In the application of carbon/carhon composites into the space vehicles, a key technology is the formation of an oxidation resistant layer on the surface. Simple coating method is apt to lead to the spalling of coating layer because of the thermal stress. In the Space Shuttle, a silicon carbide layer was formed by the conversion method. Authors fabricated trial articles made of the C/C with a functionally graded materials layer from carbon to silicon carbide (C/SiC) and performed thermal evaluation tests under the simulated conditions for the actual aerospace operation. No spalling of the CVD-SiC layer was observed after tests. But the repeated tests brought the oxidation corrosion of C/C. Therefore, authors tried to reveal a damage process by using various diagnostic means to find a course for the improvement of coating.
|出版ステータス||Published - 1999 1月 1|
|イベント||9th International Space Planes and Hypersonic Systems and Technologies Conference, 1999 - Norfolk, United States|
継続期間: 1999 11月 1 → 1999 11月 4
|Other||9th International Space Planes and Hypersonic Systems and Technologies Conference, 1999|
|Period||99/11/1 → 99/11/4|
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