Relevant bibliographies by topics / UHTCMCs

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  1. Journal articles
  2. Dissertations / Theses
  3. Book chapters
  4. Conference papers

Academic literature on the topic 'UHTCMCs'

Author: Grafiati
Published: 5 June 2025
Last updated: 8 July 2025

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Journal articles on the topic "UHTCMCs"

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Tsuganezawa, Mizuki, Yutaro Arai, and Ryo Inoue. "Thermodynamic Analysis on Complex Oxides Formed by Aerodynamic Heating for Ultrahigh-Temperature Ceramic Matrix Composites." Journal of Composites Science 9, no. 2 (2025): 87. https://doi.org/10.3390/jcs9020087.

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The oxidation and recession of carbon-fiber-reinforced ultrahigh-temperature ceramic matrix composites (C/UHTCMCs) fabricated via reactive melt infiltration (RMI) using Zr-Ti alloys with three different compositions are evaluated via an arc-jet tunnel test at temperatures above 2000 °C for 60 s. Thermodynamic evaluations show that the recession of the UHTCMCs is prevented by the formation of a solid solution of ZrTiO4 on their exposed surface. Because an increase in the Zr content increases the melting temperature of ZrTiO4, the recession of the composites increases as the Zr content in the infiltrated alloys decreases. UHTCMCs fabricated with Zr-20at%Ti showed the least recession (<5%).
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Sciti, Diletta, Pietro Galizia, Thomas Reimer, et al. "Properties of large scale ultra-high temperature ceramic matrix composites made by filament winding and spark plasma sintering." Composites Part B: Engineering 216 (July 1, 2021): 108839. https://doi.org/10.1016/j.compositesb.2021.108839.

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In this paper, for the first time, we report the manufacturing and characterization of large&nbsp;UHTCMCs&nbsp;discs, made of a ZrB<sub>2</sub>/SiC matrix reinforced with PyC-coated PAN-based carbon fibres. This work was the result of a long term collaboration between different institutions and shows how it is possible to scale-up the production process of UHTCMCs for the fabrication of large components. 150&nbsp;mm large discs were produced by filament winding and consolidated by&nbsp;spark plasma sintering&nbsp;and specimens were machined to test a large set of&nbsp;material properties&nbsp;at room and elevated temperature (up to 1800&nbsp;&deg;C). The extensive characterization revealed a new material with&nbsp;mechanical behaviour&nbsp;similar to CMCs, but with intrinsic higher thermal stability. Furthermore, the scale-up demonstrated in this work increases the appeal of UHTCMCs in sectors such as aerospace, where severe operating conditions limit the application of conventional materials.
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Venkatachalam, Vinothini, Sergej Blem, Ali Gülhan, and Jon Binner. "Thermal Qualification of the UHTCMCs Produced Using RF-CVI Technique with VMK Facility at DLR." Journal of Composites Science 6, no. 1 (2022): 24. http://dx.doi.org/10.3390/jcs6010024.

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Ultra high-temperature ceramic matrix composites (UHTCMCs) based on carbon fibre (Cf) have been shown to offer excellent temperature stability exceeding 2000 °C in highly corrosive environments, which are prime requirements for various aerospace applications. In C3Harme, a recent European Union-funded Horizon 2020 project, an experimental campaign has been carried out to assess and screen a range of UHTCMC materials for near-zero ablation rocket nozzle and thermal protection systems. Samples with ZrB2-impregnated pyrolytic carbon matrices and 2.5D woven continuous carbon fibre preforms, produced by slurry impregnation and radio frequency aided chemical vapour infiltration (RF-CVI), were tested using the vertical free jet facility at DLR, Cologne using solid propellants. When compared to standard CVI, RFCVI accelerates pyrolytic carbon densification, resulting in a much shorter manufacturing time. The samples survived the initial thermal shock and subsequent surface temperatures of &gt;2000 °C with a minimal ablation rate. Post-test characterisation revealed a correlation between surface temperature and an accelerated catalytic activity, which lead to an understanding of the crucial role of preserving the bulk of the sample.
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Galizia, Pietro, Antonio Vinci, Luca Zoli, et al. "Retained strength of UHTCMCs after oxidation at 2278 K." Composites Part A: Applied Science and Manufacturing 149 (October 2021): 106523. http://dx.doi.org/10.1016/j.compositesa.2021.106523.

