Reaction flow field change in SRM under high flight acceleration load

For studying the chemical reaction flow field of the aluminized solid rocket under high flight acceleration, the numerical simulation based on aluminium particle combustion model and turbulent no-premixed combustion model was performed. Contrast to the numerical simulation result of no-flight load, the distribution of flow field parameters such as temperature, concentration and reaction rate are changed by flight acceleration. Some obtained numerical results were tested by examination. The results show that, the numerical arithmetic recur the test malfunction of the solid rocket. Aluminum particle accumulation and intense exothermic reaction induces the high temperature region and insulator abnormal erosion of combustor under high overload. Designing of thermo protected structure must match flow spectrum.