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Aerospace
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The 10th Anniversary of Aerospace: Advances in Aerospace Sciences...
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The 10th Anniversary of Aerospace: Advances in Aerospace Sciences and Technology

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

Deadline for manuscript submissions: 31 December 2024 | Viewed by 12638

Special Issue Editors

Prof. Dr. Konstantinos Kontis

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Guest Editor
School of Engineering, University of Glasgow, James Watt Building South, University Avenue, Glasgow G12 8QQ, Scotland, UK
Interests: aerodynamic technologies; flow and flight control systems; shock physics; aerospace design and optimization; flow diagnostics
Special Issues, Collections and Topics in MDPI journals
Prof. Dr. Sergey Leonov

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Guest Editor
Department of Aerospace and Mechanical Engineering, College of Engineering, University of Notre Dame, 109 Hessert Lab, Notre Dame, IN 46556, USA
Interests: experimental plasma aerodynamics; weakly ionized plasma generation; flow actuation by electrical discharges; plasma-assisted combustion; diagnostics of low-temperature plasma; hypersonics; aerothermodynamics; high-speed combustion
Special Issues, Collections and Topics in MDPI journals
Prof. Dr. Michael Schultz

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Guest Editor
Institute of Flight Systems, Bundeswehr University Munich, 85577 Neubiberg, Germany
Interests: air transportation; data-driven and model-based environments; predictive analysis; integrated airspace and airport management
Special Issues, Collections and Topics in MDPI journals
Prof. Dr. Paolo Tortora

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Guest Editor
Dipartimento di Ingegneria Industriale, Alma Mater Studiorum Università di Bologna, Bologna, Italy
Interests: small satellites; innovative spacecraft subsystems including the ground segment; planetary exploration with particular reference to radio science experiments
Special Issues, Collections and Topics in MDPI journals

Special Issue Information

Dear Colleagues,

The year 2024 marks the 10th anniversary of our journal and together, we have achieved many things. We received our 2nd impact factor in 2022 and became a Q1 journal with a monthly publication rate exceeding 100 articles, thereby increasing the significance of the journal in this field. We would like to take this opportunity to set up an anniversary collection to celebrate our success, which will feature papers (original research articles or comprehensive review papers) in aeronautics, astronautics and space, and air traffic and transportation. Highly experienced practitioners are welcome to contribute papers, highlighting the latest developments in their research area or a detailed summary of their own work. The submission deadline for this round of call for papers is 31 December 2024.

Thank you for your continuous support in the future and we look forward to your contributions.

Prof. Dr. Konstantinos Kontis
Prof. Dr. Sergey Leonov
Prof. Dr. Michael Schultz
Prof. Dr. Paolo Tortora
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.

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Published Papers (6 papers)