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Galizia, Pietro, Simone Failla, Luca Zoli, and Diletta Sciti. "Tough salami-inspired Cf/ZrB2 UHTCMCs produced by electrophoretic deposition." Journal of the European Ceramic Society 38, no. 2 (2018): 403–9. http://dx.doi.org/10.1016/j.jeurceramsoc.2017.09.047.

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Sciti, Diletta, Luca Zoli, Thomas Reimer, Antonio Vinci, and Pietro Galizia. "A systematic approach for horizontal and vertical scale up of sintered Ultra-High Temperature Ceramic Matrix Composites for aerospace – Advances and perspectives." Composites Part B: Engineering 234 (April 1, 2022): 109709. https://doi.org/10.1016/j.compositesb.2022.109709.

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Ultra-High Temperature&nbsp;Ceramic Matrix Composites&nbsp;(UHTCMCs) are the next generation composites developed for application in the harsh environment of aerospace. Qualification of these materials requires the manufacturing of demonstrators for testing in relevant environments, which in turn, requires to scale them up. This paper illustrates the systematic approach adopted for the scale-up of UHTCMCs based on carbon fibre reinforced&nbsp;zirconium&nbsp;diboride plus&nbsp;silicon&nbsp;carbide from laboratory to industrial scale dimensions. The scale-up process covered a period of three years and concerned an increase in diameter of &sim;10 times (from 40 to 400&nbsp;mm), and in thickness of &sim;30 times (from 5 to 160&nbsp;mm). Small-scale products were consolidated by hot pressing at ISTEC whilst larger samples were consolidated by an industrial&nbsp;spark plasma sintering&nbsp;facility (NanokerResearch, Spain). After each scale-up step, reproducibility of composition, microstructure and properties was carefully checked. Thanks to the homogenous fibre distribution and sapient dosing of secondary phases, composites with different diameters and thickness were successfully consolidated by both techniques with little adjustment of sintering parameters up to the maximum size of available&nbsp;industrial furnaces. The large discs produced allowed production of 170&nbsp;mm long bars for&nbsp;tensile testing&nbsp;and large tiles for hypersonic&nbsp;wind tunnel tests. Thick samples were useful to machine complex shapes such as screws and nuts, vertical bars for characterization of properties along the composite thickness and nozzle demonstrators.
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Zoli, Luca, Antonio Vinci, Pietro Galizia, Carlos F. Gutièrrez-Gonzalez, Sergio Rivera, and Diletta Sciti. "Is spark plasma sintering suitable for the densification of continuous carbon fibre - UHTCMCs?" Journal of the European Ceramic Society 40, no. 7 (2020): 2597–603. http://dx.doi.org/10.1016/j.jeurceramsoc.2019.12.004.

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Vinci, Antonio, Luca Zoli, Diletta Sciti, Cesare Melandri, and Stefano Guicciardi. "Understanding the mechanical properties of novel UHTCMCs through random forest and regression tree analysis." Materials & Design 145 (May 2018): 97–107. http://dx.doi.org/10.1016/j.matdes.2018.02.061.

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Servadei, Francesca, Luca Zoli, Pietro Galizia, Antonio Vinci, and Diletta Sciti. "Development of UHTCMCs via water based ZrB2 powder slurry infiltration and polymer infiltration and pyrolysis." Journal of the European Ceramic Society 40, no. 15 (2020): 5076–84. http://dx.doi.org/10.1016/j.jeurceramsoc.2020.05.054.

