bluuebunny/crossref_metadata_2025_split huggingface dataset:
Multidisciplinary design of aircraft wing for multiregime purposes
Authors: Hospodář P , Drábek A 
Published: June 2023

Abstract
In this paper optimization process of the geometrical design of the wing is described. The goal is to minimize the aerodynamic drag at a requested lift in the cruise regime and thus reduce the fuel consumption. The second goal is to ensure the requested landing regime of the aircraft. Both cases are solved under the wing structural and weight considerations. As a fast design computational tool, a lifting line theory is used. It is moreover supplemented by non-linear aerodynamic airfoil characteristics to provide more accurate results of aerodynamic drag of the wing. These airfoil data were calculated with the CFD and enables to take significant accuracy between low and high-fidelity method which is verified in previous work. The list of requirements is set for aircraft for 40 passengers with a range of 2,500 km at a speed of 438 km/h. As the baseline the L-610 aircraft is selected. Optimized wing geometry in verified in cruise and landing regime/configuration with CFD solver. From the calculation of the weight of the wing and CFD results, the flight performance is calculated for the desired flight mission.
Novel active control technique of aircraft flaps asymmetry
Authors: Baldo L , Cejudo Ruiz J. M. , Dalla Vedova M D L 
Published: June 2023

Abstract
This paper proposes an active monitoring strategy to control aircraft trailing-edge high-lift devices (flaps) asymmetry. A variety of system failures can cause asymmetry in the control surfaces, including the transmission torsion bar break down and control surface actuator wear and tear. The authors’ novel asymmetry active monitoring approach detects and identifies flaps position asymmetry. Once the failure side has been identified, the active control activates the wingtip brakes to stop the uncontrolled flap surface. The still controlled flaps are driven to the damaged surface braking point to reduce flap asymmetry. As a result, the undesired aircraft roll moment (due to flaps asymmetry) will be controlled, and the aircraft maneuverability after failure will be (partially) restored. The proposed asymmetry active monitoring technique has been widely tested in different operational and failure conditions, using wear-free or worn-out actuators and considering every failure side scenario. The behavior of the proposed active model is evaluated in terms of time response and stability margin under certain operating conditions.
Sizing Approach with Flight Time Comparison of An Electric Multirotor Propulsion Chain with Batteries and Fuel Cells
Authors: Chahba S , Sehab R , Krebs G , Akrad A , Morel C 
Published: June 2023

Abstract
The concept of electric vertical take-off and landing (E-VTOL) aerial vehicles is gaining more and more attention, thanks to their non-polluting operation and simple air traffic management. Indeed, around the world, there are currently more than 500 projects that concern the development and improvement of their performances. Development of sizing methods for rapid selection of the propulsion chain components remains an important task in this process. In this paper, an approach for sizing and selecting the propulsion chain components of an E-VTOL aerial vehicle is developed and validated. First, the optimal pair motor/propeller is selected using a global nonlinear optimization in order to maximize the specific efficiency of these components. Second, two energy storage technologies are considered and sized in order to assess their influence on the aerial vehicle flight time. Finally, based on this sizing process, the optimized propulsion chain gross take-off weight (GTOW) is evaluated, using regression methods based on propulsion chain supplier data.
Deriving a year 2040 reference aircraft from a modern turboprop, implemented and calibrated in SUAVE
Authors: Brenner F , Mangold J , Eisenhut D , Moebs N , Strohmayer A 
Published: June 2023

Abstract
The FUTPRINT50 project is focused on designing and preparing ground for a hybrid-electric regional aircraft with a capacity of 50 passengers. The aircraft is designed for entry-into-service between 2035 and 2040. To evaluate and refine the design concepts, the project will use two different reference aircraft: one that is state-of-the-art, and another that is extrapolated to represent what a year 2040 model might look like. The ATR 42-500, a 50-seat aircraft with a design range of 840 nautical miles, will serve as the year 2000 reference aircraft. As part of the project, the open-source aircraft design tool SUAVE is adapted for use with hybrid-electric aircraft. The ATR 42-500 was reverse-engineered in the same SUAVE environment using official manufacturer data and other sources for reference and calibration. The environmental impact of the aircraft is assessed based on its emissions of CO2, NOX, and noise. The technology used in the ATR 42-500 will be outdated by 2040. To estimate the impact of the year 2035/2040 hybrid components, a year 2040 reference aircraft was implemented. This aircraft is based on the ATR 42-500 but will incorporate several further enhanced technologies, such as a higher wing aspect ratio, more efficient engines, and improved materials.
Regional Multi-Mission Aircraft in Clean Sky 2: Environmental Impact and Actual Technologies Evaluation from Flight Tests
Authors: Benítez Luis , Martinez Miguel , Nuñez Manuel 
Published: June 2023

