bluuebunny/crossref_metadata_2025_split huggingface dataset:
Preliminary hybrid-electric aircraft design with advancements on the open-source tool SUAVE
Authors: Mangold J , Eisenhut D , Brenner F , Moebs N , Strohmayer A 
Published: June 2023

Abstract
The large variety of possible propulsion architectures for environmentally friendly and sustainable aircraft concepts create opportunities for the overall aircraft design. In particular, hybrid-electric aircraft have an increased number of additional components that must be implemented in the aircraft design tool. Primary and secondary energy sources can be used to achieve the necessary reduction in emissions. The preliminary aircraft design tool SUAVE offers the basic setup necessary to integrate the electrification of the propulsion system into the aircraft design. For this purpose, SUAVE has been extended to enable an iterative sizing loop for hybrid-electric aircraft. Hence, many propulsion architectures are easily adaptable. Additional components can be included and their interactions are considered. Furthermore, the fidelity levels of the models are modifiable. Moreover, the top-level aircraft requirements are transformed into a sizing chart to calculate the necessary power and wing loading. Thereby, a reasonable hybridization factor of installed power can be identified. This definition of hybridization implies a specific energy management strategy. As a result, hybridization and the energy management strategy are directly coupled and have to be considered together. Finally, in the postprocessing, the raw data is processed and can be evaluated with figures of merit. This procedure converts the results into a descriptive value and facilitates the comparison to other configurations. The figures of merit include evaluations for emissions, operational aspects and development costs and effort.
Modeling the electrical part of an aeronautical EMA using Simscape
Authors: Quattrocchi Gaetano , Dalla Vedova Matteo D.L. , Maggiore Paolo , Giordano Raffaele 
Published: June 2023

Abstract
The present paper contains an analysis of the operation of the electric motor of an aerospace electromechanical servomechanism present on a test bench. Particularly, the description focuses on the electromagnetic phenomena of the three-phase stator circuit and the switching of the stator phases as a function of the applied control logic and rotor position. The activity was made possible through the construction and validation of a ‘digital twin’ physical model in the Simscape environment, which faithfully reproduces the behaviour of a High-Fidelity numeric reference model, built in the Simulink environment, perfectly representative of the electromechanical servomechanism. The recourse to the construction of a ‘digital twin’ physical model was necessary as it allows the study of non-linear phenomena that are the main cause of failures of electromechanical servomechanisms. Therefore, the analysis conducted will allow prognostics algorithms to be developed in order to predict potential failure conditions and avoid potential hazardous situations in the operating environment.
An interactive framework to facilitate probabilistic set-based multidisciplinary design optimisation studies
Authors: Krupa Gustavo P. , Spinelli Andrea , Kipouros Timoleon 
Published: June 2023

Abstract
The upcoming stringent environmental aircraft regulations and the environmental, social and governance (ESG) framework targeting net zero emissions has forced aircraft manufacturers to seek innovative feasible technical solutions. Often, there is the need to consider entirely radical solutions, such as hybrid-electric aircraft, which are not fully understood when compared with conventional kerosene driven aircraft. The recent development of a probabilistic set-based multidisciplinary optimisation methodology has demonstrated the ability to explore trade-offs when the requirements are uncertain. In this way, the weaknesses and potential to enable the feasibility of hybrid-electric aircraft can be studied from a systems perspective but maintaining the connection with more detailed trade-off studies of components of the sub-systems. We have developed an interactive interface, where the user is guided through the steps of the design methodology and the produced data is visualised to aid an informative decision-making process. In our illustrative case study, decision-makers are enabled to interactively explore the hybrid-electric propulsion design space while considering the impact to the figures of merit from expected improvements in the coming years of key enabling technologies, such as energy storage.
Effect of 3D blade design on the aerodynamic, aeroelastic and structural behavior of a scaled UHBR fan
Authors: Eggers Torben , Friedrichs Jens , Goessling Jan , Seume Joerg R. , Flüh Jan , Lindemann Jens , Paletta Nicola 
Published: June 2023

