为有效的组织固体火箭冲压发动机的二次燃烧,采用标准二方程模型、EDM(eddy-dissipationmodel)模型和粒子燃烧King模型,对二元双下侧进气式固体火箭冲压发动机补燃室三维两相流进行了数值模拟。得到了不同空燃比条件下补燃室内流场参数的分布规律并对其进行了初步分析。结果表明:在一定范围内空燃比的变化会引起补燃室各参数分布的变化,从而显著影响固冲发动机二次燃烧。

In order to organize the secondary combustion in the solid rocket ramjet motor effectively, the three dimensional and twophase flow in the afterburning chamber with binary dual underside inlet mode was numerically simulated by means of standard κ-ε turbulence model, one step eddy-dissipation combustion model and King model. The distribution laws of some parameters under different air to fuel mass fraction ratios were obtained and analyzed preliminarily. The results show that the change of air to fuel mass fraction ratio within a certain range would cause a corresponding change of the distribution of some parameters and have an obvious influence on the secondary combustion in the afterburning of the solid rocket ramjet motor.