Abstract
Airbus Defence and Space, former CASA, has lead the Regional Multi-mission aircraft configuration in the Clean Sky 2 program. The set of technologies selected for this platform have been matured with the support of multiple partners across Europe by means of theoretical studies, tests in laboratories, full scale on ground demonstration in rigs and in flight demonstration in the Regional Flight Test Bed 2 (FTB#2) platform based on an Airbus C295 aircraft. These technologies cover multiple aspects of the aircraft design, manufacturing and operations like innovative materials, systems architectures towards a more electrical aircraft, affordable flight control system devoted to control multiple control surfaces in the wing and new manufacturing and assembly processes. The outputs of the research are taken to evaluate the environmental impact in terms of gaseous emissions (fuel consumption, CO2 and NOx) and noise reduction in take-off and landing of future aircraft with respect of the reference configuration defined at the beginning of Clean Sky 2 program. This paper describes the environmental impact in future Regional Multi-mission configurations and the technology evaluation done with the flight test campaign of the Regional FTB#2 in 2022. The flight test campaign is a cornerstone milestone of the program to demonstrate the most mature technologies.
Preliminary design of next generation Mach 1.6 supersonic business jets to investigate landing & take-off (LTO) noise and emissions – SENECA.
Authors: Mourouzidis C , Del Gatto D , Adamidis S , Villena Munoz C , Lawson C , Martinez Corzo B , Leyland P , Marsh D , Lim L , Owen B , Terrenoire E , Atinault O , LeGriffon I. , Huet M , Schaefer M , Plohr M , Bake S , Madden P 
Published: June 2023

Abstract
With the approach of next generation supersonic transport entry into service, new research activities were initiated to support updates on ICAO regulations and certification processes for supersonic transport vehicles. Within this context, the EU Horizon 2020 SENECA project has been launched to investigate the levels of noise and gaseous emissions in the vicinity of airports as well as the global climate impact of next generation supersonic civil aircraft. This paper introduces some of the preliminary outcomes of this investigation. It presents the preliminary design and performance analysis of a Mach 1.6 business jet, following an integrated aircraft-engine design approach. The preliminary design was performed accounting for the limitations posed by future environmental restrictions on respective subsonic vehicles. The market space and mission route definition exercise assumed only “over-sea” supersonic operations, while for “over-land”, only subsonic operations where allowed. Parametric studies on engine integrated design demonstrated modest core temperatures while cruising and the significant impact of engine installation on performance. At this first design iteration, assuming current state of the art technology, the Mach 1.6 business jet showed good potential to satisfy the predicted mission requirements while respecting the environmental constraints in terms of Landing & Take-Off (LTO) noise and emissions.
Environmental-impact assessments at airport level of Clean Sky 2 technologies
Authors: van Eenige M J A , van Ommeren T E 
Published: June 2023

Abstract
GREENPORT2050 is a project within Clean Sky 2 Technology Evaluator. Its objective is to assess the environmental impact up to 2050 at airport level of technologies developed in the Clean Sky 2 Programme for fixed-wing aircraft. With these assessments, it complements the environmental-impact assessments of those technologies at the other two levels in Clean Sky 2 Technology Evaluator: aircraft and air-transport system level. This paper provides an overview of the systematic approach for airport-level assessments in GREENPORT2050 and of the indicators to quantify impacts in these assessments.
CO2 and non-CO2 balanced Environmental Scores Module for flight performance evaluation and optimisation
Authors: Middel Jan , Sutopo Kinanthi , Heesbeen Bart , Verbeek René , Dungen Nick van den , Sáez Raúl , Prats Xavier , Riccio Angelo 
Published: June 2023

Abstract
The SESAR2020 exploratory research (ER4) programme CREATE (Grant 890898) developed a climate and weather aware Concept of Operations (ConOps) which encompasses a multi-aircraft 4D trajectory optimisation framework, which utilises a CO2 and non-CO2 balanced Environmental Scores Module (ESM) for the en-route flight phase. The ESM provides a computational method to evaluate the “greenness” of aircraft trajectories. Some components related to the internal ESM scoring are based on expert judgement, which is in line with the technology readiness level (TRL) 1 of the solution. Fast-time simulations were performed to demonstrate the proof-of-concept of the ESM in a multi-aircraft tactical optimisation scenario in the North-Atlantic region. The results show that, because of the simplicity of the metric, the ESM could be well used for trajectory optimisation and tactical replanning, and most likely as well as flight and ATC sector environmental performance evaluations.
Operating and Environmental Cost Considerations Comparison for Hybrid-Electric Propulsion Architecture Variants
Authors: Nasoulis Christos P. , Protopapadakis Georgios , Ntouvelos Elissaios G. , Gkoutzamanis Vasilis G. , Kalfas Anestis I. 
Published: June 2023

