Publication :


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

Authors: R. D'Elia, G. Bernhart, J. Hijlkema and T. Cutard
Year: 2016
Journal: Acta Astronautica.
Volume: 126, Pages: 168-177

DOI: 10.1016/j.actaastro.2016.04.034
Référencé ISI Web Of Science
Référencé Scopus

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 behaviour 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 μm, 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 behaviour and crack generation are discussed and some improvements are proposed.

Bibtex citation :
Author={D'Elia, R. and Bernhart, G. and Hijlkema, J. and Cutard, T.},
Title={Experimental analysis of SiC-based refractory concrete in hybrid rocket nozzles},
Journal={Acta Astronautica},

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