Numerical Simulation Of Flow In Variational Section Of Segmented Solid Rocket Motor

The problem about the internal flowfields of segmented solid-propellant motors is very complicated and it works easily anomaly. One research way of SRM is numerical simulation.The segmented solid-propellant motor is studied in this paper. The program of one-dimensional internal ballistic calculation of segmented solid-propellant motors which is assembled with star and tube grain is written by use of C++ . The quasi-steady method has been used to calculate internal ballistics. It is believed that the combustion-chamber is under the equilibrium condition in one time and at the next time it is under the next equilibrium condition. At the same time, the effect of corrosion on the combustion during the calculation of internal ballistics is considered to make the results nearer to the factual data. The parameters of gas exhaust at all the spots along the axis have been calculated by means of the one-dimension iteration and it is clearly noted that the eroding combustion cannot be neglected. At the same time, the two-dimensional axisymmetric compressible Navier-Stockes equations and the standard k-e turbulent model are used. Numerical simulation of the segmented solid-propellant motors with two-dimensional axisymmetric flow field using the CFD software. In order to researching the complicity geometry flow field in SRM, two states are been considered respectively: (l)two blocks are separated by thermal protection.(2) two blocks are separated not by thermal protection, the distance between the two blocks is 5mm 10mm 20mm wide. Parameters of gas flow varieties with different conditions have been obtained in the paper. The result of one-dimensional internal ballistic is compared with CFD simulation result to examine the accuracy of the solutions. The simulation results are used to analyze the problem when the SRM working failure may occur and demonstrate the details of flow field at the two blocks discontinue domain.