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Di Vito, Vittorio; Dziugiel, Bartosz; Melo, Sandra; Ten Thije, Jens T.; Duca, Gabriella; Liberacki, Adam; Hesselink, Henk; Giannuzzi, Michele; Menichino, Aniello; Montaquila, Roberto Valentino; Cerasuolo, Giovanni; Witkowska-Konieczny, Adriana
2025 Aircraft Engineering and Aerospace Technology: An International Journal
doi: 10.1108/aeat-03-2024-0081
Urban air mobility (UAM) development and deployment into future cities is gaining increasing and relevant interest in the past years. This study, a conceptual paper, aims to report the high-level description of the most relevant UAM application use cases (UCs) emerging from the research activities carried out in the ASSURED UAM project.Design/methodology/approachThe UAM application UCs have been obtained from the ASSURED UAM project dedicated activities that have been carried out to, first, develop suitable operational concepts for UAM deployment in the next decades and, then, to further refine and design the most relevant UCs for UAM deployment in the next decades, leading to the public issue of dedicated overall document.FindingsThe ASSURED UAM UCs for UAM deployment in the next decades encompass both public (point-to-point, point-to-everywhere, direct medical transport of people) and private (direct last-mile delivery, advanced last-mile delivery, automatic personal aerial transportation) services applications, evolving in incremental way over time according to three considered time horizons (2025, 2030 and 2035), toward progressive integration into metropolitan transport system.Originality/valueThis paper provides final outline of the ASSURED UAM UCs, starting from the analysis of overall identified possible UAM applications, focusing on the description of the six main UCs considered as relevant for the application under the wider societal benefits point of view. The UCs are described in terms of expected operational environment, needed technological enablers and envisaged regulatory implications.
Grzybowski, Piotr; Ziółkowski, Kamil
2025 Aircraft Engineering and Aerospace Technology: An International Journal
doi: 10.1108/aeat-03-2024-0089
The purpose of this paper is to present research on the flight demonstration of avionics technology for CS-23 commuter category aircraft. The Integrated Mission Management System (IMMS) is designed to reduce pilot workload by aggregating hazard information from multiple domains (airspace, traffic, weather and terrain) and automatically prefiltering this data to display only hazards relevant to the flight plan, from origin to destination. This paper details the design of the IMMS, along with the process of the integration on aircraft and flight demonstration results.Design/methodology/approachThe IMMS integrates several technologies, including the Advanced Weather Awareness System, Tactical Separation System, Compact Computing Platform and Flight Reconfiguration System. Hazards are consolidated in a Unified Hazard Database (UHD) and assigned severity levels, providing automated hazard filtering and path planning.FindingsSimulations and flight tests demonstrated that the IMMS effectively reduces the information displayed to pilots in real-time without loss of critical safety data. Feedbacks from test pilots on IMMS usage, as well as suggestions for improving the multi-source Graphical User Interface, are also discussed.Research limitations/implicationsLimitations of the UHD were identified, offering insights into potential expansions to support more efficient automatic flight planning. The technology was validated through extensive laboratory testing and real-world flight trials, achieving Technology Readiness Level 5. This validation demonstrated how the severity of hazards can be linked to their transparency level on the display, with the aim of reducing information overload.Practical implicationsThe IMMS shows potential to be ground-breaking system in the CS-23 aircraft category, autonomously supporting route planning and flight execution while adapting to in-flight weather changes and ensuring tactical separation from other aircraft. It also shows that multi-domain hazard information can be processed on limited on-board avionics systems.Originality/valueThis study highlights the importance of Hardware-In-The-Loop testing in verifying new technologies and mitigating risks related to software reliability, flight demonstrations and system integration.
Szpakowska-Peas, Ewelina; Filipowicz, Maciej
2025 Aircraft Engineering and Aerospace Technology: An International Journal
doi: 10.1108/aeat-03-2024-0083
The purpose of this paper is to discuss the importance of testing avionics systems during the development phase according to standard procedures outlined in documents such as RTCA DO-160G. Specifically, it focuses on the necessity of correctly designing electronic devices to successfully pass tests for environmental conditions.Design/methodology/approachDuring the development of the flight reconfiguration system (FRS) within the Clean Sky 2/Clean Aviation cost optimized avionics System (COAST) project, this paper applied solutions for input power protection in electronic design. The methods discussed are aimed at protecting circuits from input power disturbances following Sections 16 and 17 of DO-160G. The approach includes both computer simulations and laboratory testing to analyze the effectiveness of the applied methods.FindingsThe paper presents the findings of the applied methods for input power protection in the electronic design of the FRS. Through computer simulations and laboratory tests, it was observed that the developed electronic eqty -35uipment worked correctly after completing environmental and input power testing. The achieved results indicate that the applied methods of circuits’ protection ensured proper functionality.Practical implicationsThe findings of this study have practical implications for the design and development of airborne electronic equipment. By adhering to standard procedures outlined in DO-160G and implementing appropriate input power protection methods, electronic devices can reliably operate in harsh environmental conditions encountered during aircraft operations.Originality/valueThis paper contributes to the field by presenting practical solutions for input power protection in electronic design, specifically within the context of the FRS by discussing methods of circuits’ protection in accordance with DO-160G and providing analysis of computer simulations and laboratory test results, this paper offers valuable insights into ensuring the proper functionality of avionic equipment in challenging environmental conditions.