Abstract
A promising solution for sustainable aviation is hybrid-electric propulsion, which is gaining popularity in recent years. However, hybrid-electric propulsion variants are affected by the technological maturity of electric components, which have a direct impact on the electrification benefit, compared to conventional propulsive configurations. This work aims in investigating three different Entry Into Service dates, i.e., 2027, 2030, and 2040, for two hybrid-electric propulsive configurations, namely the Series and the Parallel. Six hybrid variants are sized, one for each date and configuration, using an in-house tool, and their mission performance metrics, operating costs, and environmental impact are compared to a conventional aircraft with technological assumptions of 2014. Results indicate that the Parallel variants promise a block fuel and energy reduction of up to 33 % and 28 % respectively for 2040, whereas the Series variants show a respective reduction of 66 % and 58 % accordingly. Moreover, the 2027 Parallel aircraft has reduced annual operating costs compared to the Series 2027, whereas a turnaround point exists in which the Series becomes more economical to operate, compared to both Parallel and the Reference aircraft after 2030. Finally, the Life Cycle Assessment suggests that the Series variants have a lower environmental impact compared to the respective Parallel variants and that both configurations have better scores than the Reference aircraft. The Parallel and Series configurations of 2030 promise an environmental impact reduction of up to 22.8 % and 59.8 % respectively, compared to the reference aircraft.
Assessment of (hybrid)-electric drive-train architectures for future aircraft applications
Authors: König P , Müller P , Höschler K 
Published: June 2023

Abstract
Future regional aircraft and propulsion systems will have to address both a growing market and stricter environmental constraints. Besides the increase of component efficiencies, the technological transformation from conventional to (hybrid)-electric propulsion systems represents a paradigm shift with great potential for the aviation industry. In this context, economic, market-relevant as well as technological boundary conditions for the electrical and mechanical components are developed in this paper for a reference regional aircraft and are based on current research results from different institutions. The propulsion performance analysis of a conventional turboprop is compared and evaluated with a serial-hybrid and a fully-electric configuration (both battery-electric), status today as well as status ~2035, as an example, whereby the presented process can also be applied to other hybrid configurations too. An energy-optimised propulsion and operating concept is derived with regard to minimum resulting system weight. The results of this analysis help to define necessary boundary conditions for future subsystem investigations and identify key research items, especially in the field of the battery.
Are batteries fit for hybrid-electric regional aircraft?
Authors: Kühnelt Helmut , Mastropierro Francesco , Zhang Ningxin , Toghyani Somayeh , Krewer Ulrike 
Published: June 2023

Abstract
Hybrid electric propulsion is likely to play a more prominent role for regional aircraft with 40+ passengers in the future air transport system with reduced climatic impact. In IMOTHEP, two hybrid-electric regional (HER) aircraft concepts, a conservative and a radical, are developed. Energy dense battery technologies are needed to enable hybrid-electric propulsion of regional aircraft. Furthermore, these batteries need to become commercially available within the planned development time of the new aircraft, i.e. until 2030. This paper will discuss general requirements for the HER battery and aims at providing an overview on the most promising industrial approaches for energy dense battery cell technologies – from advanced Li-ion to all-solid-state – with view of their application in air transport and forecasted availability on the market. Furthermore, results will be presented from the study performed in IMOTHEP on hybrid polymer-ceramic all-solid-state battery electrochemistry that combines lab trials with electrochemical numerical simulation.
Overall Aircraft Design: From the open-source FAST-OAD to its training branch
Authors: Sy Ousmane , Sy Birame , Lutz Florent , Sarr Abdoulaye , Bénard Emmanuel 
Published: June 2023

Abstract
Reducing the environmental footprint of commercial aviation to a manageable level, is a formidable challenge for the whole aeronautical community. In particular, new aircraft configurations could drastically reduce the environmental footprint. Training of engineers in Overall Aircraft Design (OAD) is, therefore, an essential step to be considered in order to take environmental issues into account from the preliminary design phase. ONERA and ISAE-SUPAERO have developed FAST-OAD (Future Aircraft Sizing Tool – Overall Aircraft Design), an open source platform for the analysis, sizing and optimization of aircraft, emphasizing on user-friendliness and modularity. The open source version provides a flexible and practical framework that allows researchers and industrial actors all around the world, to extend the entire aircraft design process to new challenging aircraft configurations, in-house models and higher fidelity approaches. In this contribution, the authors introduce, with a qualitative perspective, a training branch of FAST-OAD, to help trainers to build classes and tutorials.
Parametric model of aircraft external geometry as a component of FAST-OAD aircraft preliminary design system.
Authors: Grendysa Wojciech , Jézégou Joël , Benard Emmanuel 
Published: June 2023