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Binner, Jon, Matt Porter, Ben Baker, et al. "Selection, processing, properties and applications of ultra-high temperature ceramic matrix composites, UHTCMCs – a review." International Materials Reviews 65, no. 7 (2019): 389–444. http://dx.doi.org/10.1080/09506608.2019.1652006.

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Dissertations / Theses on the topic "UHTCMCs"

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UHLMANN, FRANZISKA JOHANNA LUISE. "Protective Ultra-High Temperature Coatings/ Ceramics (UHTCs) for Ceramic Matrix Composites in Extreme Environments." Doctoral thesis, Politecnico di Torino, 2016. http://hdl.handle.net/11583/2644372.

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This thesis is focused on the development of a protective coating system for Cf/SiC SiCARBONTM (Airbus trademark) materials against very high temperatures in extreme environment. Here, we concentrate on the application of this technology in combustion chambers, for example in orbital thrusters. During combustion, the composite material needs to be protected against oxidation caused by the extreme conditions. With the aim to increase the combustion performance using higher temperatures (up to 1850 °C), this thesis deals with the replacement of the current Environmental Barrier Coating (EBC) solution (CVD-SiC coating, Chemical Vapor Deposition) by an Ultra High Temperature Ceramic (UHTC) based coating system. Different challenges of this approach are, for instance, the CTE mismatch between Cf/SiC and UHTC materials and the feasibility to create a dense, thick and adherent UHTC based coating on the hot gas wall (inner wall) of a small combustion chamber. In this work, a suitable coating process (High Performance Plasma Coating process, HPPC) for inner wall coatings is selected and further developed to create ZrB2 based coatings on Cf/SiC based substrate materials. Based on a parameter study, the coating quality of HPPC based ZrB2 coatings is optimized depending on plasma current, chamber pressure, powder flow rate, preheating and cooling rate. HPPC coatings with different material combinations (ZrB2, ZrB2-SiC, ZrB2-TaC, ZrB2-LaB6) are investigated regarding coating adhesion, voids, composition and thermo-chemical behavior within a combustion chamber-like environment. To decrease the CTE mismatch between Cf/SiC substrate and a ZrB2 based coating and to increase the thermo-chemical resistance of the composite, the SiC matrix material is modified by ZrB2 and Ta additions. Cf/SiC-ZrB2-TaC composites with different SiC/ZrB2-TaC ratios are fabricated and investigated regarding microstructure, chemical composition and material properties (physical, thermo-physical, mechanical and thermo-chemical). The adhesion of HPPC based ZrB2 coatings on Cf/SiC composites is enhanced by a ZrB2 and TaC matrix modification. Based on the results, interactions between process parameters, coating composition and substrate material are analyzed and provide the base for ZrB2 based EBCs of the inner wall coatings on Cf/SiC based components. By means of the obtained findings, the potential of several material systems is derived in order to develop a protective coating for long-term applications in combustion chamber environments.
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Foroughi, Paniz. "Synthesis & Fundamental Formation Mechanism Study of High Temperature & Ultrahigh Temperature Ceramics." FIU Digital Commons, 2018. https://digitalcommons.fiu.edu/etd/3730.

