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Research Article | Open Access

Propulsion tests on ultra-high-temperature ceramic matrix composites for reusable rocket nozzles

Diletta Scitia, Antonio Vincia( ), Luca Zolia, Pietro Galiziaa, Simone Faillaa, Stefano Mungiguerrab( ), Giuseppe D. Di Martinob, Anselmo Cecereb, Raffaele Savinob
Institute of Science, Technology and Sustainability for Ceramics—National Research Council, Faenza 48018, Italy
Department of Industrial Engineering, University of Naples Federico II, Naples 80125, Italy
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Graphical Abstract

Abstract

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.

Keywords

ultra-high-temperature ceramics (UHTCs)ceramic matrix composites (CMCs)propulsionoxidation resistancenozzle prototypes

References

[1]
Drenthe NT, Zandbergen BTC, Curran R, et al. Cost estimating of commercial smallsat launch vehicles. Acta Astronaut 2019, 155: 160–169.
Crossref Google Scholar
[2]
Mungiguerra S, Di Martino GD, Zuppardi G. Computational evaluation of aero-thermodynamic loads and effect of catalyticity in an arc-jet wind tunnel. J Aerospace Eng 2020, 33: 04020005.
Crossref Google Scholar
[3]
Sutton GP, Bibliarz O. Rocket Propulsion Elements, 7th edn. Hoboken, USA: John Wiley & Sons, 2001.
[4]
Savino R, Mungiguerra S, Di Martino GD. Testing ultra-high-temperature ceramics for thermal protection and rocket applications. Adv Appl Ceram 2018, 117: s9–s18.
Crossref Google Scholar
[5]
Evans B, Kuo KK, Cortopassi AC. Characterization of nozzle erosion behavior under rocket motor operating conditions. Int J Energ Mater Ch 2010, 9: 533–548.
Crossref Google Scholar
[6]
Padture NP. Advanced structural ceramics in aerospace propulsion. Nat Mater 2016, 15: 804–809.
Crossref Google Scholar
[7]
He QC, Li HJ, Tan Q, et al. Effects of ZrC particle size on ablation behavior of C/C–SiC–ZrC composites prepared by chemical liquid vapor deposition. Corros Sci 2022, 205: 110469.
Crossref Google Scholar
[8]
He QC, Li HJ, Tan Q, et al. Influence of carbon preform density on the microstructure and ablation resistance of CLVD-C/C–ZrC–SiC composites. Corros Sci 2021, 190: 109648.
Crossref Google Scholar
[9]
He QC, Li HJ, Yin XM, et al. Effects of PyC shell thickness on the microstructure, ablation resistance of SiCnws/PyC–C/C–ZrC–SiC composites. J Mater Sci Technol 2021, 71: 55–66.
Crossref Google Scholar
[10]
Zeng Y, Wang DN, Xiong X, et al. Ablation-resistant carbide Zr0.8Ti0.2C0.74B0.26 for oxidizing environments up to 3,000 ℃. Nat Commun 2017, 8: 15836.
Crossref Google Scholar
[11]
Du BH, Cheng Y, Xun LC, et al. Using PyC modified 3D carbon fiber to reinforce UHTC under low temperature sintering without pressure. J Adv Ceram 2021, 10: 871–884.
Crossref Google Scholar
[12]
Ni DW, Cheng Y, Zhang JP, et al. Advances in ultra-high temperature ceramics, composites, and coatings. J Adv Ceram 2022, 11: 1–56.
Crossref Google Scholar
[13]
Galizia P, Failla S, Zoli L, et al. Tough salami-inspired Cf/ZrB2 UHTCMCs produced by electrophoretic deposition. J Eur Ceram Soc 2018, 38: 403–409.
Crossref Google Scholar
[14]
Zhang DY, Hu P, Dong S, et al. Effect of pyrolytic carbon coating on the microstructure and fracture behavior of the Cf/ZrB2–SiC composite. Ceram Int 2018, 44: 19612–19618.
Crossref Google Scholar
[15]
Galizia P, Sciti D, Saraga F, et al. Off-axis damage tolerance of fiber-reinforced composites for aerospace systems. J Eur Ceram Soc 2020, 40: 2691–2698.
Crossref Google Scholar
[16]
Zoli L, Sciti D. Efficacy of a ZrB2–SiC matrix in protecting C fibres from oxidation in novel UHTCMC materials. Mater Design 2017, 113: 207–213.
Crossref Google Scholar
[17]
