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Aerospace
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Current Trend of High Temperature and Pressure Materials in Hypersonic...
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Current Trend of High Temperature and Pressure Materials in Hypersonic Vehicles

A special issue of Aerospace (ISSN 2226-4310). This special issue belongs to the section "Aeronautics".

Deadline for manuscript submissions: 31 December 2024 | Viewed by 1842

Special Issue Editors

Dr. Ikhyun Kim

E-Mail Website
Guest Editor
Department of Mechanical Engineering, Keimyung University, Daegu 42601, Republic of Korea
Interests: shock waves; nanotechnology
Dr. Yosheph Yang

E-Mail Website
Guest Editor
Department of Mechanical and Biomedical Engineering, Kangwon National University, 1, Kangwondaehak-Gil, Chuncheon, 24341, Republic of Korea
Interests: hypersonic flow; numerical methods, thermochemical nonequilibrium

Special Issue Information

Dear Colleagues,

High-temperature and -pressure materials are important for aerospace applications, where their primary function is to endure and disperse the extreme forces and temperatures produced by shock waves during high-speed flight and supersonic travel. In materials science and aerospace research, shock wave recovery in materials, particularly solids, is a relatively novel technique to determine the stability of the materials’ properties under dynamic high-pressure and -temperature conditions. Typically characterized by their exceptional high-temperature resistance, superior strength, and lightweight attributes, high-temperature and high-pressure materials find their utilization in critical aerospace components like heat shields, nose cones, and leading edges. Finding new materials that can maintain their function under high-speed and high-pressure conditions is essential for enhancing the performance of hypersonic vehicles.

Materials scientists have been drawn to the behavior changes induced by shock waves in crystalline and non-crystalline materials. Understanding the interaction of these materials with shock waves is essential for developing new advanced high-temperature materials. This Special Issue aims to provide the current state of engineering technology as well as fundamental concepts for a thorough understanding of the complex physics of dynamic waves on high-temperature materials for aerospace applications. Therefore, we can benefit from this newly released Special Issue that explores the subject of shock wave interactions with materials. We believe this Special Issue will inspire scientists to broaden the scope of their shock wave research and provide beneficial insights into the application of shock waves on materials and their systems.

Dr. Ikhyun Kim
Dr. Yosheph Yang
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

  • shock waves
  • high-temperature material
  • hypersonic flow
  • material–environment interaction

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Published Papers (3 papers)

