bluuebunny/crossref_metadata_2025_split huggingface dataset:
Overview and preliminary results of the Scalability Investigation of hybrid Electric concepts for Next-generation Aircraft (SIENA) project
Authors: Aigner Benedikt , Garriga Ana Garcia , Sirtori Gabriele , Riboldi Carlo , Trainelli Lorenzo , Mariani Costanza , Mancini Mauro 
Published: June 2023

Abstract
This paper presents an overview and preliminary system architecture evaluation results of the project SIENA developed under the European Union Clean Sky 2 Program Thematic Topics. The ambition of the project is to accelerate the development of novel aircraft propulsion technologies by identification of technologies that are scalable across different aircraft categories. One of the main tasks within this process is the aircraft-level evaluation of the various system architecture and technology options. For this, a conceptual aircraft design software developed at Politecnico di Milano, and an aircraft on-board systems design and analysis method developed at Collins Aerospace Applied Research and Technology are combined. Utilizing these joint capabilities, the paper presents system architecture performance studies for two aircraft categories, a regional turboprop (ATR 72) and a short/medium-range turbofan (A320neo). The studies compare novel propulsion system concepts, for which kerosene is replaced with hydrogen as the main energy source on board, against traditional reference systems. In this context, two future technology scenarios are considered reflecting conservative and optimistic assumptions, respectively.
FUTPRINT50 Academy – Aircraft Design Challenge 2022: Development of a hybrid-electric regional aircraft
Authors: Eissele J , Lafer S , Mejía-Burbano C , Schließus J , Wiedmann T , Rotundo C , Beyne E , Hildebrandt K , Peng Y , Alessio C , Moebs N , Eisenhut D , Strohmayer A 
Published: June 2023

Abstract
This proceeding presents summaries of three different European student teams in regard to their work within the FUTPRINT50 Academy Aircraft Design Challenge 2022. The task required them to design a regional aircraft with a newly developed hybrid-electric powertrain. The students came up with very different configurations that all led to sophisticated designs of more sustainable regional aircraft.
Automated sizing chain of aircraft structures: A Vertical Tail Plane use case
Authors: Scarano Miriam , Longueville Sébastien de , Jézégou Joël , Gourinat Yves , Bénard Emmanuel 
Published: June 2023

Abstract
Current developments in preliminary design emphasise the potential benefit of addressing detailed sizing cases in the early design stages. This implies a sound understanding of the loads that the structure must withstand and for which it must demonstrate compliance. In aircraft structural practices, stringent safety requirements demand robust designs. It is understood that the foremost limitation and very challenging aspect, in the aviation sector, consists in complying with those requirements while targeting a contained mass. In this respect, the presented work aims to propose an automated implementation of the dimensioning chain by foregrounding a specific subsystem application, id est the Vertical Tail Plane. The conditions corresponding to a set of critical flight loads are identified and used for the sizing process. The use case intends to standardise the process, narrowing down the large number of unknowns on the overall loosely defined design method.
Detailed FE aircraft fuselage sections for water impact simulations in the pre-design process chain
Authors: Leon Muñoz C , Wegener E , Petsch M , Kohlgrüber D 
Published: June 2023

Abstract
The automatic generation of representative fuselage section models with a detailed discretization for the application in computer-aided transient dynamic simulations in the aircraft pre-design process chains is described in this paper. The process consists of Python routines to select and reduce the section from the full fuselage and to refine the mesh and extrude cross-sections in arbitrary zones of the section. By this, different mesh qualities can be integrated in the model according to its individual application. These functionalities were integrated in the structural modelling and sizing framework PANDORA. A simple reinforced panel was used to investigate its structural behaviour with different discretization options under a bending loading condition. Also, a fuselage section model reinforced using either one of the discretization options was subjected to a quasi-static loading. The model was then simulated under crash conditions to investigate its non-linear structural behaviour. The focus of this paper lays on the application and the local structural analysis of the detailed fuselage section in water impact simulations.
Techniques for adjusting qualities of aircraft structural models for more effective aeroelastic flutter analyses
Authors: Olejnik Aleksander , Kachel Stanislaw , Rogólski Robert 
Published: June 2023

