Experimental analysis of SiC-based refractory concrete in hybrid rocket nozzles

Abstract : Hybrid propulsion represents a good alternative to the more widely used liquid and solid systems. This technology combines some important specifications of the latters, as the possibility of re-ignition, thrust modulation, a higher specific impulse than solid systems, a greater simplicity and a lower cost than liquid systems. Nevertheless the highly oxidizing environment represents a major problem as regards the thermo-oxidation and ablative behavior of nozzle materials. The main goal of this research is to characterize a silicon carbide based micro-concrete with a maximum aggregates size of 800 mu m, in a hybrid propulsion environment. The nozzle throat has to resist to a highly oxidizing polyethylene/nitrous oxide hybrid environment, under temperatures up to 2900 K. Three tests were performed on concrete-based nozzles in HERA Hybrid Rocket Motor (HRM) test bench at ONERA. Pressure chamber evolution and observations before and after tests are used to investigate the ablated surface at nozzle throat. Ablation behavior and crack generation are discussed and some improvements are proposed.
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Contributeur : Imt Mines Albi Ecole Nationale Supérieure Des Mines d'Albi-Carmaux <>
Soumis le : mardi 6 novembre 2018 - 15:40:16
Dernière modification le : vendredi 14 décembre 2018 - 14:46:04
Document(s) archivé(s) le : jeudi 7 février 2019 - 15:27:16


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Raffaele D'Elia, Gérard Bernhart, Jouke Hijlkema, Thierry Cutard. Experimental analysis of SiC-based refractory concrete in hybrid rocket nozzles. Acta Astronautica, Elsevier, 2016, 126 (SI), p. 168-177. 〈http://www.sciencedirect.com/science/article/pii/S0094576516304027〉. 〈10.1016/j.actaastro.2016.04.034〉. 〈hal-01609028〉



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