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Research

14 pages, 7909 KiB  
Article
Investigation of the Film Cooling Performance of Laminated SiCfSiC Composite Plates
by Zhaoguo Mi, Zhenhua Chen, Kanghe Jiang and Weihua Yang
Aerospace 2024, 11(8), 642; https://doi.org/10.3390/aerospace11080642 - 7 Aug 2024
Viewed by 270
Abstract
Silicon carbide fiber-reinforced silicon carbide matrix ceramic composites (SiCf/SiC) are extensively utilized in high-temperature resistant materials in the aerospace industry. This study investigated the influence of stacking structure on the performance of SiCf/SiC laminated composite plates with film cooling. [...] Read more.
Silicon carbide fiber-reinforced silicon carbide matrix ceramic composites (SiCf/SiC) are extensively utilized in high-temperature resistant materials in the aerospace industry. This study investigated the influence of stacking structure on the performance of SiCf/SiC laminated composite plates with film cooling. Initially, the thermal conductivity of cross-piled SiCf/SiC composites was determined using the laser flash analysis (LFA) method and differential scanning calorimetry (DSC) method. Subsequently, a representative volume element (RVE) model that reflected the stacking structure was established. The anisotropic thermal conductivity of the unidirectional SiCf/SiC layer was calculated using numerical methods and experimental results. Finally, numerical simulations were carried out to assess the film cooling effectiveness of various stacking sequences and layers. The results showed that the thermal conductivity values predicted by the RVE model for the laminated composite aligned well with the experimental results, and the unidirectional SiCf/SiC composite thermal conductivities at different temperatures were obtained. The stacking sequence impacted the temperature distribution near the film hole, with the [0-90-0] structure exhibiting a more pronounced effect on film cooling performance compared with the [0-90] and [0-90-90-0] structures. The performance of the film cooling in the laminated SiCf/SiC composites was consistent across all stacking layers [0-90]1, [0-90]2, and [0-90]3. The maximum difference in overall cooling efficiency was 1.7% between [0-90-0]1 and [0-90]1 and [0-90-90-0]1 Full article
(This article belongs to the Special Issue Current Trend of High Temperature and Pressure Materials in Hypersonic Vehicles)
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15 pages, 5067 KiB  
Article
High-Temperature DIC Deformation Measurement under High-Intensity Blackbody Radiation
by Seng Min Han and Nam Seo Goo
Aerospace 2024, 11(6), 479; https://doi.org/10.3390/aerospace11060479 - 17 Jun 2024
Viewed by 536
Abstract
During the high-speed flight of a vehicle in the atmosphere, surface friction with the air generates aerodynamic heating. The aerodynamic heating phenomenon can create extremely high temperatures near the surface. These high temperatures impact material properties and the structure of the aircraft, so [...] Read more.
During the high-speed flight of a vehicle in the atmosphere, surface friction with the air generates aerodynamic heating. The aerodynamic heating phenomenon can create extremely high temperatures near the surface. These high temperatures impact material properties and the structure of the aircraft, so thermal deformation measurement is essential in aerospace engineering. This paper revisits high-temperature deformation measurement using the digital image correlation (DIC) technique under high-intensity blackbody radiation with a precise speckle pattern fabrication and a heat haze reduction method. The effects of the speckle pattern on the DIC measurement have been thoroughly studied at room temperature, but high-temperature measurement studies have not reported such effects so far. We found that the commonly used methods to reduce the heat haze effect could produce incorrect results. Hence, we propose a new method to mitigate heat haze effects. An infrared radiation heater was employed to make an experimental setup that could heat a specimen up to 950 °C. First, we mitigated image saturation using a short-wavelength bandpass filter with blue light illumination, a standard procedure for high-temperature DIC deformation measurement. Second, we studied how to determine the proper size of the speckle pattern in a high-temperature environment. Third, we devised a reduction method for the heat haze effect. As proof of the effectiveness of our developed experimental method, we successfully measured the deformation of stainless steel 304 specimens from 25 °C to 800 °C. The results confirmed that this method can be applied to the research and development of thermal protection systems in the aerospace field. Full article
(This article belongs to the Special Issue Current Trend of High Temperature and Pressure Materials in Hypersonic Vehicles)
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14 pages, 10954 KiB  
Article
Cyclic Ablation Properties of C/SiC-ZrC Composites
by Hailang Ge, Lu Zhang, Huajun Zhang, Fang Wang, Xiguang Gao and Yingdong Song
Aerospace 2024, 11(6), 432; https://doi.org/10.3390/aerospace11060432 - 27 May 2024
Viewed by 642
Abstract
To reveal the ablation performance of C/SiC-ZrC composites under different ablation modes, C/SiC-ZrC composites were prepared using chemical vapor deposition, precursor infiltration, and pyrolysis. Single ablation and cyclic ablation tests were conducted on the C/SiC-ZrC composites using an oxyacetylene flame, in order to [...] Read more.
To reveal the ablation performance of C/SiC-ZrC composites under different ablation modes, C/SiC-ZrC composites were prepared using chemical vapor deposition, precursor infiltration, and pyrolysis. Single ablation and cyclic ablation tests were conducted on the C/SiC-ZrC composites using an oxyacetylene flame, in order to obtain ablation parameters, as well as macroscopic and microscopic ablation morphology for the different ablation modes. The results show that the linear ablation rate and mass ablation rate of different ablation modes decrease with increasing time. The linear ablation rate and mass ablation rate of cyclic ablation are 12% and 24.2% lower than those of single ablation. Within the same ablation time, the C/SiC-ZrC composites subjected to cyclic ablation exhibit shallower and more evenly distributed pits, caused by high-temperature airflow ablation. The material surface has a white oxide layer composed of SiO2 and ZrO2, and the carbon fibers inside are wrapped by oxide particles, enhancing the ablation resistance of C/SiC-ZrC composites. Full article
(This article belongs to the Special Issue Current Trend of High Temperature and Pressure Materials in Hypersonic Vehicles)
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