Search for Articles:
Title / Keyword
Author / Affiliation / Email
Journal
Article Type
 
 
Advanced Search
 
Section
Special Issue
Volume
Issue
Number
Page
 
3.4
2.1
Journals
Aerospace
Special Issues
9th EASN International Conference on Innovation in Aviation & Space
share announcement

9th EASN International Conference on Innovation in Aviation & Space

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

Deadline for manuscript submissions: closed (30 November 2019) | Viewed by 68707

Printed Edition Available!
A printed edition of this Special Issue is available here.

Special Issue Editors

Prof. Dr. Spiros Pantelakis

E-Mail Website
Guest Editor
Honorary Chairman of the European Aeronautics Science Network Association (EASN), Head of the Laboratory of Technology and Strength of Materials, Department of Mechanical Engineering and Aeronautics, University of Patras, Panepistimioupolis Rion, 26500 Patras, Greece
Interests: aeronautical materials and structures; mechanical behaviour of materials; structural integrity; damage mechanics; experimental fracture mechanics; fatigue of aircraft materials and structures; ageing aircraft; 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

Special Issue Information

Dear Colleagues,

This Special Issue is cooperating with the 9th EASN International Conference on Innovation in Aviation & Space (https://easnconference.eu/home), which will take place in Athens, Greece from the 3rd until the 6th of September, 2019.

This conference will act as a forum where innovative ideas, breakthrough concepts, and disruptive technologies are presented, while in parallel be the place for disseminating the knowledge and results achieved in the frame of research projects of the aviation and space field. The 9th EASN International Conference will include a number of Plenary Talks by distinguished personalities of the European aviation and space sectors from academia, industry, research community, and policymakers. It will also include Thematic Sessions, along with Technical Workshops where evolving ideas, technologies, products, services, and processes will be discussed. The identification of possible synergies and interactions with other sectors (e.g., automotive) will be a key aspect of the event.

Furthermore, the conference is expected to be a major European dissemination and exploitation event of aviation & space-related research. The majority of currently running research projects will exploit the 3-day technical program to present their activities and achieved goals, discuss current trends and future needs of aviation & space-related research and try to identify possible synergies with each other. Additionally, a number of policy development projects will also take the floor to present the strategic priorities of the European aviation sector with regard to the challenges of FlightPath2050 and the expected “Horizon Europe” Framework Programme.

Authors of outstanding papers related to Aviation & Space are invited to submit extended versions of their work to this Special Issue for publication.

Prof. Dr. Spiros Pantelakis
Prof. Dr. Andreas Strohmayer
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: Manufacturing
  • Aerostructures: Materials
  • Flight physics
  • Propulsion
  • Avionics, systems, and Equipment
  • Air traffic management and airports
  • Human factors
  • Innovative concepts and scenarios
  • Industry 4.0 and factories of the future
  • Space science, technologies, and exploration
  • Space applications and operations
  • Space policies
  • Environmental, recycling, and disposal strategies
  • Safety, regulation, and standards
  • Synergies and technology transfer with the automotive industry
  • European policy actions in the field of aviation & space

Benefits of Publishing in a Special Issue

  • Ease of navigation: Grouping papers by topic helps scholars navigate broad scope journals more efficiently.
  • Greater discoverability: Special Issues support the reach and impact of scientific research. Articles in Special Issues are more discoverable and cited more frequently.
  • Expansion of research network: Special Issues facilitate connections among authors, fostering scientific collaborations.
  • External promotion: Articles in Special Issues are often promoted through the journal's social media, increasing their visibility.
  • e-Book format: Special Issues with more than 10 articles can be published as dedicated e-books, ensuring wide and rapid dissemination.

Further information on MDPI's Special Issue polices can be found here.

Related Special Issues

Published Papers (9 papers)

Download All Papers
Order results
Result details
Show export options expand_more Show export options expand_less
Select all
Export citation of selected articles as:

Editorial

Jump to: Research

2 pages, 165 KiB  
Editorial
Special Issue “9th EASN International Conference on Innovation in Aviation & Space”
by Spiros Pantelakis and Andreas Strohmayer
Aerospace 2021, 8(4), 110; https://doi.org/10.3390/aerospace8040110 - 14 Apr 2021
Viewed by 1901
Abstract
This Special Issue contains selected papers from works presented at the 9th EASN International Conference on Innovation in Aviation & Space, which was successfully held in Athens, Greece, between the 3rd and 6th of September 2019 [...] Full article
(This article belongs to the Special Issue 9th EASN International Conference on Innovation in Aviation & Space)

