Regenerative cooling of graphite nozzle for hybrid rockets using nitrous oxide as oxidant

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In the framework of the project, experimental and numerical apparatus have been developed for the study of the implementation of a regenerative cooling system in hybrid rocket engines for the nozzle erosion suppression. The investigators demonstrated in this first half year that this novel technology is possible and improves the performance of the propulsion system. Many experimental tests have been carried out and no nozzle erosion was observed in the tests, despite the considered configuration is extremely affected by this phenomenon when active cooling is not implemented. In addition, accurate numerical models have been developed for the study and the prediction of the motor operating conditions. These models give an insight in the multiphase physics occurring inside the cooling channels. These models allow the prediction of the nozzle temperature and hence, the occurrence of the nozzle erosion. Finally, the numerical results have been compared with the experimental ones in order to assess their validity. In this framework, two papers were obtained and submitted to two high quality Q1 journals.