| This paper bases on the theoretical study and the test validation method to predict the performance of angled nozzle small SRM. The main points are as follows:(1) The interior ballistic experiments of rocket shell launching are conducted. And the equipment of synchronization measure pressure is designed The experimental data, including the pressure at the throat of rocket and the photo of the jet flow, are obtained.(2) A numerical model included ignition process is constructed. Runge-Kutta method is applied to obtain the numerical results of this model. The numerical results agree with experimental data well. And the results are analyzed by using ballistic laws.(3) This paper investigated the three dimensional compressible jet flow with the fluent software. The relevant calculating model and turbulence model, adapting to the flow filed of angled nozzle small SRM, are selected. The subarea of grid and the appropriate boundary condition are adopted. The numerical results of jet flow are obtained and analyzed under the conditions of different angels and pressure.
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