Research

Jump to: Editorial

22 pages, 3192 KiB  
Article
Propeller Selection by Means of Pareto-Optimal Sets Applied to Flight Performance
by Svatomir Slavik, Jan Klesa and Jiri Brabec
Aerospace 2020, 7(3), 21; https://doi.org/10.3390/aerospace7030021 - 5 Mar 2020
Cited by 6 | Viewed by 6520
Abstract
Selection process of the propeller for short take-off and landing (STOL) category aircraft is described. The aim is to achieve the highest possible performance with fixed propeller, i.e., high maximal horizontal and cruise speed, short take-off and high rate of climb. These requirements [...] Read more.
Selection process of the propeller for short take-off and landing (STOL) category aircraft is described. The aim is to achieve the highest possible performance with fixed propeller, i.e., high maximal horizontal and cruise speed, short take-off and high rate of climb. These requirements are contradictory and so Pareto sets were used in order to find the optimal propeller. The method is applied to a family of geometrically similar propellers that are suitable for 73.5 kW (100 hp) piston engine designed for ultralight category aircraft with maximal take-off weight of 472.5 kg. The propellers have from two to eight blades, blade angle settings from 15° to 40° and diameter from 1.1 m to 2.65 m. Pareto frontier is designed for each pair of flight conditions, and the optimal propeller is selected according to these results. For comparison, the optimal propeller selection from the propeller family by means of a standard single-optimal process based on the speed power coefficient cs is also used. Use of Pareto sets leads to considerable performance increase for the set of contradictory requirements. Therefore, high performance for a low price for the given aircraft can be achieved. The described method can be used for propeller optimization in similar cases. Full article
(This article belongs to the Special Issue 9th EASN International Conference on Innovation in Aviation & Space)
►▼ Show Figures

Figure 1

21 pages, 3788 KiB  
Article
Effect of Hot-Wet Storage Aging on Mechanical Response of a Woven Thermoplastic Composite
by Theofanis S. Plagianakos, Kirsa Muñoz, Diego Saenz-Castillo, Maria Mora Mendias, Miguel Jiménez and Vasileios Prentzias
Aerospace 2020, 7(2), 18; https://doi.org/10.3390/aerospace7020018 - 24 Feb 2020
Cited by 5 | Viewed by 5329
Abstract
The effect of hot-wet storage aging on the mechanical response of a carbon fiber polyether ether ketone (PEEK)-matrix woven composite has been studied. A wide range of static loads and selected cyclic load tests on the interlaminar fatigue strength were performed. Static tests [...] Read more.
The effect of hot-wet storage aging on the mechanical response of a carbon fiber polyether ether ketone (PEEK)-matrix woven composite has been studied. A wide range of static loads and selected cyclic load tests on the interlaminar fatigue strength were performed. Static tests were conducted in batch mode, including on- and off-axis tension, compression, flexure, interlaminar shear strength (ILSS) and fracture tests in Modes I, II and I/II. Respective mechanical properties have been determined, indicating a degrading effect of aging on strength-related properties. The measured response in general, as well as the variance quantified by batch-mode test execution, indicated the appropriateness of the applied standards on the material under consideration, especially in the case of fracture tests. The material properties presented in the current work may provide a useful basis towards preliminary design with PEEK-based woven thermoplastic composites during service in aerospace applications. Full article
(This article belongs to the Special Issue 9th EASN International Conference on Innovation in Aviation & Space)
►▼ Show Figures

Figure 1

15 pages, 5096 KiB  
Article
Modular Multifunctional Composite Structure for CubeSat Applications: Preliminary Design and Structural Analysis
by Giorgio Capovilla, Enrico Cestino, Leonardo M. Reyneri and Giulio Romeo
Aerospace 2020, 7(2), 17; https://doi.org/10.3390/aerospace7020017 - 24 Feb 2020
Cited by 22 | Viewed by 11070
Abstract
CubeSats usually adopt aluminum alloys for primary structures, and a number of studies exist on Carbon Fiber Reinforced Plastic (CFRP) primary structures. The internal volume of a spacecraft is usually occupied by battery arrays, reducing the volume available to the payload. In this [...] Read more.
CubeSats usually adopt aluminum alloys for primary structures, and a number of studies exist on Carbon Fiber Reinforced Plastic (CFRP) primary structures. The internal volume of a spacecraft is usually occupied by battery arrays, reducing the volume available to the payload. In this paper, a CFRP structural/battery array configuration has been designed in order to integrate the electrical power system with the spacecraft bus primary structure. The configuration has been designed according to the modular design philosophy introduced in the AraMiS project. The structure fits on an external face of a 1U CubeSat. Its external side houses two solar cells and the opposite side houses power system circuitry. An innovative cellular structure concept has been adopted and a set of commercial LiPo batteries has been embedded between two CFRP panels and spaced out with CFRP ribs. Compatibility with launch mechanical loads and vibrations has been shown with a finite element analysis. The results suggest that, even with a low degree of structural integration applied to a composite structural battery, more volume and mass can be made available for the payload, with respect to traditional, functionally separated structures employing aluminum alloy. The low degree of integration is introduced to allow the use of relatively cheap and commercial-off-the-shelf components. Full article
(This article belongs to the Special Issue 9th EASN International Conference on Innovation in Aviation & Space)
►▼ Show Figures