Kocjan, Jakub; Rogólski, Robert
2025 Aircraft Engineering and Aerospace Technology: An International Journal
doi: 10.1108/aeat-03-2024-0084
Modern warfare and modern battlefield are very demanding. The recent conflicts showed that the usage of the helicopters is very limited and only the best constructions are able to provide support for the operations. The purpose of this research is to show the possibilities of new design tool for main rotor aerostructural optimization. It is a next chapter of the research that is aimed at finding new solutions for rotorcraft constructions.Design/methodology/approachThis work presents a method of preliminary structure optimization of the main rotor blade using parametric modeling. It is the next step in the main rotor optimization studies. It is the next step after preparing the parametric model for the external shape CFD analysis. As a basis for parametric blade structure calculations, the analytical model is provided in this paper. The equations of rigid blade loads and, as a consequence of the strength elements, stresses are shown. The parametric blade modeling is conducted using the Graphic Integrated Programming language. The parametric design method is shown to be used for various blade planform models and different section airfoils. The structure of a blade is generated automatically after the user enters the parameters. The code-inbuilt analysis systems provide a quick inertia examination of the generated geometry, which is the basis for further optimization. The program calculates the blade loads and verifies them with the given material conditions and proposed safety factors. In the analysis, composite materials for the strength elements were proposed.FindingsThe results of this research showed the application of parametrization into the main rotor blade design loop. It was presented that the main rotor blade structure can be enhanced using fluid-structure interaction (FSI) methods. The time saving with the implementation the process into design loop is shown.Practical implicationsThis work can be practically used in the main rotor blade design process. It provides the possibilities to check various blade aerodynamic configuration in a structure strength aspect.Originality/valueTo the best of the authors’ knowledge, there were no published research that combines the main rotor FSI analysis. The method, which is presented in the work, provides a new approach to a rotorcraft design. The application of the parametrization and combining it with the FSI method gives a novel solution for helicopters construction enhancement.
Drupka, Grzegorz; Grzybowski, Piotr; Szczerba, Piotr; Bichajło, Lesław
2025 Aircraft Engineering and Aerospace Technology: An International Journal
doi: 10.1108/aeat-03-2024-0085
This paper aims to present research carried out on the influence of GUI graphical elements design for an integrated mission management system (IMMS) display flight planning process.Design/methodology/approachSurveys and research were conducted among students/pilots to explore graphic presentation methods for flight planning displays. Guidelines for graphical layout of the IMMS flight planning interface are proposed.FindingsA research concept was obtained, enabling GUI tests for IMMS using prepared templates and questionnaires.Practical implicationsThis study improves cockpit information readability, understanding and presentation, particularly for flight planning elements such as terrain, weather, traffic and zones influencing route organisation.Social implicationsThis study targets possible improvements to the flight path planning process in aviation, inducing a reduction in errors related to human factors while processing the visual data on-board.Originality/valueThe study verified the impact of drawing and rendering methods on IMMS flight planning, suggesting that current display methods may be error-prone when showing hazard information from multiple sources on a single screen.
Zajdel, Albert; Szczepański, Cezary; Filipowicz, Maciej; Krawczyk, Mariusz; Welcer, Michal
2025 Aircraft Engineering and Aerospace Technology: An International Journal
doi: 10.1108/aeat-03-2024-0086
The paper presents the results of the final phase of the project, namely flight tests, aimed at developing a stabilisation system utilizing trim tabs for the PZL-130 Orlik turboprop military trainer aircraft.Design/methodology/approachThe proposed flight stabilisation system was developed using modern techniques of model-based design, automatic code generation and software and hardware-in-the-loop testing. The project progressed to the flight testing stage, enabling the assessment of the control system’s quality and its final calibration.FindingsAnalysis of the results obtained during flight tests confirmed the high quality of the stabilisation system. Specifically, the anticipated accuracy of both longitudinal and lateral channel stabilisation was achieved.Originality/valueThe proposed flight stabilisation system, utilizing trim tabs, offers several advantages over classic automatic flight systems in terms of weight, energy consumption, structural simplicity and obviates the need for primary control modifications on the aircraft. It was developed using modern techniques of model-based design, automatic code generation and hardware-in-the-loop simulations.