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Borides and carbides of tantalum and hafnium are of great interest due to their ultrahigh temperature applications. Properties of these ceramics including oxidation resistance and mechanical properties might be further improved through solid solution/composite formation. Synthesis of single-phase TaxHf1-xC and TaxHf1-xB2 solid solution powders including nanopowders via carbothermal reduction (CTR) is complicated due to noticeable difference in reactivity of parent oxides with carbon, and also the low solubility of those oxides in each other. Moreover, for TaC-HfC system the solid solution may go through phase separation due to the presence of a miscibility gap at temperatures below 887°C.In this study, a method of low-cost aqueous solution processing followed by CTR was used to synthesize TaxHf1-xC and TaxHf1-xB2 solid solution powders. In fact, method was first used to synthesize boron carbide (B4C) powders as it paves the way for a detailed study on the synthesis of TaxHf1-xC and TaxHf1-xB2 solid solutions powders considering the fact that B4C contains both carbon and boron in its structure. Particular emphasis was given to investigate the influences of starting compositions and processing conditions on phase separation during the formation of both carbide and boride phase(s). It was found that individual TaC-HfC and TaB2-HfB2 phases always form quickly but separately during the CTR process (e.g., at 1600 °C within a few minutes). Those carbides and borides remain phase-separated unless heated to much higher temperatures for long time due to the slow inter-diffusion between them. It was also found that for TaxHf1-xC applying a DC electric field through the use of spark plasma sintering (SPS) system significantly accelerates the inter-diffusion of Ta and Hf leading to formation of a single-phase TaxHf1-xC solid solution at 1600 °C for 15 minutes. On the other hand, for borides alkali metal reduction reaction (AMR) method appears to be an excellent alternative to CTR-based method for formation of a single-phase TaxHf1-xB2 solid solution. In this method, chlorides of tantalum and hafnium are directly reduced using sodium borohydride (NaBH4) giving rise to formation of a single-phase Ta0.5Hf0.5B2 solid solution nanopowders in one step at much lower temperatures (e.g., 700 °C) by avoiding the oxides formation and the associated phase separation of individual borides as observed in the CTR-based process.
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Da, Rold Guillaume. "Catalycité et vieillissement des matériaux à haute technicité. Etude des barrières de diffusion vis-à-vis de l'oxygène." Phd thesis, 2009. http://pastel.archives-ouvertes.fr/pastel-00006059.

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Lors de la rentrée atmosphérique, la protection thermique d'un véhicule spatial est soumise à un plasma d'air. Le transfert de l'énergie cinétique de l'oxygène atomique à la surface conduit à une importante élévation de température. L'énergie libérée lors de la recombinaison de l'oxygène atomique provoque une élévation de température supplémentaire. Cet excès de température endommage la protection thermique. Cette étude a pour objectif de comprendre les transferts de matière (coefficient de recombinaison γ) et de chaleur (coefficient d'accommodation β) mis en jeu lors de cette rentrée atmosphérique. Ces phénomènes sont quantifiables par la mesure de la catalycité. Ces mesures seront réalisées sur des oxydes semi-conducteurs de type n jusqu'à 1100 K, avec pour objectif de réduire la recombinaison de l'oxygène atomique. Cette dernière conduit à l'oxydation de la surface et à un vieillissement accéléré de la surface. En effet grâce à l'utilisation de l'oxygène isotopique couplée à la spectrométrie de masse, les phénomènes d'oxydation (active et passive), d'ablation et de diffusion de l'oxygène à cœur ont été identifiés. A l'aide d'analyses SIMS, une cinétique de diffusion de l'oxygène sera établie dans ce genre de couche afin de tester leur effet barrière. Un nouveau genre de dépôt (UHTCs) possédant des propriétés de résistance à l'oxydation et de barrière de diffusion, sera également soumis à différents traitements thermiques (jusqu'à 1500 K). Enfin cette étude sera complétée par des simulations de recombinaison de l'oxygène atomique à l'aide du code de calcul Chemkin®.
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Book chapters on the topic "UHTCMCs"

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Huang, Zhenkun, and Laner Wu. "Ultrahigh-Temperature Ceramics (UHTCs) Systems." In Phase Equilibria Diagrams of High Temperature Non-oxide Ceramics. Springer Singapore, 2018. http://dx.doi.org/10.1007/978-981-13-0463-7_4.

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Neuman, Eric W., and Greg E. Hilmas. "Mechanical Properties of Zirconium-Diboride Based UHTCs." In Ultra-High Temperature Ceramics. John Wiley & Sons, Inc, 2014. http://dx.doi.org/10.1002/9781118700853.ch8.

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Zhang, Guo Jun, Wen Wen Wu, Yan Mei Kan, and Pei Ling Wang. "Ultra-High Temperature Ceramics (UHTCs) via Reactive Sintering." In Key Engineering Materials. Trans Tech Publications Ltd., 2007. http://dx.doi.org/10.4028/0-87849-410-3.1159.

