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Aerospace
Special Issues
Advanced Aerospace Composite Materials and Smart Structures
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Advanced Aerospace Composite Materials and Smart Structures

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

Deadline for manuscript submissions: 31 December 2024 | Viewed by 4155

Special Issue Editor

Dr. Kyungil Kong

E-Mail Website
Guest Editor
Bristol Composites Institute, Department of Aerospace Engineering, University of Bristol, Queen’s Building, University Walk, Bristol BS8 1TR, UK
Interests: experimental mechanics; FRP composites; non-destructive evaluation; self-sensing; micromechanics; composite manufacturing
Special Issues, Collections and Topics in MDPI journals

Special Issue Information

Dear Colleagues,

Aerospace science and technology are increasingly dedicated to the advancement of high-performance structural composite materials and the integration of smart structures through cutting-edge manufacturing processes, meticulous material characterisations, and rigorous structural evaluations. Fibre-reinforced composites are considered paramount in propelling aerospace development forward, given their compatibility with a range of matrices, including polymers (both thermoset or thermoplastic), metals, and ceramics. This multidisciplinary approach encompasses research into structural and material interactions, emphasizing specific strength, stiffness, superior mechanical properties, and multifunctionality.

Smart composite structures are enablers for mitigating adverse environmental challenges and operational complexities (such as fatigue, damage tolerance, gust alleviation, humidity, and temperature). Thus, enhancing the performance of structural composites becomes imperative for improving manoeuvrability and enabling data-driven management. The next generation of technologies, including nano-techniques, self-healing materials, and renewable composite materials, is expected to make significant contributions to the sustainability of aerospace applications.

Research and technology in advanced aerospace composite materials and smart structures encompass various other areas, including multifunctionality, digital twin technology, life cycle assessment, self-healing mechanisms, predictive maintenance, maintenance repair and overhaul, non-destructive evaluation, and structural composite mechanics and simulation.

We cordially invite you to contribute to this Special Issue on advanced aerospace composite materials and smart structures. We also welcome studies related to non-destructive inspection methods, novel material characterisation and testing, and certification efforts that support the implementation of smart composite structures.

Members of the research community are welcome to contribute their research articles, reviews, and short communications on this Special Issue, titled Advanced Aerospace Composite Materials and Smart Structures.

I would like to thank Jason Hwang (NLR, Netherlands) for his significant contribution to this Special Issue.

Dr. Kyungil Kong
Guest Editor

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

  • experimental mechanics

  • smart structures
  • non-destructive inspection
  • renewable composites
  • digital twin
  • interphase (interface)
  • self-healing composites
  • structural health monitoring
  • composite manufacturing

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

Published Papers (4 papers)