Dziugiel, Bartosz; Liberacki, Adam; Di Vito, Vittorio; Menichino, Aniello; Duca, Gabriella
2025 Aircraft Engineering and Aerospace Technology: An International Journal
doi: 10.1108/aeat-03-2024-0087
Today all domains of life are affected by development of digital technologies. They are seen as shaping the future of transportation as well. This paper aims to identify the development directions of urban air mobility (UAM) applications as driven by sustainability criteria as well as resulting from development of digitalisation, information and communication technologies as well as smart-city related trends.Design/methodology/approachSustainability was assumed as key indicator standing behind perceived attractiveness of UAM. For defined sustainability – consisting of economic, environmental and social components, the base sustainability level of UAM was analysed. Then the potential for increase of sustainability was examined as resulted from UAM applications taking advantage from smart-city concept.FindingsDevelopment of digital technologies can support development of UAM as driving its integration within external systems especially transport systems. Deployment of information and communication technologies creates new opportunities for UAM in terms of multitask applications, shared platforms solutions leading to significant increase level of sustainability of UAM.Practical implicationsResults of this paper can be directly used by researchers as well as industry. They indicate both the trends related to development of UAM as integrated component of transport system as well as directly describe new, more sustainable UAM applications contributing to the successful implementation of UAM in urban conditions as well as efficient development of smart-city concepts consolidating UAM valuable functionalities.Originality/valueResearch results cover UAM sustainability definition, description of new, more sustainable UAM applications as well as revolutionary meaning of digital technologies especially in the context of climate neutrality and operational efficiency improvement in four-dimensional urban transport ecosystems.
Stalewski, Wienczyslaw; Bugała, Pamela; Galinski, Cezary
2025 Aircraft Engineering and Aerospace Technology: An International Journal
doi: 10.1108/aeat-03-2024-0088
The paper aims to optimise several concepts of the flat-upper-surface wing that could install the largest possible number of photovoltaic cells and test them in flight. A wing ideal flat upper surface was necessary to provide the same lighting conditions for each tested cell.Design/methodology/approachThe optimised wings were built based on a developed family of airfoils having 75% of their upper surface flat. Within the developed parametric model of the wings, the design parameters described the spanwise distribution of base airfoils. Maximisation of the endurance factor was assumed as the main objective. The aerodynamic properties of optimised wings were evaluated using a panel method coupled with boundary layer analysis.FindingsThe paper proves that it is possible to design wings with 75% of their upper surface perfectly flat, which are also characterised by good aerodynamic properties.Practical implicationsThe research conducted will allow designing an experimental unmanned aerial vehicle dedicated to investigating the properties of electrical propulsion systems at various altitudes. Data obtained in these investigations will help in the development of future generations of electric-propulsion aircraft.Originality/valueThe innovative wings, developed within the research are unique due to their unusual geometric and aerodynamic properties. They have 75% of their upper surface perfectly flat. That makes them ideal for testing various photovoltaic cells in flight. The biggest challenge was to design the wings so that their specific geometric features did not impair their aerodynamic properties. The paper proves that this challenge has been fully overcome.
Jaume, Jose; Alonso, Gustavo; Benito, Arturo
2025 Aircraft Engineering and Aerospace Technology: An International Journal
doi: 10.1108/aeat-04-2024-0101
In a highly competitive scenario, such as today’s airline business, changes in the regulatory framework may produce important variations in the airlines’ results. An example is the introduction of Sustainable Aviation Fuel (SAF) mandates to help air transport decarbonization. The airlines’ break–even curve provides a useful tool to evaluate the competitive position among airlines and to assess and address the cost impact due to the new regulatory environment. The purpose of this paper is to evaluate the impact of new environmental regulations on airlines’ business results to achieve air transport decarbonization.Design/methodology/approachBased on the break–even curve and the relationship between fuel cost increment and fuel cost related to the airlines’ operating expenses, the unit cost increment due to SAF introduction is obtained for several scenarios of SAF prices and different airlines.FindingsIn many cases, we find that using 100% SAF with prices beyond 1.5 times the present fuel price generates losses: it is not feasible if it is not possible to transfer SAF price to passenger fares due to demand elasticity.Originality/valueThe novelty of this approach is the application of a rationale method to accurately determine the impact of several scenarios of SAF prices on airlines’ business results. This approach also provides a sound and compelling basis to argue before Environmental Regulation Authorities based on facts and figures. This paper is of use and value to airlines, the International Civil Aviation Organization (ICAO), the International Air Transport Association (IATA), practitioners and academics.
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