13th International Conference on Fracture June 16–21, 2013, Beijing, China -7- t=20s t=30s t=40s Figure 8. Temperature distribution of cylinder C/C RVE during thermal radiation Figure 9. Temperature change process of selected nodes 5. Conclusion In this paper, the ablation damage of C/C composites in high temperature radiation environment was investigated. The conclusions can be remarked as follows. (1) The mismatch of ablation rate between fiber and matrix leads to a high heat flux and damage at the interface during thermal radiation. (2) The ablation morphology of C/C composites takes the shape of typical “needle clusters” due to the mismatch of the thermal property of the carbon fibers and matrixes. Acknowledgements The authors gratefully acknowledge the support from Foundation of China under grant #11172012 and the Municipal Natural Science Foundation of Beijing under grant #3092006. References [1] F.J. Yi, J. Liang, S.H. Meng, S.Y. Du. Study on ablation mechanism and models of heatshield composites. Journal of Solid Rocket Technology. 23(2000) 48-56. [2] J.D. Buckley. Carbon-carbon materials and composites. USA: Noyes Pulications. 1993. [3] R.P. Nathan. Modeling of Ablation of Carbon-Carbon Composite Thermal Protection System. Collection of Technical Papers - 39th AIAA Thermophysics Conference. 2(2007) 1307-1314.
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