Abstract
To solve numerically the problem of aeroelastic flutter, two virtual components are required: a structural finite element model (FEM) and an aerodynamic model. MSC Software package containing Nastran with embedded flutter solution enables to perform calculations with the use of an integrated aeroelastic model. For data block including the model and the set of entry parameters, flutter equation is being solved. On the basis of postprocessed output data curves of run for resulting parameters can be plotted which gives information of flutter critical point.
Numerical results may be subject to some uncertainty. Result deviation could occur as effects of various factors resulting from inaccurate geometry or poor structural qualities of mapped aircraft. Structural defects affecting mass or stiffness matrices of FEM are often hard to identify. Aspects important for effective flutter solutions are strictly connected with the coincidence of structural properties of the real aircraft and its model. In the paper, the method of numerical flutter analysis was presented with the use of techniques available in MSC Nastran. Three assessment methods were proposed to identify structural parameters usable for validating FEMs. The method of mass correction relies on adjustment of model mass values and tuning the location of the center of mass of the model to the coordinates of the location of the center of mass of the real aircraft. For adjusting stiffness of model parts, very useful are results obtained from strength test of the real airframe. The completely reliable but costly method is performing ground vibration tests (GVT) to measure precisely resonant frequencies and natural modes of free vibrations. The results obtained from experiments should be treated as the referenced, but tuning FEM to them requires both adjusting numerical eigenfrequencies and normal modes.
Towards numerical simulation of fatigue damage detection in CFRP laminates by modelling of stochastic vibration response
Authors: Tsivouraki Niki , Tserpes Konstantinos , Fassois Spilios 
Published: June 2023

Abstract
Due to the widespread use of composites in aerospace applications, there is an increasing need for developing Structural Health Monitoring (SHM) systems for composite structures. In this process, simulation models can play a crucial role by contributing to the optimization of the experimental techniques and to understanding of the physical mechanisms. The objective of this work is to numerically simulate fatigue damage detection in laminated composites subjected to random vibration through a white gaussian noise. To this end, the ANSYS FE code has been used. The developed FE model represents an experimental set-up consisting of the composite specimen, the speakers producing the white noise and the measuring equipment. 24 specimens were modelled in total, a healthy one and 23 damaged ones. The white noise was modelled by introducing a normalized sequence of numbers adapted to the free vibration eigenfrequency range. Fatigue damage in the form of matrix cracking and delamination was modelled based on C-Scan images of fatigued specimens by degrading the appropriate elastic properties of the layers in specific groups of elements. Damage of different geometry, size, and type was modelled. The numerical results are in the form Power Spectral Density (PSD) diagrams, natural frequencies, eigenfrequencies and contour plots. The comparison between the numerical and experimental eigenfrequency values show a maximum deviation of 1.7%. The numerical results show a change in the vibration response even in the presence of a small damage, which is an indication of the sensitivity of the method. A significant decrease in natural frequencies of the specimen with the damage accumulation is observed. The present model comprises the first effort towards a fully validated digital twin which will be used for the virtual testing and the optimization of the vibration test.
CubeSat satellite patch antenna designed with 3D printable materials: a numerical analysis
Authors: Pittella Erika , D’Alvia Livio , Piuzzi Emanuele 
Published: June 2023

Abstract
The paper presents a compact patch antenna system designed using 3D printable materials and compatible with any CubeSat satellite structure. Small satellites are transforming the space industry, allowing space access with an important cost reduction for satellite industries and a shorter plan development time compared to bulky satellites. Moreover, using additive manufacturing, it is possible to design specific system components, also with a complex geometry of the inner part, without material wasting. Furthermore, a key point of 3D printing is to allow to go from design to construction straight, having an enormous effect on the supply chain. Generally, CubeSats count on Very High Frequency and Ultra High Frequency communication systems for low bit-rate uplink and downlink. Instead, S-band is among the favourite choices for high bit rates since the frequency range 2.40–2.45 GHz is one of the International Telecommunication Union (ITU) amateur satellite frequency range. An S-band printed antenna system is designed in the present paper, considering the limitations on size and the weight of CubeSat standard. The antenna system is simulated with an electromagnetic CAD, using the polylactic acid as substrate, or polylactide, a thermoplastic polyester widely used in 3D printing.
Development of an urban air mobility vehicle family concept by system of systems aircraft design and assessment
Authors: Ratei Patrick , Naeem Nabih , Prakasha Prajwal Shiva 
Published: June 2023

Abstract
The concept of urban air mobility promises a modern air taxi transport solution providing on-demand air mobility and hence time savings compared to congested terrestrial transportation in major cities and metropolitan areas. To make it a reality, vehicles, infrastructure, services, and operations must be developed simultaneously and cross-linked. These interconnections and interactions of the multitude of systems involved necessitate a system of systems approach, which is accounted for and implemented through agent-based simulations. Accordingly, the system of systems simulation framework is tuned to vehicle architecture as well as fleet design and assessment, thus allows to expand the aircraft design process by fleet operations and transport network perspectives. In this paper, the top level aircraft requirements of electric vertical take-off and landing vehicles are investigated by a fleet-centric approach. Herein, two disparate configurations, i.e. multirotor and tiltrotor, are modelled to depict representative wingless and winged configurations. The optimal design points are found and traded off by formulating different measures of effectiveness accounting for conversion of passenger requests, fleet energy consumption, and vehicle load factor. In summary, this study demonstrates the need for system of systems simulations to derive market-and operations-tailored vehicles and fleets. Furthermore, work on heterogeneous fleet compositions is required.
Unleashing the potentials of digital twinning in the production of composite aircraft components
Authors: Baalbergen E H , de Marchi J A , Klerx R 
Published: June 2023