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Wang, J., and L. J. Vandeperre. "Deformation and Hardness of UHTCs as a Function of Temperature." In Ultra-High Temperature Ceramics. John Wiley & Sons, Inc, 2014. http://dx.doi.org/10.1002/9781118700853.ch10.

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Ionescu, Emanuel, Samuel Bernard, Romain Lucas, et al. "Polymer-Derived Ultra-High Temperature Ceramics (UHTCs) and Related Materials." In PoliTO Springer Series. Springer International Publishing, 2021. http://dx.doi.org/10.1007/978-3-030-85776-9_9.

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Wang, Zhen, Shaoming Dong, Le Gao, Xiangyu Zhang, Yusheng Ding, and Ping He. "Fabrication of Carbon Fiber Reinforced Ultrahigh Temperature Ceramics (UHTCs) Matrix Composite." In Ceramic Transactions Series. John Wiley & Sons, Inc., 2010. http://dx.doi.org/10.1002/9780470930953.ch8.

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Parthasarathy, Triplicane A., Michael K. Cinibulk, and Mark Opeka. "Modeling and Evaluating the Environmental Degradation of UHTCs under Hypersonic Flow." In Ultra-High Temperature Ceramics. John Wiley & Sons, Inc, 2014. http://dx.doi.org/10.1002/9781118700853.ch11.

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Ott, Catherine, and Ian McCue. "The Morphological and Compositional Stability of Nanoporous UHTCs During Fabrication from Metallic Precursors." In The Minerals, Metals & Materials Series. Springer Nature Switzerland, 2025. https://doi.org/10.1007/978-3-031-80664-3_3.

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Orrù, Roberto, and Giacomo Cao. "Self-Propagating High-Temperature Synthesis (SHS) and Spark Plasma Sintering (SPS) of Zr-, Hf-, and Ta-Based Ultra-High Temperature Ceramics." In MAX Phases and Ultra-High Temperature Ceramics for Extreme Environments. IGI Global, 2013. http://dx.doi.org/10.4018/978-1-4666-4066-5.ch009.

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The identification of efficient techniques for the fabrication of Ultra High Temperature Ceramics (UHTCs) is very crucial in view of their rapid and wider development. Along these lines, the use of the self-propagating high-temperature synthesis (SHS) technique in combination with the SPS technology is examined in this chapter for the obtainment of fully dense MB2-SiC and MB2-MC-SiC (M=Zr, Hf, Ta) ceramics. The starting reactants are first processed by SHS to successfully form the desired composites. The resulting powders are subsequently consolidated by spark-plasma sintering (SPS). Bulk products with relative densities = 96% can be obtained within 30 minutes, when the dwell temperature is 1800 °C and P=20 MPa. Hardness, fracture toughness, and oxidation resistance of the obtained dense bodies are comparable to, and in some cases superior than, those reported for analogous products synthesized using alternative routes. Possible future developments of this approach with the final purpose of obtaining whiskers/fibers reinforced UHTCs are finally discussed.
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Silvestroni, Laura, and Diletta Sciti. "Effect of Transition Metal Silicides on Microstructure and Mechanical Properties of Ultra-High Temperature Ceramics." In MAX Phases and Ultra-High Temperature Ceramics for Extreme Environments. IGI Global, 2013. http://dx.doi.org/10.4018/978-1-4666-4066-5.ch005.