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Research

21 pages, 35079 KiB  
Article
Energy Absorption Properties of 3D-Printed Polymeric Gyroid Structures for an Aircraft Wing Leading Edge
by Mats Overbeck, Sebastian Heimbs, Jan Kube and Christian Hühne
Aerospace 2024, 11(10), 801; https://doi.org/10.3390/aerospace11100801 - 29 Sep 2024
Viewed by 1075
Abstract
Laminar flow offers significant potential for increasing the energy efficiency of future transport aircraft. At the Cluster of Excellence SE2A—Sustainable and Energy-Efficient Aviation—the laminarization of the wing by means of hybrid laminar flow control (HLFC) is being investigated. The aim is [...] Read more.
Laminar flow offers significant potential for increasing the energy efficiency of future transport aircraft. At the Cluster of Excellence SE2A—Sustainable and Energy-Efficient Aviation—the laminarization of the wing by means of hybrid laminar flow control (HLFC) is being investigated. The aim is to maintain the boundary layer as laminar for up to 80% of the chord length of the wing. This is achieved by active suction on the leading edge and the rear part of the wing. The suction panels are constructed with a thin micro-perforated skin and a supporting open-cellular core structure. The mechanical requirements for this kind of sandwich structure vary depending on its position of usage. The suction panel on the leading edge must be able to sustain bird strikes, while the suction panel on the rear part must sustain bending loads from the deformation of the wing. The objective of this study was to investigate the energy absorption properties of a triply periodic minimal surface (TPMS) structure that can be used as a bird strike-resistant core in the wing leading edge. To this end, cubic-sheet-based gyroid specimens of different polymeric materials and different geometric dimensions were manufactured using additive manufacturing processes. The specimens were then tested under quasi-static compression and dynamic crushing loading until failure. It was found that the mechanical behavior was dependent on the material, the unit cell size, the relative density, and the loading rate. In general, the weight-specific energy absorption (SEA) at 50% compaction increased with increasing relative density. Polyurethane specimens exhibited an increase in SEA with increasing loading rate, as opposed to the specimens of the other investigated polymers. A smaller unit cell size induced a more consistent energy absorption, due to the higher plateau force. Full article
(This article belongs to the Special Issue Advanced Aerospace Composite Materials and Smart Structures)
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12 pages, 5873 KiB  
Article
Validation of Experimental Data for the Application of the Magnesium Alloy “Elektron 43”
by Michele Guida
Aerospace 2024, 11(9), 695; https://doi.org/10.3390/aerospace11090695 - 25 Aug 2024
Viewed by 658
Abstract
The behaviour of a structural component, such as the spreader installed on an aeroplane passenger seat made of the magnesium alloy Elektron® 43, is evaluated under a variety of load conditions. The purpose of this research project is to considerably reduce weight [...] Read more.
The behaviour of a structural component, such as the spreader installed on an aeroplane passenger seat made of the magnesium alloy Elektron® 43, is evaluated under a variety of load conditions. The purpose of this research project is to considerably reduce weight by employing the new alloy while keeping the strength and ductility necessary to meet the dynamic standards for both the 16 g forward and 14 g downward tests. A comprehensive campaign of static and dynamic testing on coupons was conducted to characterise the mechanical behaviour of the E43 magnesium alloy, from quasi-static to dynamic loading, and across a wide range of deformation rates. The elastic–plastic and strain rate sensitive material model of E43 is then calibrated using an FEA approach and LS-DYNA software, utilising stress–strain curves and properties determined from standardised experimental tensile and compression trials at varied strain rates. Finally, this material model was used to perform a finite element structural study of a major component of an aeroplane seat built using Elektron® 43 under typical in-flight stresses. Full article
(This article belongs to the Special Issue Advanced Aerospace Composite Materials and Smart Structures)
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20 pages, 4106 KiB  
Article
Thermally Induced Vibration of a Flexible Plate with Enhanced Active Constrained Layer Damping
by Yueru Guo, Yongbin Guo, Yongxin Zhang, Liang Li, Dingguo Zhang, Sijia Chen and Mohamed A. Eltaher
Aerospace 2024, 11(7), 504; https://doi.org/10.3390/aerospace11070504 - 23 Jun 2024
Cited by 1 | Viewed by 720
Abstract
When spacecraft execute missions in space, their solar panels—crucial components—often need to be folded, unfolded, and adjusted at an angle. These operations can induce numerous detrimental nonlinear vibrations. This paper addresses the issues of nonlinear and thermal-coupled vibration control within the context of [...] Read more.
When spacecraft execute missions in space, their solar panels—crucial components—often need to be folded, unfolded, and adjusted at an angle. These operations can induce numerous detrimental nonlinear vibrations. This paper addresses the issues of nonlinear and thermal-coupled vibration control within the context of space-based flexible solar panel systems. Utilizing piezoelectric smart hybrid vibration control technology, this study focuses on a flexible plate augmented with an active constrained layer damping. The solar panel, under thermal field conditions, is modeled and simulated using the commercial finite element simulation software ABAQUS. The research examines variations in the modal frequencies and damping properties of the model in response to changes in the coverage location of the piezoelectric patches, their coverage rate, rotational angular velocity, and the thickness of the damping layer. Simulation results indicate that structural damping is more effective when the patches are closer to the rotation axis, the coverage area of the patches is larger, the rotational speed is lower, and the damping layer is thicker. Additionally, the effectiveness of vibration suppression is influenced by the interplay between the material shear modulus, loss factor, and specific working temperature ranges. The selection of appropriate parameters can significantly alter the system’s vibrational characteristics. This work provides necessary technical references for the analysis of thermally induced vibrations in flexible solar sails under complex space conditions. Full article
(This article belongs to the Special Issue Advanced Aerospace Composite Materials and Smart Structures)
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19 pages, 16327 KiB  
Article
Experimental Investigation of the Mechanical Behavior of the Strain Isolation Pad in Thermal Protection Systems under Tension
by Maoxu Lu, Zhenqiang Wu, Ziqing Hao and Liu Liu
Aerospace 2024, 11(4), 305; https://doi.org/10.3390/aerospace11040305 - 12 Apr 2024
Viewed by 1113
Abstract
A strain isolation pad is a critical connection mechanism that enables deformation coordination between the rigid thermal insulation tile and the primary structure in the thermal protection system of a reusable hypersonic vehicle. An experimental investigation has been conducted to determine the static, [...] Read more.
A strain isolation pad is a critical connection mechanism that enables deformation coordination between the rigid thermal insulation tile and the primary structure in the thermal protection system of a reusable hypersonic vehicle. An experimental investigation has been conducted to determine the static, loading–unloading, and high-cycle fatigue (HCF) responses of the SIP with 0.2 mm adhesive under through-thickness tension at room temperature. The contributions of the rigid thermal insulation tile and metallic substructure have not been considered so far. The results indicate that the tensile behavior of the SIP joint is highly nonlinear. The static and fatigue tensile failures both initiate from the corner close to the adhesive/SIP interface due to the stress concentration and the edge effect. The uniform breakage of the aramid fiber can be seen on the cross-section. A novel method is proposed to quantify the residual strain due to the short-time ratcheting effect of the SIP joint in the initial loading–unloading tensile response. As the number of fatigue cycles increases, the thickness of the SIP joint continues to increase until failure. An explicit expression associated with the growth of SIP joint thickness, fatigue cycle number, and peak cyclic stress is established. The turning point of the thickness growth rate with the fatigue cycle number is proposed as a new fatigue failure index for the SIP joint under tensile fatigue, and a fatigue life prediction model is developed. Full article
(This article belongs to the Special Issue Advanced Aerospace Composite Materials and Smart Structures)
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