Abstract
The aircraft industry is continuously challenged to deliver more complex products in order to meet increasingly stricter regulations and growing customer demands, to provide better quality products in larger quantities, and to pay more attention to reusability and circularity issues. At the same time, the industry needs to work with lower costs, shorter lead and production times, less waste, delay, energy consumption, and emissions, and reduce its dependence on non-renewable materials. To keep up with these challenges, the industry automates and continuously innovates as much as is possible. The increasing use of composites in aircraft and aircraft components adds the extra challenge of rapidly bringing innovative manufacturing processes to the factory floor. Aircraft product design, analysis, testing, and production are increasingly being digitized and automated, and consequently involve, and produce, more and more data. Digital twinning is an important enabler for mastering and exploiting this ever-growing plethora of data. In this paper we discuss the potentials of digital twinning in innovative production processes in the aircraft industry, and describe first-hand results and experiences in developing and using digital twinning in the production of composite aircraft components, illustrated by concrete example applications.
Towards a human-centric Digital Twin architecture for Industry 5.0: Aiding skilled operators with composites production automation
Authors: de Marchi J A , Baalbergen E H 
Published: June 2023

Abstract
Industry 4.0 uses digitalization technologies to collect huge amounts of data during production processes. Digital twins can support processing, mastering, and exploiting the plethora of data to assist in optimizing production throughput [1]. But how can digital twins actually support skilled operators on the factory floor? In this paper, we present the design of an operator-centric digital twin for an automated composites production process from start to end, thereby exploring key elements of the architecture of the operator-tailored digital twin and exposing valuable lessons learned from the operator-centric design process. The development methodology applied, and the resultant digital twin architecture, show how operator-centric design guidelines are successfully translated into implementation. This approach helped transforming an otherwise straightforward Industry 4.0 implementation into a state-of-the-art Industry 5.0 implementation, wherein the digital twin plays a central role in supporting and assisting operator-based decision-making at the core of the production process [2].
Simplification of requalification procedure of outdated carbon/epoxy prepregs and scenarios of reuse
Authors: Amare Constance , Mantaux Olivier , Gillet Arnaud , Pedros Mathieu 
Published: June 2023

Abstract
As a result of their combined high mechanical performances and easy processability, carbon/epoxy prepregs are widely used in the manufacture of aerostructures. The resin of these materials is in an intermediate state of polymerisation which makes these materials perishable. Drastic manufacture conditions lead continuously to the generation of expired prepregs that, today, can no more be used in the aeronautic industry nor in other industries. Although requalification procedure can be carried out, its high cost does not always justify such a procedure. This is why large quantities of expired prepregs are send to landfill. The objective of the Cleansky project MANIFICA is to set up a complete recycling chain of carbon fibre composites “from aeronautic waste to innovative composite parts”. The aim of this work is to propose a simplified requalification procedure by avoiding unnecessary tests. These studies are illustrated by property measures on compliant and expired prepregs. The main results were that in most cases, aging induces processing difficulties while mechanical performance remains unaffected. It was also shown that a simpler requalification procedure was possible and that expired prepregs can be reused without loss of performance outside the aeronautical field. Rather than considering expired material as waste, MANIFICA offers several new reuse scenarios.
Manufacturing and LCA Data Collection for a Biomaterial a/c Interior Demonstrator using the example of a Drawer Box
Authors: Baucke Jan 
Published: June 2023