Abstract
Rapid evolutions in fields such as aerospace propulsion, materials engineering, geometry modelling tools or optimization tools provide the opportunity to search for novel configurations of future aircraft in an expanding domain. In order to effectively explore the space of variables of constantly expanding size, one needs tools that give the ability to automate this process. Such a tool is the Future Aircraft Sizing Tool for Overall Aircraft Design or FAST-OAD. FAST-OAD allows for rapid estimation of aircraft size, based on set, so-called Top Level Aircraft Requirements (TLARs) by using multi-disciplinary and multi-fidelity analysis and optimization.
An essential component of such a system is a module capable of modelling the external geometry of the calculated case. This article describes an attempt to use a powerful commercial Computer Aided Design software, Siemens NX, to model the aircraft external geometry based on the results of the analysis performed by FAST-OAD. This approach, compared to previous works, brings some limitations but, on the other hand, gives the possibility to base the geometry on a mathematically consistent model and helps to better understand the set of parameters necessary to describe the geometry correctly.
The main objective of this research is to provide a tool that allows the automatic generation of aircraft exterior geometry based on the output parameters received from the FAST-OAD package.
An additional goal of this activity is to determine the parameter set necessary to properly define the external geometry, but at the same time not containing redundant, dependent geometric parameters. The minimum number of independent parameters necessary to completely describe the external geometry is sought.
Numerical Investigation of the Magnetic Alignment of Fe-Co-Coated Single Reinforcement Fibers
Authors: Xu Yun , Winkler Anja , Helwig Martin , Modler Niels , Gude Maik , Dittes Axel , Höhlich Dominik , Lampke Thomas 
Published: June 2023

Abstract
Fiber-reinforced composites are progressively more used in a variety of industrial applications. In recent years, carbon fiber-reinforced plastics have become increasingly popular, particularly in the aerospace sector because they offer outstanding mechanical properties combined with low weight. However, the orientation and distribution of the fibers have a significant effect on the mechanical and physical properties of the composite materials. Using conventional manufacturing technologies, it is not always technologically possible to adjust the fiber orientation to the load direction. One possible approach to targeted fiber alignment is the combination of classical manufacturing processes with a superimposed alignment mechanism so that the fibers can be oriented according to the load during component manufacturing. In this context, the orientation and distribution of short and long fibers through an external magnetic field seem to be well-suited to be integrated into the conventional manufacturing process of fiber-reinforced composites. Therefore, the generally non-magnetic reinforcement fibers, e.g. carbon or glass fibers, need to be modified or coated with magnetic materials. In this paper, carbon fibers coated with an iron-cobalt alloy are prepared by electrodeposition for the validation of simulation models developed in previous studies. Furthermore, numerical studies are presented in regard to the orientation of such fibers in polymeric matrices. Thus, simulative investigations of the orientability of coated carbon fibers in polymeric materials are shown and the works provide an important reference for future studies of fiber orientation and alignment using magnetic fields.
Coupling of a zonal air and temperature distribution model with an low pressure environmental control system ducting model
Authors: Matheis C , Korth P , Norrefeldt V , Lindner A , Urzua-Reichl K , Munoz-Sanchez M 
Published: June 2023

Abstract
The Regional Cabin Demonstrator is developed within the Clean Sky 2 project and integrates the latest developments in sustainable and high-performance cabin interiors for enhanced passenger experience. Within this project, an innovative low pressure environmental control system (ECS) ducting is developed and integrated into the demonstrator. Together with these hardware demonstration efforts, the associated model based development capabilities are strengthened. The goal is to virtually design the aircraft prior to its actual hardware integration. Such integration requires heterogeneous submodels interaction in an overall aircraft model. The current work presents such a model coupling. On the one hand, a component database for 1D system simulation is developed. By connecting these parameterized component models, it is possible to build any desired low pressure ECS system for which the pressure drop and the air outlet flow distributions are calculated. This system model is interfaced with a zonally decomposed indoor environment Modelica-model of the Regional Cabin Demonstrator showing resulting cabin air temperature, stratification and airflow. Both models interact on the one hand because the air temperature and distribution in the air outlets generates a boundary condition for the zonal model. On the other hand, part of the cabin exhaust air is recirculated and thus generates a boundary condition for the low pressure ECS model. The coupling is performed by the functional mock-up (FMU) standard allowing to couple different models through standardized in- and outputs while maintaining protection of individual partners’ IP. The model application is demonstrated on the example of a cruise condition thermal boundary condition.