Numerical Investigation Of Flow Field In Spinning Solid Rocket Motor

The study of performance of SRM varying with spinning speed was mainly paid attention on the aspects of the spinning effects to interior ballistic performance, propellant combustion rate and the ablation of the heat-resistant material in rocket for a long time. The study of flow field configuration in spinning SRM is still a key problem. The CFD technique was employed to investigate the chamber-nozzle united flow field in spinning SRM in this thesis, and the configuration characteristics of flow field in spinning SRM were analysed emphatically.On account of the vortical characteristics in spinning SRM, the numerical simulation method of the swirling flow field was investigated firstly. The standard k -εturbulent model, RNG k -εturbulent model and RSM turbulent model's validation to the swirling flow field was examined, and the calculated precision problem of swirling flow field was also investigated. Based on the RSM turbulent model, two kind of spinning SRM are simulated respectively:First, the gas flow field in inside-burning SRM was calculated in the condition of different rotating speed. The vortical characteristics of exhaust gas in SRM, the pressure difference between propellant surface and chamber centre, axial velocity and radical velocity distribution in chamber, the effect to seal in the front of SRM caused by vortex and the turbulent characteristics in SRM were analysed particularly.Second, the gas flow field in end-burning SRM was calculated in the condition of different rotating speed. The vortical characteristics of exhaust gas, axial velocity and radical velocity distribution, the configuration change of flow field in SRM and turbulent characteristics in end-burning SRM were analysed specially.