Abstract
An experimental study was conducted to study the effects of chemical vapor deposition (CVD) carbon content on the erosion behavior of 5 direction (5D) carbon-carbon (C/C) composite in a solid rocket motor (SRM). A small SRM, which can compare the erosion performance of two samples under the same working conditions, was designed and tested. The erosion of the carbon-carbon composite ablative morphology at macroscale and microscale was obtained and analyzed. Results show that the average erosion rates of 1# and 2# samples are 0.35 mm/s and 0.45 mm/s, respectively, which means the erosion rate of the sample with high CVD carbon content is 22.2% times lower than the one with low CVD carbon content. During SRM operation, the fibers within fiber bundles and carbon rods are in a dispersive and integral state, respectively, thus carbon rods have a better anti-ablation capability, followed by fiber bundles and matrix in turn. As a result, a carbon rod will be positioned higher than the matrix and fiber bundles around. Furthermore, the ablation of fibers within fiber bundles and carbon rods, although they have significant differences in the ablation process, can both be described as a single fiber ablation. The oxidizing species react with the matrix, then with the CVD carbon and the fiber within a fiber bundle in turn, while they react with the matrix, the CVD carbon and the fiber within a carbon rod simultaneously. This shows that the increase in CVD carbon content will improve the ablation performance of C/C composite by protecting the fibers within the fiber bundles. The present study provides a fundamental understanding of the effect of CVD carbon on the ablation performance of C/C composite, serving as a reference for further design and optimizations of C/C composite.
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References
Zhang, B., Li, X.: Thermal response of a 4D carbon-carbon composite with volume ablation : a numerical simulation study. Appl Compos Mater. 25((1)), 191–202 (2017)
Qin, F., Peng, L., Li, J., et al.: Numerical simulations of multiscale ablation of carbon-carbon throat with morphology effects. AIAA J. 55((10)), 3476–3485 (2017)
Han, M., Silberschmidt, V.V.: Theoretical analysis on needle-punched carbon-carbon composites. Appl Compos Mater. 26((3)), 805–816 (2019)
Wan, F., Pirzada, T.J., Liu, R., et al.: Microstructure characterization by X-ray computed tomography of C/C-SiC ceramic composites fabricated with different carbon fiber architectures. Appl Compos Mater. 26((4)), 1247–1260 (2019)
Guo, W., Bai, S., Ye, Y., et al.: Rapid preparation of 2D C/C composite by moulding method based on recycled carbon fiber. Appl Compos Mater. 26((4)), 1163–1175 (2019)
Lachaud, J., Vignoles, G.L., Gohyeneche, J.M., et al.: Ablation in carbon-carbon composites:microscopic observations and 3D numerical simulation of surface roughness evolution. Ceram Trans. 191, 149–160 (2006)
Thakre, P. K., Yang, V.: Graphite nozzle material erosion in solid-propellant rocket motors. 45st AIAA Aerospace Sciences Meeting and Exhibit. 2007–778
Vignoles, G.L., Aspa, Y., Quintard, M.: Modelling of carbon-carbon composite ablation in rocket nozzles. Compos Sci Technol. 70, 1303–1311 (2010)
Delaney, L.J., Eagleton, L.C., Jones, W.H.: A semiquantitative prediction of the erosion of graphite nozzle inserts. AIAA J. (2, (8)), 1428–1433 (1964)
McDonald, A.J., Hedman, P.O.: Erosion of graphite in solid-propellant combustion gases and effects on heat transfer. AIAA J. (3, (7)), 1250–1257 (1965)
Klager, K.: The interaction of the efflux of solid propellants with nozzle materials. Propellants and Explosives. 2, 55–63 (1977)
Kuo, K.K., Keswani, S.: A comprehensive theoretical model for carbon-carbon composite nozzle recession. Combust Sci Technol. 42, 177–192 (1986)
Thakre, P., Yang, V.: A comprehensive model to predict and mitigate the erosion of carbon-carbon/graphite rocket nozzles. 43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit. 2007–5777
Acharya, R., Kuo, K.K.: Effect of pressure and propellant composition on graphite rocket nozzle erosion rate. J Propuls Power. 23((6)), 1242–1254 (2007)
