In this paper internal ballistics of a Solid Rocket Motor (SRM) with internal and external burnings is numerically simulated. Gas flow exists in two passages along the grain, one in the core of grain and the other between the grain and the casing. Solution domain including these two passages and the converging diverging nozzle, is discretized using control-volume finite-element method. Governing equations of quasi one-dimensional Euler equations are integrated over the control volumes. The flux vector components are related to the nodal values using a Physical Influence Scheme. Erosive burning is incorporated in our calculation using two different models. Since control volumes in two passages come together at the end of grain, the resulting system of equations deviates from a block tri-diagonal one, and therefore special care is needed for its solution. Performance of the present method is evaluated by comparing its numerical results for a reference SRM with the experimental data. Excellent agreement is achieved in this test case which validates the algorithm. Possibility of modeling a SRM including internal and external burnings, with an equivalent motor including only a core flow is also investigated. It is shown that such a modeling is not always possible.
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