Abstract
A numerical approach to simulate the evolution of the combustion surface of an energetic composite materials is described. Cubic spline interpolation is used to describe the dynamically changing shape of the combustion surface. The statement of the interpolation problem for the parametric description of the geometry and the problem of choosing the method for parameterizing the control points are given. The direct step-bystep method is used to calculate the combustion front. The normal velocity of the combustion surface is variable and is determined from the solution of an additional gas dynamics problem. The basic formulae for calculating the combustion rate of a solid propellant that consists of a particle-reinforced energetic composition are given. Examples of combustion simulation of a laboratory-scale structure for three values of the initial geometry parameters are presented.
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