Geisler, R. L.: A global view of the use of aluminum fuel in solid rocket motors. AIAA Paper. 2002–3748
Piyush, T., Rajesh, R., Richard, C.: Mechanical erosion of graphite nozzle material in solid-propellant rocket motors. AIAA Paper. 2010–615
Piyush, T., Rajesh, R., Richard, C.: Mechanical erosion of graphite nozzle in solid-propellant rocket motor. J Propuls Power. 29(3), 593–601 (2013)
Golovina, E.C.: The gasification of carbon by carbon dioxide at high temperatures and pressures. Carbon. 18, 197–201 (1980)
Yin, J., Zhang, H.B., Xiong, X., et al.: Ablation performance of carbon-carbon composite throat after a solid rocket motor ground ignition test. Appl Compos Mater. 19((3–4)), 237–245 (2012)
Wei, K., Li, J., Shi, H., et al.: Two-scale prediction of effective thermal conductivity of 3D braided C/C composites considering void defects by asymptotic homogenization method. Appl Compos Mater. 26((5–6)), 1367–1387 (2019)
Zhao, Y., Song, L., Li, J., Jiao, Y.: Multi-scale finite element analyses of thermal conductivities of three dimensional woven composites. Appl Compos Mater. 24, 1525–1542 (2017)
Shigang, A., Rujie, H., Yongmao, P.: A numerical study on the thermal conductivity of 3D woven C/C composites at high temperature. Appl Compos Mater. 33, 823–835 (2015)
Daniele, B., Francesco, N., Marcello, O.: Radius of curvature effects on throat thermochemical erosion in solid rocket motors. AIAA Paper. 2012–0533
Libby, P.A., Blake, T.R.: Burning carbon particles in the presence of water vapor. Combustion and Flame. 41, 123–147 (1981)
Bradley, D., Dixon-Lewis, G., Habik, S.E., et al.: The oxidation of graphite powder in flame reaction zones. 20th Symposium (International) on Combustion. The Combustion Institute. 931–940 (1984)
Peng, L., He, G., Li, J., et al.: Effect of combustion gas mass flow rate on carbon-carbon composite nozzle ablation in a solid rocket motor. Carbon. (50, (2)), 1554–1562 (2012)
Li, Q., Li, J., He, G., et al.: Erosion of carbon-carbon composites using a low-velocity, high-particle-concentration two-phase jet in a solid rocket motor. Carbon. 67, 141–145 (2014)
Yen, C.C., Chang, Y.C., Tsai, H.C., Woon, W.Y.: Nucleation and growth dynamics of graphene grown through low power capacitive coupled radio frequency plasma enhanced chemical vapor deposition. Carbon. 154, 420–427 (2019)
Al-Hagri, A., Li, R., Rajput, N.S., et al.: Direct growth of single-layer terminated vertical graphene array on germanium by plasma enhanced chemical vapor deposition. Carbon. 155, 320–325 (2019)
Zhang, H., Wu, S., Lu, Z., Chen, X., Chen, Q., Gao, P., Yu, T., Peng, Z., Ye, J.: Efficient and controllable growth of vertically oriented grapheme nanosheets by mesoplasma chemical vapor deposition. Carbon. 147, 341–347 (2019)
Boury, D., Filipuzzi L. S.: Materials for solid rocket booster nozzle components. AIAA Paper. 2001–3438
Lachaud, J., Aspa, Y., Vignoles, G.L.: Analytical modeling of the steady state ablation of a 3D C/C composite. Int J Heat Mass Transf. 51, 2614–2627 (2008)
Borie, V., Brulard, J., Lengelle, G.: Aerothermochemical analysis of carbon-carbon nozzle recession in solid-propellant rocket motors. Journal of Propulsion. 5((6)), 665–673 (1989)
Liggett, N. D., Menon, S.: Simulation of nozzle erosion process in a solid propellant rocket motor. 45th AIAA aerospace sciences meeting and exhibit. 2007–776
Acknowledgements
This work was financially supported by the National Basic Research Program (973) of China (No.61391). We would like to extend special thanks to Mrs. Ni Chen for assisting with the hot-fire testing and Mr. Fei Zhang for providing technical assistance during the tests.
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Wang, L., Tian, W., Guo, Y. et al. Effects of CVD Carbon on the Erosion Behavior of 5D Carbon-Carbon Composite in a Solid Rocket Motor. Appl Compos Mater 27, 391–405 (2020). https://doi.org/10.1007/s10443-020-09820-8
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DOI: https://doi.org/10.1007/s10443-020-09820-8