Effects of space extreme temperature cycling on carbon/carbon-(Zr-Si-B-C-O) composites performances.
- Resource Type
- Article
- Authors
- Zhang, Mao-yan; Li, Ke-zhi; Shi, Xiao-hong; Li, He-jun; Ma, Chun-hong; Hu, Chun-xia; Wang, Lu; Cheng, Chun-yu
- Source
- Corrosion Science. Feb2019, Vol. 147, p212-222. 11p.
- Subject
- *THERMOCYCLING
*CARBON composites
*MICROCRACKS
*INTERFACIAL bonding
*MICROSTRUCTURE
*FLEXURAL strength testing
- Language
- ISSN
- 0010-938X
Highlights • Cyclic thermal loading was performed on C/C-(Zr-Si-B-C-O) composites between −120 °C and 120 °C for up to 200 cycles. • Extreme-temperature thermal cycling (ETC) resulted in a 16.98% flexural strength decrease after 200 cycles. • Microcracks and interfacial debonding lead to the increase of the open porosity with ETC increasing. • Cyclic exposure to high-temperature oxidation has been carried out to test self-sealing behavior. • Exceeding 50 ETC cycles, the Zr-Si-B-C-O matrix could not heal the rapidly generated defects during HT oxidation tests. Abstract Microstructures, mechanical properties, and oxidation resistance of ZrC-SiC-ZrB 2 -ZrO 2 modified carbon/carbon composites (C/C-(Zr-Si-B-C-O)) have been investigated in the simulated space environment with different extreme-temperature thermal cycling (ETC) treatment. Cyclic thermal loading was performed in the temperature range between −120 °C and 120 °C for up to 200 cycles. Results showed that the microstructure degradation of the composite after ETC treatment was attributed to the formation of microcracks and the interfacial debonding. ETC treatment resulted in a 16.98% flexural strength decrease after 200 cycles. An oxidation model on the microstructure evolution of ETC treated C/C-(Zr-Si-B-C-O) composites was proposed to explain the oxidation failure mechanism. [ABSTRACT FROM AUTHOR]