Abstract
This paper presents a simple method for numerical simulation of axisymmetric two-dimensional temperature distribution in a composite structure solid rocket nozzle. A body-fitted moving curvilinear coordinate system is adopted to deal with the complex contour of the nozzle and the moving boundary of ablation surface. The concept of equivalent volumetic heat capacity is also used to unify the energy balance equations of the control volume for all different material layers, which makes the moving boundaries caused by pyrolysis processes inside the material easy to handle. A time forward explicit scheme for the inner nodes and a time backward implicit scheme for the boundary nodes are used in numerical calculation. A sample calculation for an experimental solid rocket nozzle indicates that the numerical results of the tempeniature distribution agree with the measured data fairly well.
Published Version
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