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Research

21 pages, 18364 KiB  
Article
Flow Structure behind Spanwise Pin Array in Supersonic Flow
by Philip A. Lax, Skye Elliott, Stanislav Gordeyev, Matthew R. Kemnetz and Sergey B. Leonov
Aerospace 2024, 11(1), 93; https://doi.org/10.3390/aerospace11010093 - 19 Jan 2024
Viewed by 1325
Abstract
This work focused on the experimental characterization of a complex flow structure behind a cross-flow array of cylindrical pins installed on the wall of a supersonic duct. This geometry simulates several common gas dynamic configurations, such as a supersonic mixer, a turbulence-generating grid, [...] Read more.
This work focused on the experimental characterization of a complex flow structure behind a cross-flow array of cylindrical pins installed on the wall of a supersonic duct. This geometry simulates several common gas dynamic configurations, such as a supersonic mixer, a turbulence-generating grid, or, to some extent, a grid fin. In this work, the instrumentation employed is essentially non-intrusive, including spanwise integrating techniques such as (1) fast schlieren visualization and (2) Shack–Hartmann wavefront sensors; and planar techniques, namely (3) acetone Mie scattering and (4) acetone planar laser-induced fluorescence. An analysis of the data acquired by these complementary methods allowed the reconstruction of a three-dimensional portrait of supersonic flow interactions with a discrete pin array, including the shock wave structure, forefront separation zone, shock-induced separation zone, shear layer, and the mixing zone behind the pins. The main objective of this activity was to use various visualization techniques to acquire essential details of a complex compressible flow in a wide range of temporal–spatial scales. Particularly, a fine structure in the supersonic shear layer generated by the pin tips was captured by a Mie scattering technique. Based on the available publications, such structures have not been previously identified or discussed. Another potential outcome of this work is that the details revealed could be utilized for adequate code validation in numerical simulations. Full article
(This article belongs to the Special Issue The 10th Anniversary of Aerospace: Advances in Aerospace Sciences and Technology)
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19 pages, 4607 KiB  
Article
A Methodology for Allocating Incremental Resources in Single-Airport Time Slots
by Shuce Wang, Minghua Hu, Zhening Chang and Xuhao Zhu
Aerospace 2023, 10(9), 772; https://doi.org/10.3390/aerospace10090772 - 31 Aug 2023
Cited by 1 | Viewed by 1612
Abstract
Air carriers shall not readily relinquish their held flight slots. In cases where the historical flight slot pool cannot be easily altered, a pressing need arises for an allocation method that can efficiently utilize the incremental resources of these time slots. This paper [...] Read more.
Air carriers shall not readily relinquish their held flight slots. In cases where the historical flight slot pool cannot be easily altered, a pressing need arises for an allocation method that can efficiently utilize the incremental resources of these time slots. This paper presents an integer planning model to address the efficient allocation of incremental airport time slot resources. The model considers the capacity of key resource nodes and flight waveforms as constraints to maximize the total incremental slots. Moreover, it considers the adaptation of strategic and tactical optimization. After conducting a case study using Beijing Capital International Airport for verification, the proposed model effectively reduces potential operational delays by 66.27% while adding 366 to 397-time slots. Notably, the model demonstrates remarkable delay reduction capabilities and can serve as a valuable decision-support tool for the incremental allocation of time slots. Full article
(This article belongs to the Special Issue The 10th Anniversary of Aerospace: Advances in Aerospace Sciences and Technology)
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21 pages, 20353 KiB  
Article
Airfoil Analysis and Optimization Using a Petrov–Galerkin Finite Element and Machine Learning
by Pedro Areias, Rodrigo Correia and Rui Melicio
Aerospace 2023, 10(7), 638; https://doi.org/10.3390/aerospace10070638 - 15 Jul 2023
Cited by 1 | Viewed by 2361
Abstract
For the analysis of low-speed incompressible fluid dynamics with turbulence around airfoils, we developed a finite element formulation based on a stabilized pressure and velocity formulation. To shape the optimization of bidimensional airfoils, this formulation is applied using machine learning (TensorFlow) and public [...] Read more.
For the analysis of low-speed incompressible fluid dynamics with turbulence around airfoils, we developed a finite element formulation based on a stabilized pressure and velocity formulation. To shape the optimization of bidimensional airfoils, this formulation is applied using machine learning (TensorFlow) and public domain global optimization algorithms. The goal is to maximize the lift-over-drag ratio by using the class-shape function transformation (CST) parameterization technique and machine learning. Specifically, we propose equal-order stabilized three-node triangles for the flow problem, standard three-node triangles for the approximate distance function (ADF) required in the turbulence stage, and stabilized three-node triangles for the Spalart–Allmaras turbulence model. The backward Euler time integration was employed. An implicit time-integration algorithm was adopted, and a solution was obtained using the Newton–Raphson method. This was made possible in the symbolic form via Mathematica with the AceGen package. Three benchmarks are presented, with Reynolds numbers up to 1×107, demonstrating remarkable robustness. After the assessment of the new finite element, we used machine learning and global optimization for four angles of attack to calculate airfoil designs that maximized CL/CD. Full article
(This article belongs to the Special Issue The 10th Anniversary of Aerospace: Advances in Aerospace Sciences and Technology)
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18 pages, 4063 KiB  
Article
Design of Aerospace Vehicles’ Thermal Protection Based on Heat-Insulating Materials with Optimal Structure
by Oleg M. Alifanov, Margarita O. Salosina, Sergey A. Budnik and Aleksey V. Nenarokomov
Aerospace 2023, 10(7), 629; https://doi.org/10.3390/aerospace10070629 - 12 Jul 2023
Cited by 7 | Viewed by 2485
Abstract
Highly porous open-cell carbon materials have great potential for use as high-temperature thermal insulation for space vehicles due to a unique combination of properties: low density, high rigidity, sufficient compressive strength, and low thermal conductivity. The physical properties of these materials essentially depend [...] Read more.