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The IV and V group transition metals borides, carbides, and nitrides are widely known as ultra-high temperature ceramics (UHTCs), owing to their high melting point above 2500°C. These ceramics possess outstanding physical and engineering properties, such as high hardness and strength, low electrical resistivity and good chemical inertness which make them suitable structural materials for applications under high heat fluxes. Potential applications include aerospace manufacturing; for example sharp leading edge parts on hypersonic atmospheric re-entry vehicles, rocket nozzles, and scramjet components, where operating temperatures can exceed 3000°C. The extremely high melting point and the low self-diffusion coefficient make these ceramics very difficult to sinter to full density: temperatures above 2000°C and the application of pressure are necessary conditions. However these processing parameters lead to coarse microstructures, with mean grain size of the order of 20 µm and trapped porosity, all features which prevent the achievement of the full potential of the thermo-mechanical properties of UHTCs. Several activities have been performed in order to decrease the severity of the processing conditions of UHTCs introducing sintering additives, such as metals, nitrides, carbides or silicides. In general the addition of such secondary phases does decrease the sintering temperature, but some additives have some drawbacks, especially during use at high temperature, owing to their softening and the following loss of integrity of the material. In this chapter, composites based on borides and carbides of Zr, Hf and Ta were produced with addition of MoSi2 or TaSi2. These silicides were selected as sintering aids owing to their high melting point (&gt;2100°C), their ductility above 1000°C and their capability to increase the oxidation resistance. The microstructure of fully dense hot pressed UHTCs containing 15 vol% of MoSi2 or TaSi2, was characterized by x-ray diffraction, scanning, and transmission electron microscopy. Based on microstructural features detected by TEM, thermodynamical calculations, and the available phase diagrams, a densification mechanism for these composites is proposed. The mechanical properties, namely hardness, fracture toughness, Young’s modulus and flexural strength at room and high temperature, were measured and compared to the properties of other ultra-high temperature ceramics produced with other sintering additives. Further, the microstructural findings were used to furnish possible explanations for the excellent high temperature performances of these composites.
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Conference papers on the topic "UHTCMCs"

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Airoldi, Alessandro, Diletta Sciti, Lorenzo Cavalli, et al. "Numerical and Experimental Approach for the Design of CMC and UHTCMC Reusable Structures: Results of AM3aC2A Project." In IAF Materials and Structures Symposium, Held at the 75th International Astronautical Congress (IAC 2024). International Astronautical Federation (IAF), 2024. https://doi.org/10.52202/078369-0167.

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VINCI, ANTONIO, LUCA ZOLI, PIETRO GALIZIA, et al. "FABRICATION AND CHARACTERIZATION OF UHTCMCS." In Thirty-sixth Technical Conference. Destech Publications, Inc., 2021. http://dx.doi.org/10.12783/asc36/35776.

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The materials currently used in aerospace and aviation, such as C/C and C/SiC composites, possess excellent mechanical properties but are limited to a maximum operational temperature of 1600°C (C/SiC) and poorly oxidizing environments (C/C). For more demanding applications, new materials able to withstand extreme temperatures without recession are required. In the framework of the C3harme project, a new class of materials labelled UHTCMCs, consisting of a UHTC matrix reinforced with carbon fibers, has been developed and characterized in order to overcome these challenges. Different fiber reinforcements and sintering parameters have been investigated from the microstructural point of view. The composites were fabricated via slurry infiltration of fiber, using a powder mixture of ZrB2 and SiC; the green pellets were then sintered via hot pressing. Extensive microstructural analysis was carried out on the sintered samples, showing how the sintering parameters and the choice of the fibers are crucial to obtain full densification without jeopardizing the fibers integrity and permit adequate load transfer.
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VENKATACHALAM,, VINOTHINI, JON BINNER, THOMAS REIMER, BUCKARD ESSER, STEFANO MUNGIGUERRA, and RAFFAELE SAVINO. "PROCESSING OF ULTRA-HIGH TEMPERATURE CERAMIC MATRIX COMPOSITES (UHTCMCS) THROUGH RF ENHANCED CHEMICAL VAPOUR INFILTRATION (RF-CVI)." In Thirty-sixth Technical Conference. Destech Publications, Inc., 2021. http://dx.doi.org/10.12783/asc36/35775.

