The Working Process Simulation Of Hybrid Rocket Motor Based On Thermal Coupling At Burning Surface

In the field of chemical rocket propulsion, hybrid rocket motors have the advantages of low cost, safety, controllable thrust and so on. The combustion in the hybrid rocket motor is affected by a lot of factors, such as heat transfer, flow and combustor structure, so the calculation of its performance is very difficult. In this paper, a general numerical simulation method based on thermal coupling at burning face was proposed. It is an effective way to simulate the working process of hybrid rocket motors.Based on the chemical equilibrium method, an internal ballistic calculation model was established. This model was used to calculated the performance of a test motor. All the performance parameters, such as regression rate, combustion pressure, thrust, specific impulse, etc. were obtained.By the analysis of the diffusion combustion of solid fuel, a general calculation model was proposed. This model is based on thermal coupling at burning face, turbulence model and PDF combustion model. To verify the model, two test motors reported by other researchers were calculated on the their test conditions. the calculations results agree well with the experimental results. Then, a two dimensional and a three dimensional hybrid rocket motors were simulated by the model, the flow field and the distribution of the regression rate were obtained.The internal ballistic and the flow field of the motor which has a tube grain were calculated by the models established in this thesis. The performance obtained by these two methods is nearly same. The influence of the combustion chamber structure and the nozzle throat on the performance was researched.The research results show that the internal ballistic calculation method and the calculation model are suitable for the simulation of the working process of hybrid rocket motors, and they are technical support for the further research on hybrid rocket motors.