Furthermore, its adaptability positions it for potential application across various sectors, offering a transformative approach to sustainable engineering practices. Full article
(This article belongs to the Special Issue 13th EASN International Conference on Innovation in Aviation and Space for Opening New Horizons)
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14 pages, 2539 KiB  
Article
Investigation into the Effect of H2-Enriched Conditions on the Structure and Stability of Flames in a Low-Swirl Combustor Derived from Aero-Engine Design
by Sara Bonuso, Pasquale Di Gloria, Guido Marseglia, Ramón A. Otón Martínez, Ghazanfar Mehdi, Zubair Ali Shah, Antonio Ficarella and Maria Grazia De Giorgi
Aerospace 2024, 11(1), 43; https://doi.org/10.3390/aerospace11010043 - 30 Dec 2023
Viewed by 1587
Abstract
This study introduces an innovative approach involving the injection of hydrogen into a low-swirl, non-premixed flame, which operates with gaseous fuels derived from an air-blast atomizer designed for aero-engine applications. The aim is to characterize how hydrogen enrichment influences flame structures while maintaining [...] Read more.
This study introduces an innovative approach involving the injection of hydrogen into a low-swirl, non-premixed flame, which operates with gaseous fuels derived from an air-blast atomizer designed for aero-engine applications. The aim is to characterize how hydrogen enrichment influences flame structures while maintaining a constant thermal output of 4.6 kW. Using high-speed chemiluminescence imaging, three fueling conditions were compared: the first involved pure methane/air, while the second and third conditions introduced varying levels of hydrogen to an air–methane mixture. The results reveal significant effects of hydrogen enrichment on flame characteristics, including a slightly shorter length and a wider angle attributed to heightened expansion within the Combustion Recirculation Zone. Moreover, the emission of UV light underwent considerable changes, resulting in a shifted luminosity zone and reduced variance. To delve deeper into the underlying mechanisms, the researchers employed Proper Orthogonal Decomposition (POD) and Spectral Proper Orthogonal Decomposition (SPOD) analyses, showing coherent structures and energetic modes within the flames. Hydrogen enrichment led to the development of smaller structures near the nozzle exit, accompanied by longitudinal oscillations and vortex shedding phenomena. These findings contribute to an advanced understanding of hydrogen’s impact on flame characteristics, thereby propelling efforts toward improved flame stability. Additionally, these insights hold significance in the exploration of hydrogen as an alternative energy source with potential environmental benefits. Full article
(This article belongs to the Special Issue 13th EASN International Conference on Innovation in Aviation and Space for Opening New Horizons)
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28 pages, 3575 KiB  
Article
From Raw Data to Practical Application: EEG Parameters for Human Performance Studies in Air Traffic Control
by María Zamarreño Suárez, Juan Marín Martínez, Francisco Pérez Moreno, Raquel Delgado-Aguilera Jurado, Patricia María López de Frutos and Rosa María Arnaldo Valdés
Aerospace 2024, 11(1), 30; https://doi.org/10.3390/aerospace11010030 - 28 Dec 2023
Viewed by 1564
Abstract
The use of electroencephalography (EEG) techniques has many advantages in the study of human performance in air traffic control (ATC). At present, these are non-intrusive techniques that allow large volumes of data to be recorded on a continuous basis using wireless equipment. To [...] Read more.
The use of electroencephalography (EEG) techniques has many advantages in the study of human performance in air traffic control (ATC). At present, these are non-intrusive techniques that allow large volumes of data to be recorded on a continuous basis using wireless equipment. To achieve the most with these techniques, it is essential to establish appropriate EEG parameters with a clear understanding of the process followed to obtain them and their practical application. This study explains, step by step, the approach adopted to obtain six EEG parameters: excitement, stress, boredom, relaxation, engagement, and attention. It then explains all the steps involved in analysing the relationship between these parameters and two other parameters that characterise the state of the air traffic control sector during the development of real-time simulations (RTS): taskload and number of simultaneous aircraft. For this case study, the results showed the highest relationships for the engagement and attention parameters. In general, the results confirmed the potential of using these EEG parameters. Full article
(This article belongs to the Special Issue 13th EASN International Conference on Innovation in Aviation and Space for Opening New Horizons)
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15 pages, 5310 KiB  
Article
Toward Zero Carbon Emissions: Investigating the Combustion Performance of Shaped Microcombustors Using H2/Air and NH3/Air Mixtures
by Giacomo Cinieri, Zubair Ali Shah, Guido Marseglia and Maria Grazia De Giorgi
Aerospace 2024, 11(1), 12; https://doi.org/10.3390/aerospace11010012 - 22 Dec 2023
Cited by 4 | Viewed by 1309
Abstract
The research effort in the microcombustor field has recently increased due to the demand for high-performance systems in microelectromechanical and micro power generation devices. To address rising concerns about pollutants from fossil sources, zero-carbon fuels such as hydrogen (H2) and ammonia [...] Read more.