Sciti D, Silvestroni L, Monteverde F, et al. Introduction to H2020 project C3HARME—Next generation ceramic composites for combustion harsh environment and space. Adv Appl Ceram 2018, 117: s70–s75.
Crossref Google Scholar
[18]
Mungiguerra S, Di Martino GD, Cecere A, et al. Arc-jet wind tunnel characterization of ultra-high-temperature ceramic matrix composites. Corros Sci 2019, 149: 18–28.
Crossref Google Scholar
[19]
Mungiguerra S, Di Martino GD, Savino R, et al. Ultra-high-temperature ceramic matrix composites in hybrid rocket propulsion environment. In: Proceedings of the 2018 International Energy Conversion Engineering Conference, Cincinnati, USA, 2018: AIAA 2018-4694.
Crossref
[20]
Rubio V, Binner J, Cousinet S, et al. Materials characterisation and mechanical properties of Cf–UHTC powder composites. J Eur Ceram Soc 2019, 39: 813–824.
Crossref Google Scholar
[21]
Yan CL, Liu RJ, Cao YB, et al. Preparation and properties of 3D needle-punched C/ZrC–SiC composites by polymer infiltration and pyrolysis process. Ceram Int 2014, 40: 10961–10970.
Crossref Google Scholar
[22]
Wu HT, Xie CM, Zhang WG, et al. Fabrication and properties of 2D C/C–ZrB2–ZrC–SiC composites by hybrid precursor infiltration and pyrolysis. Adv Appl Ceram 2013, 112: 366–373.
Crossref Google Scholar
[23]
Galizia P, Sciti D, Jain N. Insight into microstructure and flexural strength of ultra-high temperature ceramics enriched SICARBONTM composite. Mater Design 2021, 208: 109888.
Crossref Google Scholar
[24]
Li Y, Chen S, Ma X, et al. Influence of preparation temperature on the properties of C/ZrC composites. J Alloys Compd 2017, 690: 206–211.
Crossref Google Scholar
[25]
Yan CL, Liu RJ, Zhang CR, et al. Effects of SiC/HfC ratios on the ablation and mechanical properties of 3D Cf/HfC–SiC composites. J Eur Ceram Soc 2017, 37: 2343–2351.
Crossref Google Scholar
[26]
Zhang XH, Du BH, Hu P, et al. Thermal response, oxidation and ablation of ultra-high temperature ceramics, C/SiC, C/C, graphite and graphite–ceramics. J Mater Sci Technol 2022, 102: 137–158.
Crossref Google Scholar
[27]
Paul A, Venugopal S, Binner JGP, et al. UHTC–carbon fibre composites: Preparation, oxyacetylene torch testing and characterisation. J Eur Ceram Soc 2013, 33: 423–432.
Crossref Google Scholar
[28]
Paul A, Rubio V, Binner J, et al. Evaluation of the high temperature performance of HfB2 UHTC particulate filled Cf/C composites. Int J Appl Ceram Technol 2017, 14: 344–353.
Crossref Google Scholar
[29]
Sayir A. Carbon fiber reinforced hafnium carbide composite. J Mater Sci 2004, 39: 5995–6003.
Crossref Google Scholar
[30]
Wang Z, Dong SM, Zhang XY, et al. Fabrication and properties of Cf/SiC–ZrC composites. J Am Ceram Soc 2008, 91: 3434–3436.
Crossref Google Scholar
[31]
Li QG, Dong SM, Wang Z, et al. Fabrication and properties of 3-D Cf/ZrB2–ZrC–SiC composites via polymer infiltration and pyrolysis. Ceram Int 2013, 39: 5937–5941.
Crossref Google Scholar
[32]
Vignoles GL. Chemical vapor deposition/infiltration processes for ceramic composites. In: Advances in Composites Manufacturing and Process Design. Philippe B, Ed. Amsterdam, the Netherlands: Woodhead Publishing, 2015: 147–176.
Crossref
[33]
Chen S, Zhang CR, Zhang YD, et al. Preparation and properties of carbon fiber reinforced ZrC–ZrB2 based composites via reactive melt infiltration. Compos Part B-Eng 2014, 60: 222–226.
Crossref Google Scholar
[34]
Pi HL, Fan SW, Wang YG. C/SiC–ZrB2–ZrC composites fabricated by reactive melt infiltration with ZrSi2 alloy. Ceram Int 2012, 38: 6541–6548.
Crossref Google Scholar
[35]
Vinci A, Zoli L, Galizia P, et al. Reactive melt infiltration of carbon fibre reinforced ZrB2/B composites with Zr2Cu. Compos Part A-Appl S 2020, 137: 105973.
Crossref Google Scholar
[36]
C³HARME. Available at https://c3harme.eu/.
[37]