Figure 1

17 pages, 2488 KiB  
Article
Estimation of Performance Parameters of Turbine Engine Components Using Experimental Data in Parametric Uncertainty Conditions
by Olexandr Khustochka, Sergiy Yepifanov, Roman Zelenskyi and Radoslaw Przysowa
Aerospace 2020, 7(1), 6; https://doi.org/10.3390/aerospace7010006 - 16 Jan 2020
Cited by 9 | Viewed by 6481
Abstract
Zero-dimensional models based on the description of the thermo-gas-dynamic process are widely used in the design of engines and their control and diagnostic systems. The models are subjected to an identification procedure to bring their outputs as close as possible to experimental data [...] Read more.
Zero-dimensional models based on the description of the thermo-gas-dynamic process are widely used in the design of engines and their control and diagnostic systems. The models are subjected to an identification procedure to bring their outputs as close as possible to experimental data and assess engine health. This paper aims to improve the stability of engine model identification when the number of measured parameters is small, and their measurement error is not negligible. The proposed method for the estimation of engine components’ parameters, based on multi-criteria identification, provides stable estimations and their confidence intervals within known measurement errors. A priori information about the engine, its parameters and performance is used directly in the regularized identification procedure. The mathematical basis for this approach is the fuzzy sets theory. Synthesis of objective functions and subsequent scalar convolutions of these functions are used to estimate gas-path components’ parameters. A comparison with traditional methods showed that the main advantage of the proposed approach is the high stability of estimation in the parametric uncertainty conditions. Regularization reduces scattering, excludes incorrect solutions that do not correspond to a priori assumptions and also helps to implement the gas path analysis with a limited number of measured parameters. The method can be used for matching thermodynamic models to experimental data, gas path analysis and adapting dynamic models to the needs of the engine control system. Full article
(This article belongs to the Special Issue 9th EASN International Conference on Innovation in Aviation & Space)
►▼ Show Figures

Figure 1

17 pages, 9228 KiB  
Article
Superhydrophobic Coatings as Anti-Icing Systems for Small Aircraft
by Filomena Piscitelli, Antonio Chiariello, Dariusz Dabkowski, Gianluca Corraro, Francesco Marra and Luigi Di Palma
Aerospace 2020, 7(1), 2; https://doi.org/10.3390/aerospace7010002 - 2 Jan 2020
Cited by 52 | Viewed by 9782
Abstract
Traditional anti-icing/de-icing systems, i.e., thermal and pneumatic, in most cases require a power consumption not always allowable in small aircraft. Therefore, the use of passive systems, able to delay the ice formation, or reduce the ice adhesion strength once formed, with no additional [...] Read more.
Traditional anti-icing/de-icing systems, i.e., thermal and pneumatic, in most cases require a power consumption not always allowable in small aircraft. Therefore, the use of passive systems, able to delay the ice formation, or reduce the ice adhesion strength once formed, with no additional energy consumption, can be considered as the most promising solution to solve the problem of the ice formation, most of all, for small aircraft. In some cases, the combination of a traditional icing protection system (electrical, pneumatic, and thermal) and the passive coatings can be considered as a strategic instrument to reduce the energy consumption. The effort of the present work was to develop a superhydrophobic coating, able to reduce the surface free energy (SFE) and the work of adhesion (WA) of substrates, by a simplified and non-expensive method. The developed coating, applied as a common paint with an aerograph, is able to reduce the SFE of substrates by 99% and the WA by 94%. The effects of both chemistry and surface morphology on the wettability of surfaces were also studied. In the reference samples, the higher the roughness, the lower the SFE and the WA. In coated samples with roughness ranging from 0.4 and 3 µm no relevant variations in water contact angle, nor in SFE and WA were observed. Full article
(This article belongs to the Special Issue 9th EASN International Conference on Innovation in Aviation & Space)
►▼ Show Figures