Highly porous open-cell carbon materials have great potential for use as high-temperature thermal insulation for space vehicles due to a unique combination of properties: low density, high rigidity, sufficient compressive strength, and low thermal conductivity. The physical properties of these materials essentially depend on their microstructure. This implies the possibility of constructing a new advanced technique for the optimal design of multilayer thermal protection systems for aerospace vehicles, taking into account the dependence of materials’ thermal properties on microstructure. The formulation of the optimization problem traditional to thermal design implies the determination of the layer thicknesses that provide a minimum specific mass of the thermal protection, subject to the specified constraints on the maximum temperatures in the layers. The novelty of this work lies in the fact that, along with the thickness of the layers, the design parameters include the cell diameter and porosity, which characterize the structure of highly porous cellular materials. The innovative part of the presented paper lies in the determination of cell diameter and the porosity of open-cell carbon foam together with the thickness of the layers for multilayer thermal insulation, ensuring the required operational temperature on the boundaries of the layers and a minimum of the total mass of the system. This article reveals new possibilities for using the numerical optimization method to determine the geometric parameters of the thermal protection system and the morphology of the materials used. A new methodology for designing heat-loaded structures based on the simultaneous selection of macro- and micro-parameters of the system is proposed. The basic principles of constructing an algorithm for designing a multilayer thermal protection system are outlined, taking into account the possibility of choosing the parameters of the highly porous materials’ structure. The reliability of the developed optimization method was verified by comparing the results of mathematical modeling with experimental data obtained for highly porous cellular materials with known microstructure parameters. Full article
(This article belongs to the Special Issue The 10th Anniversary of Aerospace: Advances in Aerospace Sciences and Technology)
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15 pages, 4798 KiB  
Article
A Tether System at the L1, L2 Collinear Libration Points of the Mars–Phobos System: Analytical Solutions
by Vladimir S. Aslanov and Daria V. Neryadovskaya
Aerospace 2023, 10(6), 541; https://doi.org/10.3390/aerospace10060541 - 5 Jun 2023
Cited by 1 | Viewed by 1724
Abstract
This paper is dedicated to identifying stable equilibrium positions of the tether systems attached to the L1 or L2 libration points of the Mars–Phobos system. The orbiting spacecraft deploying the tether is at the L1 or L2 libration point [...] Read more.
This paper is dedicated to identifying stable equilibrium positions of the tether systems attached to the L1 or L2 libration points of the Mars–Phobos system. The orbiting spacecraft deploying the tether is at the L1 or L2 libration point and is held at one of these unstable points by the low thrust of its engines. In this paper, the analysis is performed assuming that the tether length is constant. The equation of motion for the system in the polar reference frame is obtained. The stable equilibrium positions are found and the dependence of the tether angular oscillation period on the tether length is determined. An analytical solution in the vicinity of the stable equilibrium positions for small angles of deflection of the tether from the local vertical is obtained in Jacobi elliptic functions. The comparison of the numerical and analytical solutions for small angles of deflection is performed. The results show that the dependencies of the oscillation period on the length of the tether are fundamentally different for L1 and L2 points. Analytical expressions for the tether tension are derived, and the influence of system parameters on this force is investigated for static and dynamic cases. Full article
(This article belongs to the Special Issue The 10th Anniversary of Aerospace: Advances in Aerospace Sciences and Technology)
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31 pages, 11567 KiB  
Article
Low-Dimensional Models for Aerofoil Icing Predictions
by David Massegur, Declan Clifford, Andrea Da Ronch, Riccardo Lombardi and Marco Panzeri
Aerospace 2023, 10(5), 444; https://doi.org/10.3390/aerospace10050444 - 11 May 2023
Cited by 3 | Viewed by 1996
Abstract
Determining the aero-icing characteristics is key for safety assurance in aviation, but it may be a computationally expensive task. This work presents a framework for the development of low-dimensional models for application to aerofoil icing. The framework builds on: an adaptive sampling strategy [...] Read more.
Determining the aero-icing characteristics is key for safety assurance in aviation, but it may be a computationally expensive task. This work presents a framework for the development of low-dimensional models for application to aerofoil icing. The framework builds on: an adaptive sampling strategy to identify the local, nonlinear features across the icing envelope for continuous intermittent icing; a classic technique based on Proper Orthogonal Decomposition, and a modern Neural Network architecture. The extreme diversity in simulated ice shapes, from smooth and streamlined to rugged and irregular shapes, motivated the use of an unsupervised classification of the ice shapes. This allowed deploying the Proper Orthogonal Decomposition locally within each sub-region, sensibly improving the prediction accuracy over the global model. On the other hand, the Neural Network architecture and the convolutional auto-encoder were found insensitive to the complexity in ice shapes. A strong correlation was found to exist between the ice shape, resulting ice mass and aerodynamic performance of the iced aerofoil, both in terms of the average and variance. On average, rime ice causes a loss of maximum lift coefficient of 21.5% compared to a clean aerofoil, and the average ice thickness is 0.9% of the aerofoil chord. For glaze ice, the average loss of maximum lift coefficient is 46.5% and the average ice thickness is 2.1%. Glaze ice was also found to have three times more surface coverage than rime ice. Full article
(This article belongs to the Special Issue The 10th Anniversary of Aerospace: Advances in Aerospace Sciences and Technology)
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