Stefano Mungiguerra, Giuseppe D. Di Martino, Anselmo Cecere, Raffaele Savino, Diletta Scit
DOI Number XXX-YYY-ZZZ
Conference Number HiSST-2022-209
This paper presents the results of extensive test campaigns carried out in the framework of the
European C3HARME project, for the characterization of Ultra-High-Temperature Ceramic Composites
for near-zero ablation Thermal Protection Systems (TPS) and near-zero erosion rocket nozzles. Tests
were carried out in a supersonic arc-jet wind tunnel, where conditions typical of atmospheric re-entry
were reproduced, and in different configurations in a lab-scale hybrid rocket engine. Materials having
a ZrB2-SiC-based matrix and carbon fibre reinforcement showed an outstanding erosion resistance for
both applications. In the arc-jet environment, a spontaneous temperature jump of 4-500 K was
observed, which was attributed to a combination of increased catalytic activity and reduced thermal
conductivity upon oxidation. In the high-pressure environment of the propulsion tests, long-fibre
reinforcement demonstrated better mechanical resistance, which can be improved by proper tuning of
the densification process. The small-scale results paved the way for large scale qualification tests on a
complete TPS assembly and a medium-scale solid rocket nozzle.