Abstract
In this paper, the effect of a 3D blade design on the aerodynamic, aeroelastic and structural behavior of a scaled UHBR fan is investigated numerically. First, an initial sensitivity analysis for the geometrical design features sweep and lean as well as an adaption of the thickness position in the fan hub region is conducted. Positive sweep is found to benefit the total pressure ratio, while positive lean improves the polytropic efficiency of the fan stage. Moving the maximum thickness position upwards leads to decreased flow turning and total pressure ratio.
The mode shape and by that the twist-to-plunge ratio of the first mode is significantly influenced by the modifications. Thus, changing the aerodynamic damping of the blade and influencing the flutter behavior of the fan.
Additionally, the fan displacements under aerodynamic and rotational loads are affected. For the fan presented a positive lean causes the blade to bend towards the pressure side when subjected to inertial forces, countering deformation from aerodynamic loads. Thickness adaption moves the shear center of the cross sections to the back. These results are used to optimize the fan blade behavior to achieve the project’s objectives. A final design, which satisfies the aerodynamic, aeroelastic and structrual needs of the CA3ViAR fan stage, is presented.
Hybrid Strategies for the Improvement of the Flame Retardancy of in-situ Silica-Epoxy Nanocomposites cured with Aliphatic Hardener
Authors: Bifulco A , Imparato C , Gaan S , Malucelli G , Aronne A 
Published: June 2023

Abstract
The aerospace industry requires materials showing good mechanical performance, durability, and thermal stability to satisfy very stringent requirements in several applications. Epoxy-based composites can be a suitable solution, due to the peculiar characteristics of the polymer matrix. Epoxy resins can be cured by aliphatic or aromatic hardeners. The use of aliphatic amines is preferable because of their lower toxicity, though these curing agents are easily flammable. Recently, hybrid systems conjugating in-situ modified epoxy matrix with organic and inorganic additives have been developed to flame retard aliphatic epoxy composites. This short review summarizes some applications of such strategies, which are based on the use of the sol-gel technique, DOPO-based flame retardants, bio-waste compounds and other synergists. The review describes the main concept of this approach and the preparation of no-dripping self-extinguishing silica-epoxy hybrid composites showing low phosphorus loadings, tailored interphases and good mechanical properties.
Joining of Composites with Metals using Graded Metal Fabric Interfaces
Authors: Grothe Richard , Weck Daniel , Sennewald Cornelia , Troschitz Juliane , Gude Maik , Cherif Chokri 
Published: June 2023

Abstract
A major challenge in the implementation of fibre-reinforced plastics (FRPs) is the provision of stress-appropriate joints with other materials. Establishing a high-strength, graded metal fabric interface using industrially established joining methods is a target-oriented approach in this context. For this purpose, a novel solution based on a textile transition structure in combination with the evaluation of different joining methods is presented in this article. A process chain was developed that depicts both the design and production of textile transition structure as reinforcement material of the FRP component and the further processing to metal FRP composites. Within the textile transition structure, the hybrid fabrics combine glass fibre yarns and metal flat wires, where the latter enable the joining process and transfer loads into the reinforcing glass fibres. The manufacturing implementation of this new joining interface from the textile to the hybrid component is described in detail within the paper. Furthermore, results of mechanical load tests of the graded metal fabric interface are presented. The research results make a significant contribution to the development of innovative graded metal fabric interface with a benign failure behaviour and a great potential especially with regard to the efficient joining of mixed material constructions in large-scale applications.
Sustainable scrapping method of thermoplastic composite materials
Authors: Ruiz R , Llácer M , Sandá A , Ander J , Halm J , Sterk S 
Published: June 2023

Abstract
In this work, a novel method for more sustainable recycling and cost-efficient manufacturing technique of thermoplastic composite materials is proposed to recover and reprocess waste and end-of-life materials in aerospace industry. For the recycling of carbon fibre reinforced thermoplastics, an innovative scrapping process based on mechanical cutting has been developed and the properties of the obtained scrap and the recycled panel have been analysed. Thus, a cutting tool has been developed for the delamination of the input material with the aim of retaining long fibres in the resulting scrap. Different processing approaches of material scrapping have been evaluated aiming to obtain manageable scrap that can be subsequently used for a compression moulding process. Additionally, an automatic process has been evaluated to manage the scrap and perform the corresponding lay-up to manufacture high-quality thermoplastic composite products with recycled materials. Tensile strength and elasticity modulus properties were tested, and results were discussed. Finally, the life cycle assessment of the new process technology was conducted.
Identification of circular eco-subsystems for end-of-life aviation composite components based on a systematized R6-strategy
Authors: Johst P , Kucher M , Schulz P , Knorr A , Kupfer R , Böhm R 
Published: June 2023

