Nicholas PAROLINI, Abhendra SINGH

DOI Number: N/A

Conference number: HiSST-2025-337

In hypersonic flights, hot structural materials capable of maintaining structural integrity at high temperatures are needed for various vehicle components. In response to this, interest has grown in ultra-high temperature ceramic matrix composites (UHTCMCs). The work performed in this investigation looks at the changes in microstructure and mechanical strength of short-term thermal exposure and thermal aging of C/C-SiC UHTCMC. The studies are performed at 600°C and 1200°C. After being thermally exposed, all samples showed a loss in mass. Closer inspection of the thermally exposed C/C-SiC samples showed erosion in the fibers, matrix, as well as the fiber and matrix interface. EDS scans
detected oxygen co-located in carbon rich areas of the composites, indicating that there was a preferential oxidation of carbon in the thermally exposed samples. Disk compression tests of the samples indicated that the splitting tensile strength of the composites decreases with increasing time and temperature of exposure. Differences in failure modes were also observed due to differences in temperature and duration of exposure.

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In Categories: 1.Events, 1.HiSST 2025, Materials and Structures for vehicle and all subsystems
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