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Carbon fibre (Cf) reinforced Ultra High Temperature Ceramic (UHTC) Matrix Composites (UHTCMCs) have proven to be excellent materials that can survive nearly 3000°C in highly oxidizing environments along with a good specific strength. Consequently, they have excellent potential for use in aerospace applications such as rocket nozzle throats and thermal protection systems (TPS). Due to the presence of the carbon fibres, UHTCMCs offer high strength and modulus combined with excellent thermal shock behaviour whilst the presence of the ultra-high temperature ceramic phase protects the carbon fibres at the application temperatures. High temperature oxidation, thermal ablation behaviour and mechanical properties of the UHTCMC’s relies heavily on the bonding between the carbon fibre and matrices especially the oxides formed to avoid any progressive failure and predict the life of the components. In the present investigation, a radio frequency assisted chemical vapor infiltration (RF-CVI) technique has been used to make the 2.5D Cf reinforced ZrB2, ZrB2/carbon matrices composites with various interphase materials. The advantage of RF heating is that it creates an inverse temperature profile in the sample, which means that the infiltration starts from inside and progresses outwards. This allows the time needed for processing to be reduced very significantly compared to the conventional CVI process. This presentation will report on the latest results from the research that has been undertaken at the University of Birmingham, including the results from a wide range of testing that has been undertaken at both DLR in Germany and the University of Naples in Italy.
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ZOLI, LUCA, and DILETTA SCITI. "INTRODUCTION TO C3HARME PROJECT." In Thirty-sixth Technical Conference. Destech Publications, Inc., 2021. http://dx.doi.org/10.12783/asc36/35777.

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High-speed aviation brings many challenges, one being the materials used ensure the aircraft and rockets travelling at hypersonic speed arrive at their destination safely. Control surfaces and thermal protection systems for vehicles flying at Mach 5 or above must withstand extremely hot temperatures and intense mechanical vibrations at launch, during cruising and re-entry into the Earth’s atmosphere. UHTCMCs (Ultra-High Temperature Ceramic Matrix Composites) belong to a new subclass of ceramic matrix composites (CMCs) with superior properties in terms of structural and chemical stability at elevated temperature and erosion/ablation resistance keeping excellent strength-to-weight ratio, thermal shock resistance and adequate damage tolerance. They are the latest potential candidates for thermal protection systems (TPSs), able to outperform bulk ultra-high temperature ceramics (UHTCs). C3HARME is a 4-years EU funded program involving 12 European partners from 6 countries focused on the design, fabrication and testing of UHTCMCs for nearzero erosion nozzles and near-zero ablation TPS tiles. C3harme will look at different technologies coming from the science of bulk ceramics and CMCs and combine them to find out new approaches for their manufacturing. Novel theoretical models and testing methodologies are necessary to characterize properly these materials. This talk will summarize some of the findings and advances of the program, with special emphasis on the innovative approaches that we have implemented.
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MUNGIGUERRA, STEFANO, ANSELMO CECERE, and RAFFAELE SAVINO. "AERO-THERMO-DYNAMIC STUDY OF ULTRA-HIGH- TEMPERATURE CERAMIC COMPOSITES FOR THERMAL PROTECTION SYSTEMS AND ROCKET NOZZLES." In Thirty-sixth Technical Conference. Destech Publications, Inc., 2021. http://dx.doi.org/10.12783/asc36/35774.