AbstractThe demand of composites in the aviation and space industry has increased significantly in recent decades. This is due to the excellent properties of composite materials, especially their low density and design flexibility. However, the reuse and further utilization of composite structures and their materials provide new challenges for the recycling sector. In accordance with the ‘Green Deal’ of the European Commission, new pathways are required to ensure an effective and economic reuse of composite components at their end-of-life (EoL). We discuss a strategic approach for returning decommissioned parts of aviation composites back into the material cycle with a particular focus on waste reduction, as well as the decrease of the associated energy demand and emissions. Therefore, a sustainable strategy to exploit various circular possibilities was applied, consisting of the six R-strategies:reuse, repair, refurbish, remanufacture, repurposeandrecycling. The Multi-Tiered System of Support is transferred to the introduced R6-strategy. The concept provides an approach to address the challenges of reintroducing EoL composites into the material chain. Based on the systematized R6-strategy it was possible to identify circular eco-subsystems for aviation composite components with minimal effort. Finally, this paper discusses a potential criterion used for assigning EoL aviation composites to the various eco-subsystems.
Air Ejector Analysis in Extended Operational Perimeter for Control Oriented Simulation of Bleed-Air Aircraft Systems
Authors: Eugenio Schillaci , Carles Oliet , Babu Vemula Jagadish , Matthieu Duponcheel , Yann Bartosiewicz , Philippe Planquart 
Published: June 2023

Abstract
The integration of large size Ultra High Bypass Ratio (UHBR) engines introduces new restrictions of space for their integration with the aircraft wing. Under this scenario, a reduction of the size of the bleed air system and particularly of the pre-coolers is requested. The current research aims to introduce air-air ejectors as a potential solution. A combined methodology based on experimental and CFD analyses is proposed to obtain physical insights and validation material for the development of a robust and accurate lumped model, capable of simulating the static and dynamic ejector behaviour in normal and abnormal conditions. In this paper, an overview on the performed initial activities on the dynamic aspects is provided.
Data acquisition unit for suborbital rocket vibration measurement
Authors: Wojciechowski K , Graczyk H , Piwowarczyk M , Truszkowski R , Rękawek P 
Published: June 2023

Abstract
Suborbital rockets and space launch vehicles experience high levels of vibration. They are caused by various factors, such as aerodynamic effects on the external surfaces and engine combustion instability. The second factor is especially pronounced in hybrid rocket engines, such as the main engine of the ILR-33 AMBER 2K rocket. In order to ensure the correct operation of all the equipment and payload on board, vibration testing of the devices is necessary as part of pre-flight qualification. For such tests to be truly indicative of in-flight performance, the vibration environment of the vehicle must be analysed. A conceptual measurement method was proposed, along with a prototype measurement system. The system is adapted to be integrated into the modular ILR-33 AMBER 2K on-board computer or work independently as a separate module. The device measures vibration in three axes in several key points onboard the rocket, with the possibility of connecting multiple units in a daisy-chain configuration. This paper presents the design of the module, including the key aspects of integrating it as part of the avionics package. The means of acquiring and storing of measurement data are presented. The method of validating the system’s data acquisition capabilities is described in detail. Qualification testing results and identified issues are discussed. Possible future improvements are proposed.
Enhancement of the Advanced Weather Awareness System for the development of an Integrated Mission Management System in the COAST project
Authors: Zollo A L , Montesarchio M , Ferrucci M , Bucchignani E , Cinquegrana D 
Published: June 2023

Abstract
The COAST (Cost Optimized Avionics SysTem) project, funded by Clean Aviation Joint Undertaking, works toward the realization of cost-effective key technologies for cockpit and avionics of Small Air Transport (SAT) aircraft. In 2020 the design of a new technology started, the Integrated Mission Management System (IMMS), devoted to automatically optimize the trajectory while considering air-traffic, weather conditions, terrain and obstacles. It is aimed to implement into a unique system the functionalities of Trajectory Planning, Flight Reconfiguration, Tactical Separation and Weather Awareness, benefitting from the integration and interaction on-board of three technologies, individually developed and tested in the first phases of the COAST project: Flight Reconfiguration System (FRS, managing pilot’s incapacitation emergency), Tactical Separation System (TSS, managing tactical traffic separation and enhanced situational awareness) and Advanced Weather Awareness System (AWAS, devoted to provide on-board updated weather data). The present work focuses on the last one and more in detail on the description of new functionalities introduced to the baseline AWAS system, already demonstrated in flight in 2021, in order to allow its integration in IMMS. Specifically, enhancements to the AWAS technology were required to integrate new input weather data and generate additional information, needed for IMMS purposes. These data are produced on-ground and sent through satellite link to the AWAS on-board segment, which has been updated to manage and exchange them with the other components on the aircraft. All the achieved progresses in the development of the evolved version of the AWAS system presented in this work will be demonstrated and tested in flight during a dedicated campaign planned in 2023 in the framework of COAST project.
Hybrid Navigation Prototype for Small Aircraft Transportation Vehicles
Authors: Vaispacher Tomas , Baranek Radek , Malinak Pavol , Kucera Matej 
Published: June 2023