Galizia P, Vinci A, Zoli L, et al. Retained strength of UHTCMCs after oxidation at 2278 K. Compos Part A-Appl S 2021, 149: 106523.
Crossref Google Scholar
[38]
Zoli L, Vinci A, Galizia P, et al. Is spark plasma sintering suitable for the densification of continuous carbon fibre— UHTCMCs? J Eur Ceram Soc 2020, 40: 2597–2603.
Crossref Google Scholar
[39]
Zoli L, Vinci A, Galizia P, et al. On the thermal shock resistance and mechanical properties of novel unidirectional UHTCMCs for extreme environments. Sci Rep 2018, 8: 9148.
Crossref Google Scholar
[40]
Fahrenholtz WG, Hilmas GE, Talmy IG, et al. Refractory diborides of zirconium and hafnium. J Am Ceram Soc 2007, 90: 1347–1364.
Crossref Google Scholar
[41]
Vinci A, Zoli L, Sciti D. Influence of SiC content on the oxidation of carbon fibre reinforced ZrB2/SiC composites at 1500 and 1650 ℃ in air. J Eur Ceram Soc 2018, 38: 3767–3776.
Crossref Google Scholar
[42]
Sciti D, Zoli L, Reimer T, et al. A systematic approach for horizontal and vertical scale up of sintered Ultra-High Temperature Ceramic Matrix Composites for aerospace— Advances and perspectives. Compos Part B-Eng 2022, 234: 109709.
Crossref Google Scholar
[43]
Medri V, Capiani C, Gardini D. Slip casting of ZrB2–SiC composite aqueous suspensions. Adv Eng Mater 2010, 12: 210–215.
Crossref Google Scholar
[44]
Di Martino GD, Mungiguerra S, Carmicino C, et al. Two-hundred-Newton laboratory-scale hybrid rocket testing for paraffin fuel-performance characterization. J Propul Power 2019, 35: 224–235.
Crossref Google Scholar
[45]
Mungiguerra S, Di Martino GD, Savino R, et al. Characterization of novel ceramic composites for rocket nozzles in high-temperature harsh environments. Int J Heat Mass Tran 2020, 163: 120492.
Crossref Google Scholar
[46]
Sciti D, Zoli L, Silvestroni L, et al. Design, fabrication and high velocity oxy-fuel torch tests of a Cf–ZrB2-fiber nozzle to evaluate its potential in rocket motors. Mater Design 2016, 109: 709–717.
Crossref Google Scholar
[47]
Di Martino GD, Mungiguerra S, Cecere A, et al. Hybrid rockets with nozzle in ultra-high-temperature ceramic composites. In: Proceedings of the 69th International Astronautical Congress, Bremen, Germany, 2018: IAC-18,C4,3,6,x47333.
[48]
Chorin AJ. Numerical solution of the Navier–Stokes equations. Math Comput 1968, 22: 745–762.
Crossref Google Scholar
[49]
Menter FR. Two-equation eddy-viscosity turbulence models for engineering applications. AIAA J 1994, 32: 1598–1605.
Crossref Google Scholar
[50]
Magnussen B. On the structure of turbulence and a generalized eddy dissipation concept for chemical reaction in turbulent flow. In: Proceedings of the 19th Aerospace Sciences Meeting, St. Louis, USA, 1981: AIAA 1981-42.
Crossref
[51]
Modest MF. Radiative Heat Transfer, 2nd edn. Amsterdam, the Netherlands: Academic Press, 2003.
Crossref
[52]
Galizia P, Sciti D. Disclosing residual thermal stresses in UHT fibre-reinforced ceramic composites and their effect on mechanical behaviour and damage evolution. Compos Part B-Eng 2023, 248: 110369.
Crossref Google Scholar
[53]
Galizia P, Zoli L, Sciti D. Impact of residual stress on thermal damage accumulation, and Young’s modulus of fiber-reinforced ultra-high temperature ceramics. Mater Design 2018, 160: 803–809.
Crossref Google Scholar
[54]
Monteverde F, Guicciardi S, Bellosi A. Advances in microstructure and mechanical properties of zirconium diboride based ceramics. Mater Sci Eng A 2003, 346: 310–319.
Crossref Google Scholar
[55]
Pradere C, Sauder C. Transverse and longitudinal coefficient of thermal expansion of carbon fibers at high temperatures (300–2500 K). Carbon 2008, 46: 1874–1884.
Crossref Google Scholar
[56]
Sciti D, Zoli L, Vinci A, et al. Effect of PAN-based and pitch-based carbon fibres on microstructure and properties of continuous Cf/ZrB2–SiC UHTCMCs. J Eur Ceram Soc 2021, 41: 3045–3050.