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The most extreme aero-thermo-dynamic conditions encountered in aerospace applications include those of atmospheric re-entry, characterized by hypersonic Mach numbers, high temperatures and a chemically reacting environment, and of rocket propulsion, in which a combusting, high-pressure, supersonic flow can severely attack the surfaces of the motor internal components (particularly nozzle throats), leading to thermo-chemical erosion and consequent thrust decrease. For these applications, Ultra-High-Temperature Ceramics (UHTC), namely transition metal borides and carbides, are regarded as promising candidates, due to their excellent high-temperature properties, including oxidation and ablation resistance, which are boosted by the introduction of secondary phases, such as silicon carbide and carbon fibers reinforcement (in the so-called Ultra-High- Temperature Ceramic Matrix Composites, UHTCMC). The recent European H2020 C3HARME research project was devoted to development and characterization of new-class UHTCMCs for near-zero ablation thermal protection systems for re-entry vehicles and near-zero erosion rocket nozzles. Within the frame of the project and in collaboration with several research institutions and private companies, research activities at the University of Naples “Federico II” (UNINA) focused on requirements definition, prototypes design and test conditions identification, with the aim to increase the Technology Readiness Level (TRL) of UHTCMC up to 6. Experimental tests were performed with two facilities: an arc-jet plasma wind tunnel, where small specimens were characterized in a relevant atmospheric re-entry environment (Fig.1a), and a lab-scale hybrid rocket engine, where material testing was performed with different setups, up to complete nozzle tests, in conditions representative of real propulsive applications (Fig.1b). The characterization of the aero-thermo-chemical response and ablation resistance of different UHTCMC formulations was supported by numerical computations of fluiddynamic flowfields and materials thermal behavior. The UNINA activities provided a large database supporting the achievement of the project objectives, with development and testing of full-scale TPS assemblies and a large-size solid rocket nozzle.
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Garino, Gia. "Fracture strength of multi-component ultra-high temperature carbides." In MME Undergraduate Research Symposium. Florida International University, 2022. http://dx.doi.org/10.25148/mmeurs.010564.

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Ultra-high temperature ceramics (UHTCs) have emerged as a promising material for next generation re-entry hypersonic vehicles due to high melting point (&gt;3000 °C), and high mechanical properties and oxidation resistance. Yet none of the unary UHTCs can satisfy the whole gamut of demanding requirements for aerospace applications. Recently, the single-phase solid-solution formation in a multi-component ultra-high temperature ceramic (MC-UHTC) materials have gained interest due to their superior thermo-mechanical properties compared to conventional UHTCs. Herein, a systematic approach was used to fabricate binary (Ta, Nb)C, ternary (Ta, Nb, Hf)C, and quaternary (Ta, Nb, Hf, Ti)C UHTCs by gradual addition of UHTC components via spark plasma sintering (SPS). Fracture strength of the samples was measured using 4-point bend testing to understand the effect of UHTC components on the failure behavior of MC-UHTCs. A high-speed camera was also used to visualize and record the failure in each sample. The results showed that the quaternary UHTC has a fracture strength of ~351 MPa, which is ~227% and 10% higher than binary and ternary samples, respectively. Enhancement in the fracture strength has been attributed to increase in the entropy of a MC-UHTC with gradual addition of UHTC component. The present findings promote MC-UHTCs as a candidate damage tolerant structural material for aerospace applications.
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Gardi, Roberto, Antonio Del Vecchio, Giuliano Marino, and Gennaro Russo. "CIRA activities on UHTC's: on-ground and in flight experimentations." In 17th AIAA International Space Planes and Hypersonic Systems and Technologies Conference. American Institute of Aeronautics and Astronautics, 2011. http://dx.doi.org/10.2514/6.2011-2303.

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Yu, Huaqiang, and Mingqiang Lin. "Analysis of Average Crack Spacing of UHTCC Reinforced Beams." In 2017 2nd International Conference on Civil, Transportation and Environmental Engineering (ICCTE 2017). Atlantis Press, 2017. http://dx.doi.org/10.2991/iccte-17.2017.27.

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9

Wang Yongjun, Wang Zhenqing, Liu Yang, and Lv Hongqing. "Mechanical investigations on high temperature oxidation of ZrB2-SiC UHTCs." In 2008 2nd International Symposium on Systems and Control in Aerospace and Astronautics (ISSCAA). IEEE, 2008. http://dx.doi.org/10.1109/isscaa.2008.4776338.

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Su, Jun, and Shilang Xu. "Effect of UHTCC on seismic behavior of reinforced concrete frame joints." In 2011 International Conference on Electric Technology and Civil Engineering (ICETCE). IEEE, 2011. http://dx.doi.org/10.1109/icetce.2011.5775178.

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