Propulsion tests on ultra-high-temperature ceramic matrix composites for reusable rocket nozzles
Ultra-high-temperature ceramic matrix composites (UHTCMCs) based on a ZrB2/SiC matrix have been investigated for the fabrication of reusable nozzles for propulsion. Three de Laval nozzle prototypes, obtained by sintering with either hot pressing (HP) or spark plasma sintering (SPS), were tested 2–3...
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| Format: | Article |
| Language: | English |
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Tsinghua University Press
2023-07-01
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| Series: | Journal of Advanced Ceramics |
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| Online Access: | https://www.sciopen.com/article/10.26599/JAC.2023.9220759 |
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| author | Diletta Sciti Antonio Vinci Luca Zoli Pietro Galizia Simone Failla Stefano Mungiguerra Giuseppe D. Di Martino Anselmo Cecere Raffaele Savino |
| author_facet | Diletta Sciti Antonio Vinci Luca Zoli Pietro Galizia Simone Failla Stefano Mungiguerra Giuseppe D. Di Martino Anselmo Cecere Raffaele Savino |
| author_sort | Diletta Sciti |
| collection | DOAJ |
| description | Ultra-high-temperature ceramic matrix composites (UHTCMCs) based on a ZrB2/SiC matrix have been investigated for the fabrication of reusable nozzles for propulsion. Three de Laval nozzle prototypes, obtained by sintering with either hot pressing (HP) or spark plasma sintering (SPS), were tested 2–3 times in a hybrid rocket motor for proving reusability. Sections were extracted after oxidation tests to study the microstructural changes and oxidative and thermomechanical stresses induced by the repeated tests. Compared to a reference graphite nozzle, no measurable erosion was observed for the UHTCMC-based nozzles. The oxidation mechanism consisted in the formation of a ZrO2 intermediate layer, with a liquid silicon oxide (SiO2) layer on the surface that was displaced by the action of the gas flux towards the divergent part of the nozzle, protecting it from further oxidation. Both specimens obtained by HP and SPS displayed similar performance, with very slight differences, which were attributed to small changes in porosity. These tests demonstrated the capability of complex-shaped prototypes made of the developed UHTCMCs to survive repeated exposure to environments representative of a realistic space propulsion application, for overall operating time up to 30 s, without any failure nor measurable erosion, making a promising step towards the development of reusable rocket components. |
| first_indexed | 2024-03-12T21:47:47Z |
| format | Article |
| id | doaj.art-f38f0eb104bd47c5bafbe31404e978cd |
| institution | Directory Open Access Journal |
| issn | 2226-4108 2227-8508 |
| language | English |
| last_indexed | 2024-03-12T21:47:47Z |
| publishDate | 2023-07-01 |
| publisher | Tsinghua University Press |
| record_format | Article |
| series | Journal of Advanced Ceramics |
| spelling | doaj.art-f38f0eb104bd47c5bafbe31404e978cd2023-07-26T10:09:29ZengTsinghua University PressJournal of Advanced Ceramics2226-41082227-85082023-07-011271345136010.26599/JAC.2023.9220759Propulsion tests on ultra-high-temperature ceramic matrix composites for reusable rocket nozzlesDiletta Sciti0Antonio Vinci1Luca Zoli2Pietro Galizia3Simone Failla4Stefano Mungiguerra5Giuseppe D. Di Martino6Anselmo Cecere7Raffaele Savino8Institute of Science, Technology and Sustainability for Ceramics—National Research Council, Faenza 48018, ItalyInstitute of Science, Technology and Sustainability for Ceramics—National Research Council, Faenza 48018, ItalyInstitute of Science, Technology and Sustainability for Ceramics—National Research Council, Faenza 48018, ItalyInstitute of Science, Technology and Sustainability for Ceramics—National Research Council, Faenza 48018, ItalyInstitute of Science, Technology and Sustainability for Ceramics—National Research Council, Faenza 48018, ItalyDepartment of Industrial Engineering, University of Naples Federico II, Naples 80125, ItalyDepartment of Industrial Engineering, University of Naples Federico II, Naples 80125, ItalyDepartment of Industrial Engineering, University of Naples Federico II, Naples 80125, ItalyDepartment of Industrial Engineering, University of Naples Federico II, Naples 80125, ItalyUltra-high-temperature ceramic matrix composites (UHTCMCs) based on a ZrB2/SiC matrix have been investigated for the fabrication of reusable nozzles for propulsion. Three de Laval nozzle prototypes, obtained by sintering with either hot pressing (HP) or spark plasma sintering (SPS), were tested 2–3 times in a hybrid rocket motor for proving reusability. Sections were extracted after oxidation tests to study the microstructural changes and oxidative and thermomechanical stresses induced by the repeated tests. Compared to a reference graphite nozzle, no measurable erosion was observed for the UHTCMC-based nozzles. The oxidation mechanism consisted in the formation of a ZrO2 intermediate layer, with a liquid silicon oxide (SiO2) layer on the surface that was displaced by the action of the gas flux towards the divergent part of the nozzle, protecting it from further oxidation. Both specimens obtained by HP and SPS displayed similar performance, with very slight differences, which were attributed to small changes in porosity. These tests demonstrated the capability of complex-shaped prototypes made of the developed UHTCMCs to survive repeated exposure to environments representative of a realistic space propulsion application, for overall operating time up to 30 s, without any failure nor measurable erosion, making a promising step towards the development of reusable rocket components.https://www.sciopen.com/article/10.26599/JAC.2023.9220759ultra-high-temperature ceramics (uhtcs)ceramic matrix composites (cmcs)propulsionoxidation resistancenozzle prototypes |
| spellingShingle | Diletta Sciti Antonio Vinci Luca Zoli Pietro Galizia Simone Failla Stefano Mungiguerra Giuseppe D. Di Martino Anselmo Cecere Raffaele Savino Propulsion tests on ultra-high-temperature ceramic matrix composites for reusable rocket nozzles Journal of Advanced Ceramics ultra-high-temperature ceramics (uhtcs) ceramic matrix composites (cmcs) propulsion oxidation resistance nozzle prototypes |
| title | Propulsion tests on ultra-high-temperature ceramic matrix composites for reusable rocket nozzles |
| title_full | Propulsion tests on ultra-high-temperature ceramic matrix composites for reusable rocket nozzles |
| title_fullStr | Propulsion tests on ultra-high-temperature ceramic matrix composites for reusable rocket nozzles |
| title_full_unstemmed | Propulsion tests on ultra-high-temperature ceramic matrix composites for reusable rocket nozzles |
| title_short | Propulsion tests on ultra-high-temperature ceramic matrix composites for reusable rocket nozzles |
| title_sort | propulsion tests on ultra high temperature ceramic matrix composites for reusable rocket nozzles |
| topic | ultra-high-temperature ceramics (uhtcs) ceramic matrix composites (cmcs) propulsion oxidation resistance nozzle prototypes |
| url | https://www.sciopen.com/article/10.26599/JAC.2023.9220759 |
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