Crossref Google Scholar
[57]
Schäfer W, Vogel WD. Faserverstärkte keramiken hergestellt durch polymerinfiltration. In: Keramische Verbundwerkstoffe. Walter K, Ed. Weinheim, Germany: Wiley-VCH Verlag GmbH, 2002: 76–94. (in German)
Crossref
[58]
SGL Carbon. SIGRASIC® carbon fiber reinforced silicon carbide. Available at https://www.sglcarbon.com/en/markets-solutions/material/sigrasic-carbon-fiber-reinforced-silicon-carbide/, 2023.
[59]
Krenkel W. Carbon fibre reinforced silicon carbide composites (C/SiC, C/C–SiC). In: Handbook of Ceramic Composites. Bansal NP, Ed. New York, USA: Springer New York, 2005: 117–148.
Crossref
[60]
Savino R, Criscuolo L, Di Martino GD, et al. Aero-thermo-chemical characterization of ultra-high-temperature ceramics for aerospace applications. J Eur Ceram Soc 2018, 38: 2937–2953.
Crossref Google Scholar
[61]
Jain N, Sanvito S. Specific set of recommendation for materials development in WP2 based on micro-models/DFT. Report of Deliverable 3.7, C3HARME Project, 2017: 685594. Available at https://c3harme.eu/wp-content/uploads/2018/02/C3_D3.7.pdf.
[62]
Reimer T, Esser B, Mungiguerra S, et al. Next generation ceramic composites for combustion harsh environments and space. Periodical Technical Report Part B: WP3, 2020: 47–50. Available at https://cordis.europa.eu/project/id/685594/results/it.
[63]
Vinci A, Reimer T, Zoli L, et al. Influence of pressure on the oxidation resistance of carbon fiber reinforced ZrB2/SiC composites at 2000 and 2200 ℃. Corros Sci 2021, 184: 109377.
Crossref Google Scholar
[64]
Mungiguerra S, Di Martino GD, Cecere A, et al. Ultra-high-temperature testing of sintered ZrB2-based ceramic composites in atmospheric re-entry environment. Int J Heat Mass Tran 2020, 156: 119910.
Crossref Google Scholar
[65]
Mungiguerra S, Cecere A, Savino R, et al. Improved aero-thermal resistance capabilities of ZrB2-based ceramics in hypersonic environment for increasing SiC content. Corros Sci 2021, 178: 109067.
Crossref Google Scholar
[66]
Nait-Ali B, Haberko K, Vesteghem H, et al. Thermal conductivity of highly porous zirconia. J Eur Ceram Soc 2006, 26: 3567–3574.
Crossref Google Scholar
[67]
Mungiguerra S, Silvestroni L, Savino R, et al. Qualification and reusability of long and short fibre-reinforced ultra-refractory composites for aerospace thermal protection systems. Corros Sci 2022, 195: 109955.
Crossref Google Scholar
[68]
Cheng Y, Lyu Y, Xie YS, et al. Starting from essence to reveal the ablation behavior and mechanism of 3D PyC Cf/ZrC–SiC composite. Corros Sci 2022, 201: 110261.
Crossref Google Scholar
[69]
Cheng Y, Liu C, Hu P, et al. Using in-situ conversed nano SiC to bond UHTC particles and construct anti-ablation coating. Compos Part A-Appl S 2022, 162: 107159.
Crossref Google Scholar
[70]
Savino R, Festa G, Cecere A, et al. Experimental set up for characterization of carbide-based materials in propulsion environment. J Eur Ceram Soc 2015, 35: 1715–1723.
Crossref Google Scholar
[71]
Di Martino GD, Mungiguerra S, Cecere A, et al. Ultra-high-temperature ceramic matrix composites for hybrid rocket nozzles. 2019. Available at https://www.iris.unina.it/handle/11588/779636.
Crossref
Journal of Advanced Ceramics
Volume 12 Issue 7,
July 2023
Pages 1345-1360
DOI: 10.26599/JAC.2023.9220759
Cite this article:
Sciti D, Vinci A, Zoli L, et al. Propulsion tests on ultra-high-temperature ceramic matrix composites for reusable rocket nozzles. Journal of Advanced Ceramics, 2023, 12(7): 1345-1360. https://doi.org/10.26599/JAC.2023.9220759

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Received: 06 February 2023
Revised: 04 April 2023
Accepted: 24 April 2023
Published: 08 June 2023
© The Author(s) 2023.

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