Propulsion tests on ultra-high temperature ceramic matrix composites for reusable rocket nozzles
نویسندگان
چکیده
Ultra-high temperature ceramic matrix composites based on a ZrB2/SiC have been investigated for the fabrication of reusable nozzles propulsion. Three De Laval nozzle prototypes, obtained by sintering with either hot pressing or spark plasma sintering, were tested 2-3 times in hybrid rocket motor proving reusability. Sections extracted after oxidation tests to study microstructural changes and oxidative thermomechanical stresses induced repeated tests. Compared reference graphite nozzle, no measurable erosion was observed UHTCMC-based nozzles. The mechanism consisted formation ZrO2 intermediate layer, liquid SiO2 layer surface that displaced action gas flux towards divergent part protecting it from further oxidation. Both specimens HP SPS displayed similar performance, very slight differences which attributed small porosity. These demonstrated capability complex-shaped prototypes made developed UHTCMC survive exposure environments representative realistic space propulsion application, an overall operating time up 30 s, without any failure nor erosion, making promising step development components.
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ژورنال
عنوان ژورنال: Journal of Advanced Ceramics
سال: 2023
ISSN: ['2227-8508', '2226-4108']
DOI: https://doi.org/10.26599/jac.2023.9220759