This study entails the analysis of the working performance of solid rocket motors (SRM), featuring the essential element of internal ballistic analysis. Therefore, the internal flow field under the condition of burning surface regression needs to be calculated. The boundary of the internal flow field of the SRM moves with the combustion of the propellant; therefore, it is necessary to accurately track the mobile interface to provide boundary conditions for the flow field calculation. The coupling of the level set method and the volume fraction method is utilized to track the burning surface, and the porous media model is used to divide the fluid and solid calculation domains. The interface between the two calculation domains is used to characterize the burning surface, and then, the area of the burning surface is obtained by solving the area of the interface. The calculation and analysis are carried out for SRM with tubular charge and star charge. The results verify that the calculation model can accurately calculate the transient internal flow field of SRM under the condition of burning surface regression.

中文翻译：

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固体火箭发动机瞬态内部流场模拟的液位集和流体体积耦合方法

这项研究需要对固体火箭发动机 (SRM) 的工作性能进行分析，其中包含内部弹道分析的基本要素。因此，需要计算燃烧面回归条件下的内部流场。SRM内部流场的边界随着推进剂的燃烧而移动；因此，需要准确跟踪移动界面，为流场计算提供边界条件。利用水平集法和体积分数法的耦合跟踪燃烧面，利用多孔介质模型划分流体和固体计算域。两个计算域之间的界面用于表征燃烧表面，然后，燃烧面面积通过求解界面面积得到。对管状装药和星型装药的SRM进行了计算分析。结果验证了该计算模型能够准确计算燃烧面回归条件下SRM的瞬态内部流场。