Theoretical and experimental investigation of a low thrust paraffin/N2O hybrid rocket

Hybrid rocket propulsion can be considered the challenge for new generation space launchers since they demonstrated promising performance for future space missions by combining high performance, throttleability and stop-restart capabilities. However, the current state of the art suffers of scarce understanding of physics of solid/liquid combustion and not adequate fluid-dynamic modelling. Since combustion occurs heterogeneously, fuel and oxidizer heating, mixing and combustion efficiency are key issues to be investigated. In this context, a 200 N Paraffin/N2O hybrid rocket has been sized and realized at the School of Aerospace Engineering of La Sapienza in order to better understand the physics of hybrid propulsion for different inlet and operative conditions. A preliminary analysis of the possible failures, overpressures and back flows is mandatory to setup a safe test bench. 3DRANS for different port diameter have been simulated to account for the port diameter increase in time. A 5 step kinetic model has been investigated and proposed in order to be implemented in the CFD code.