Document Type : Research Paper

Authors

1 Department of Mechanical Engineering, Tarbiat Modares University, Tehran, Iran

2 Department of Mechanical Engineering, Arak University, Arak, Iran

3 Department of Mechanical Engineering, Tarbiat Modares University, Tehran IRAN

Abstract

In this paper, the heat transfer and ablation thermal insulators in solid rocket motor are investigated. Therefore, by collecting and solving the thermal ablation equations, a computer program, using MATLAB software, is developed which can predict the thermal response of insulators in different operating conditions and compare the performance of these insulators. The heat and mass transfer equations are considered in two dimensions in a solid body. We used the equations, finite volume method with implicit formulation for time dependency to solve equations. The reaction equation which written in the form of Arrhenius, is solved using Runge-Kutta method, and the density and the flux of the gas produced at each step are obtained. Also we represent a model for the rate of recession.

Keywords

Main Subjects

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