Abstract
The Small Aircraft Transportation (SAT) segment represented mainly by helicopters, piston fixed-wing aircraft, turboprop aircraft, and business jets requires a reliable source of navigation information with an appropriate price. This paper describes the research and development activity funded by Clean Sky 2 Cost Optimized Avionic Systems (COAST) development program targeting affordable hybrid navigation solutions. The affordability is driven by size, weight, and power consumption (SWAP) requirements. The desired level of accuracy, integrity, and availability is being achieved by a hybrid navigation solution based on GPS/INS fusion extended by other navigation sensors. The hybrid core of the systems uses GPS with SBAS augmentation to outperform standard tightly coupled GPS-based hybrid systems. The purpose of this article is to describe the current state, algorithmic structure, and hardware maturity of the navigation system prototype. The paper describes individual hardware components, points to the resulting prototype, and summarizes tests in a representative environment. The ultimate goal is to demonstrate the overall performance of the hybrid system based on a low-cost micro-electro-mechanical system (MEMS) Inertial Measurement Unit (IMU). The low-cost inertial sensor is one of the key components securing the affordability of the proposed system, so its testing plays important role. Another assumption considered in the system design was integration of standardly-used onboard sensors. For this purpose, the hardware prototype was tested in a demonstrative and outdoor environment. The results of this exercise are summarized in this paper.
Preliminary weight estimation of canister based light foldable wing electric propulsion UAV, as a platform for swarm applications
Authors: Karatzas E , Kostopoulos V , Lappas V 
Published: June 2023

Abstract
Lots of disruptive UAV technologies are rising every day. Especially in the design process, under the prism of the upcoming swarm trend, a novelty touch to new foldable designs has started. In combination with electric propulsion systems, those platforms come in reality. Because of their size, the same design can be enlarged and reduced with minor changes at its subsystems. This simplifies the construction process and minimizes the costs. Due to their application range both, civilian and military platforms started to develop their own foldable UAVs, basically for swarm applications. In this study, the basic parameters of such a scalable design will be proposed. A literature survey will be presented, to determine the most common sizes of those platforms and the battery market availability. Afterwards, a mission profile will form the basis of the conceptual process for different dimensional UAVs. Two different methods about the weight estimation of the UAV will be examined. The goal of this multilateral examination is that; enable the designer to precede to an appropriate selection of subsystems of the UAVs, i.e., battery, autopilot and telemetry systems based on the weight estimation.
A Drone Secure Handover Architecture validated in a Software in the Loop Environment
Authors: Filho Enio Vasconcelos , Gomes Filipe , Monteiro Stéphane , Severino Ricardo , Penna Sergio , Koubaa Anis , Tovar Eduardo 
Published: June 2023

Abstract
The flight and control capabilities of uncrewed aerial vehicles (UAVs) have increased significantly with recent research for civilian and commercial applications. As a result, these devices are becoming capable of flying ever greater distances, accomplishing flights beyond line of sight (BVLOS). However, given the need for safety guarantees, these flights are increasingly subject to regulations. Handover operations between controllers and the security of the exchanged data are a challenge for implementing these devices in various applications. This paper presents a secure handover architecture between control stations, using a Software in the Loop (SIL) model to validate the adopted strategies and mitigate the time between simulation and real systems implementations. This architecture is developed in two separate modules that perform the security and handover processes. Finally, we validate the proposed architecture with several drone flights on a virtual testbed.
Vision-Based Real-Time Motion Estimation of Ground Vehicles from Aerial Imagery
Authors: Kurt Yagiz , Soken Halil Ersin 
Published: June 2023

Abstract
This research presents vision-based maneuvering object motion estimation in case of occlusion. Unequal dimension Interactive Multiple Model (UDIMM) approach is applied to increase the motion prediction accuracy when no measurement is available. Current deep learning-based multi-object tracking algorithms cannot track the objects when an occlusion exists, even for quite a short time. The main reason is the motion model used in tracking algorithms. If the measurement coming from the object detector is not available, the prediction model propagates the Kalman Filter’s motion model. In this period, the object may maneuver or accelerate/decelerate so that the tracker cannot assign the tracklets successfully. Eventually, the ID switch occurs, and object tracking gets lost. Using the UDIMM approach, track loss due to the ID switch is highly reduced compared to the simple constant velocity motion model used in the StrongSort multi-object tracker algorithm. A two-dimensional simulation environment is created to compare the ground truth data with the estimation results. Performance results of different filters are compared.