The research effort in the microcombustor field has recently increased due to the demand for high-performance systems in microelectromechanical and micro power generation devices. To address rising concerns about pollutants from fossil sources, zero-carbon fuels such as hydrogen (H2) and ammonia (NH3) have been considered as an alternative in microcombustion processes. In a microcombustor, the surface area-to-volume ratio is much higher compared to conventional combustion systems, resulting in faster heat transfer rates and more intense combustion reactions. However, achieving efficient mixing of fuel and an oxidizer in a microcombustor can be challenging due to its small size, particularly for highly reactive fuels like H2. For NH3, challenges in microcombustion involve a low reactive, high ignition temperature (923 K vs. 793 K of H2) and high concentration of NOx combustion products. Therefore, studying the performance of these fuels in microcombustors is important for developing clean energy technologies. In this paper, to explore features of non-premixed NH3/air and H2/air combustion in micro-scale combustors, an Ansys Fluent numerical investigation was conducted on a Y-shaped microcombustor. Results show that for combustion with H2, stationary flames can be achieved even at lower equivalence ratios. Additionally, the pollutants generated from H2 in the flame are generally twice those of NH3. The overall efficiency of the microcombustor is two times greater for NH3 conditions than for H2 conditions. Full article
(This article belongs to the Special Issue 13th EASN International Conference on Innovation in Aviation and Space for Opening New Horizons)
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13 pages, 2577 KiB  
Article
The Impact of Data Injection on Predictive Algorithm Developed within Electrical Manufacturing Engineering in the Context of Aerospace Cybersecurity
by Jorge Bautista-Hernández and María Ángeles Martín-Prats
Aerospace 2023, 10(12), 984; https://doi.org/10.3390/aerospace10120984 - 23 Nov 2023
Cited by 1 | Viewed by 1406
Abstract
Cybersecurity plays a relevant role in the new digital age within the aerospace industry. Predictive algorithms are necessary to interconnect complex systems within the cyberspace. In this context, where security protocols do not apply, challenges to maintain data privacy and security arise for [...] Read more.
Cybersecurity plays a relevant role in the new digital age within the aerospace industry. Predictive algorithms are necessary to interconnect complex systems within the cyberspace. In this context, where security protocols do not apply, challenges to maintain data privacy and security arise for the organizations. Thus, the need for cybersecurity is required. The four main categories to classify threats are interruption, fabrication, modification, and interception. They all share a common thing, which is to soften the three pillars that cybersecurity needs to guarantee. These pillars are confidentiality, availability, and integrity of data (CIA). Data injection can contribute to this event by the creation of false indicators, which can lead to error creation during the manufacturing engineering processes. In this paper, the impact of data injection on the existing dataset used in manufacturing processes is described. The design model synchronizes the following mechanisms developed within machine learning techniques, which are the risk matrix indicator to assess the probability of producing an error, the dendrogram to cluster the dataset in groups with similarities, the logistic regression to predict the potential outcomes, and the confusion matrix to analyze the performance of the algorithm. The results presented in this study, which were carried out using a real dataset related to the electrical harnesses installed in a C295 military aircraft, estimate that injection of false data indicators increases the probability of creating an error by 24.22% based on the predicted outcomes required for the generation of the manufacturing processes. Overall, implementing cybersecurity measures and advanced methodologies to detect and prevent cyberattacks is necessary. Full article
(This article belongs to the Special Issue 13th EASN International Conference on Innovation in Aviation and Space for Opening New Horizons)
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17 pages, 6721 KiB  
Article
Study on the Transition to True North in Air Navigation
by Octavian Thor Pleter and Cristian Emil Constantinescu
Aerospace 2023, 10(11), 912; https://doi.org/10.3390/aerospace10110912 - 25 Oct 2023
Cited by 2 | Viewed by 2348
Abstract
The paper is an introductory study on the possible transition from Magnetic North reference to True North reference in air navigation, as envisaged by the International Association of Institutes of Navigation’s AHRTAG Group. The use of the Magnetic Field of the Earth as [...] Read more.
The paper is an introductory study on the possible transition from Magnetic North reference to True North reference in air navigation, as envisaged by the International Association of Institutes of Navigation’s AHRTAG Group. The use of the Magnetic Field of the Earth as a direction reference in aviation is explained briefly. Magnetic North is an unstable and irregular directional reference that aviation manages well, but with significant costs. The unpredictability and uncertainties of the Magnetic Field of the Earth might be critical in the future, especially in the case of reversal of the magnetic poles, or incipient reversal. The paper puts forward the case for calculating the probability of such a catastrophic event, with a view to engaging further expert research in the geomagnetic phenomena. The purpose of such a probability estimate would be for the aviation decision makers to determine whether contingency planning might be required or not. Furthermore, the paper analyses the adoption of True North in maritime navigation as a possible model. Full article
(This article belongs to the Special Issue 13th EASN International Conference on Innovation in Aviation and Space for Opening New Horizons)
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