Graphical abstract

19 pages, 3781 KiB  
Article
Assessment of Aircraft Surface Heat Exchanger Potential
by Hagen Kellermann, Anaïs Luisa Habermann and Mirko Hornung
Aerospace 2020, 7(1), 1; https://doi.org/10.3390/aerospace7010001 - 19 Dec 2019
Cited by 26 | Viewed by 9554
Abstract
Providing sufficient cooling power for an aircraft will become increasingly challenging with the introduction of (hybrid-) electric propulsion. To avoid excessive drag from heat exchangers, the heat sink potential of the aircraft surface is evaluated in this study. Semi-empirical correlations are used to [...] Read more.
Providing sufficient cooling power for an aircraft will become increasingly challenging with the introduction of (hybrid-) electric propulsion. To avoid excessive drag from heat exchangers, the heat sink potential of the aircraft surface is evaluated in this study. Semi-empirical correlations are used to estimate aircraft surface area and heat transfer. The impact of surface heating on aircraft drag is qualitatively assessed. Locating surface heat exchangers where fully turbulent flow is present promises a decrease in aircraft drag. Surface cooling potential is investigated over a range from small regional aircraft to large wide body jets and a range of surface temperatures. Four mission points are considered: Take-off, hot day take-off, climb and cruise. The results show that surface heat exchangers can provide cooling power in the same order of magnitude as the waste heat expected from (hybrid-) electric drive trains for all sizes of considered aircraft. Also, a clear trend favouring smaller aircraft with regards to the ratio of available to required cooling power is visible. Full article
(This article belongs to the Special Issue 9th EASN International Conference on Innovation in Aviation & Space)
►▼ Show Figures

Figure 1

16 pages, 4420 KiB  
Article
Determination of Serviceability Limits of a Turboshaft Engine by the Criterion of Blade Natural Frequency and Stall Margin
by Yaroslav Dvirnyk, Dmytro Pavlenko and Radoslaw Przysowa
Aerospace 2019, 6(12), 132; https://doi.org/10.3390/aerospace6120132 - 9 Dec 2019
Cited by 17 | Viewed by 8577
Abstract
This paper analyzes the health and performance of the 12-stage axial compressor of the TV3-117VM/VMA turboshaft operated in a desert environment. The results of the dimensional control of 4800 worn blades are analyzed to model the wear process. Operational experience and two-phase flow [...] Read more.
This paper analyzes the health and performance of the 12-stage axial compressor of the TV3-117VM/VMA turboshaft operated in a desert environment. The results of the dimensional control of 4800 worn blades are analyzed to model the wear process. Operational experience and two-phase flow simulations are used to assess the effectiveness of an inlet particle separator. Numerical modal analysis is performed to generate the Campbell diagram of the worn blades and identify resonant blade vibrations which can lead to high cycle fatigue (HCF): mode 7 engine order 30 in the first stage and mode 8 engine order 60 in the fourth. It is also shown that the gradual loss of the stall margin over time determines the serviceability limits of compressor blades. In particular, the chord wear of sixth-stage blades as high as 6.19 mm results in a reduction of the stall margin by 15–17% and a permanent stall at 770–790 flight hours. In addition, recommendations setting out go/no-go criteria are made to maintenance and repair organizations. Full article
(This article belongs to the Special Issue 9th EASN International Conference on Innovation in Aviation & Space)
►▼ Show Figures

Figure 1

14 pages, 1136 KiB  
Article
Predesign Considerations for the DC Link Voltage Level of the CENTRELINE Fuselage Fan Drive Unit
by Stefan Biser, Guido Wortmann, Swen Ruppert, Mykhaylo Filipenko, Mathias Noe and Martin Boll
Aerospace 2019, 6(12), 126; https://doi.org/10.3390/aerospace6120126 - 20 Nov 2019
Cited by 12 | Viewed by 7947
Abstract
Electric propulsion (EP) systems offer considerably more degrees of freedom (DOFs) within the design process of aircraft compared to conventional aircraft engines. This requires large, computationally expensive design space explorations (DSE) with coupled models of the single components to incorporate interdependencies during optimization. [...] Read more.
Electric propulsion (EP) systems offer considerably more degrees of freedom (DOFs) within the design process of aircraft compared to conventional aircraft engines. This requires large, computationally expensive design space explorations (DSE) with coupled models of the single components to incorporate interdependencies during optimization. The purpose of this paper is to exemplarily study these interdependencies of system key performance parameters (KPIs), e.g., system mass and efficiency, for a varying DC link voltage level of the power transmission system considering the example of the propulsion system of the CENTRELINE project, including an electric motor, a DC/AC inverter, and the DC power transmission cables. Each component is described by a physically derived, analytical model linking specific subdomains, e.g., electromagnetics, structural mechanics and thermal analysis, which are used for a coupled system model. This approach strongly enhances model accuracy and simultaneously keeps the computational effort at a low level. The results of the DSE reveal that the system KPIs improve for higher DC link voltage despite slightly inferior performance of motor and inverter as the mass of the DC power transmission cable has a major share for a an aircraft of the size as in the CENTRELINE project. Modeling of further components and implementation of optimization strategies will be part of future work. Full article
(This article belongs to the Special Issue 9th EASN International Conference on Innovation in Aviation & Space)
►▼ Show Figures

Figure 1

Show export options expand_more Show export options expand_less
Select all
Export citation of selected articles as:
 
Displaying articles 1-9
Back to TopTop