Abstract
In the environment of the CleanSky2 project ecoTECH, INVENT developed an alternative sustainable aircraft interior item.
The main objective of the ecoTECH project is to explore new solutions to reduce the environmental footprint of aircraft components during their global lifecycles and make these solutions available to the aviation industry.
In the Workpackage Biomaterial a/c Interior Demonstrator INVENT leads the development of a drawer box as an exemplary aircraft interior part, made from eco-friendly materials.
The benchmark with regard to economic and ecologic aspects is set by a state-of-the-art aircraft interieur item for which the new biomaterial drawer box is developed as a 100% substitute.
Along the way to catch up with this commercial example, several challenges that are typical for the use of biomaterials were faced during the different development phases which could be divided into material evaluation and selection, design, testing on specimen level and manufacturing of the demonstrator.
Especially the development of the material-appropriated design and manufacturing approach to compensate specific disadvantages of the selected eco-friendly materials to fulfill the same requirements as the state-of-the-art example, were central aspects and took up a large proportion of the overall effort. In parallel with the technical development, also a complete LCA data collection was prepared and later completed during the manufacturing phase of the biomaterials drawer box.
In combination with the EoL approaches, evaluated by the associated project ELIOT, the collected information forms a holistic picture of the environmental footprint over the lifecycle of the new interieur part.
This data set allows also a comparison with the already existing state-of-the-art drawer box not only under the aspects of weight and stability, but also regarding for example energy consumption, production time and recycling potential.
This project has received funding from the Clean Sky 2 Joint Undertaking under the European Union’s Horizon 2020 research and innovation programme
SBAS-based navigation system for precision approach in CAT II LVC
Authors: Kovar Martin , Cypriano Lucas Almeida , Kucera Matej , Ptacek Pavel 
Published: June 2023

Abstract
Due to lack of advanced navigation systems, secondary airports are normally unable to support instrument approaches in low visibility conditions (LVC) more adverse than Category (CAT) I, making them inaccessible during such conditions. Incoming flights are then delayed, diverted to adjacent airports, or cancelled before take-off. This paper presents an onboard navigation solution, under development in scope of SESAR 2020 Solution PJ02-W2- 17.2, which focuses on technology development to mitigate these traffic disruptions by enabling instrument approaches in CAT II LVC with minimum airport and air navigation service provider investments. The concept builds upon global navigation satellite systems (Global Positioning System L1 frequency – GPS L1, satellite-based augmentation system), which currently enables Localizer Performance with Vertical guidance (LPV) operation down to LPV 200 minima. The designed system includes radio altimeter-based aiding and innovative integrity algorithm to improve navigation performance in support of operations below 200ft down to CAT II / LPV 100 minima. As no such requirements have yet been officially published, authors also defined sets of candidates based on Instrument Landing System Collision Risk Model and other sources. The team developed and verified a Monte-Carlo fast-time simulation toolset to enable representative and statistically significant evaluation of the concept feasibility via its availability throughout Europe, as well as sensitivity to proposed sets of alert limits. Also, flight data collection and a developed software prototype allow for further validations. Simulations demonstrated over 95% average availability with the best results achieving level of 99% depending on used set of requirements. The solution enabling operations in LVC allows unlocking various benefits to business/airline operators (e.g., avoided extra costs, increased predictability), passengers (avoided opportunity loss) and airports (retained profit from flights, less traffic at diversion airports). Technology development also marks an important step towards gate-to-gate autonomous operations.
Modelling of a battery supported fuel cell electric power train topology for a regional aircraft
Authors: Staggat Martin , Ludowicy Jonas , Bahrs Victor , Link Antje , Kazula Stefan 
Published: June 2023

Abstract
Electrification of aircraft propulsion may offer a way towards carbon dioxide (CO2) neutral air travel. Here, the electric aircraft demonstrators already flying mostly rely on the use of batteries as energy source. While battery electric concepts may be suitable solutions for short range applications, such as urban air vehicles, the energy density of state of the art batteries is not yet sufficient to power regional aircraft with a typical range of 1000 nautical miles and 70 passengers. One possible topology option of a propulsion concept suitable for a regional aircraft is a hybrid composed of a fuel cell system (FCS) and a battery. On the one hand, this concept uses hydrogen (H2) as the primary energy carrier, resulting in a significant reduction of the required battery stack mass in comparison to a battery only aircraft. On the other hand, a battery support of flight phases with high power demand, such as take-off or climb, allows a smaller dimensioning of the fuel cell system and the corresponding thermal management system (TMS) and therefore additional overall system mass benefits in comparison to a fuel cell only aircraft. The present paper analyses the weight reduction potential of a battery stack supported fuel cell system electric power train architecture for a typical regional aircraft with regard to the hybridization factor (HF) and battery specific energy (BSE). The modelling includes the sizing of the fuel cell system and the battery stack, other mechanical and electric components, such as gearboxes, electric motors and power electronics and the corresponding TMS. The according electrified aircraft is resized, keeping wing loading and power-to-weight ratio constant. The best combination of HF and BSE yielding the lowest MTOM with 27 100 kg is still about 19.9 % heavier than the conventionally powered reference aircraft with 22 800 kg. The study shows that future aircraft of similar weight and hence size require very advanced battery technology with regard to the BSE compared to available state of the art solutions.