Detailed chemistry simulations of heterogeneous solid propellant combustion at the microstructure scale are very costly as they involve large and stiff chemical schemes in the gas phase. A usual workaround is to use global chemistry to approximate gas phase reactions. A drawback of this approach is the need for an a priori calibration which necessitates reference data and often limits the operating conditions range of validity. An alternative method based on 1-D burner-stabilized flames tabulation is proposed in this paper. The theoretical and numerical frameworks are detailed. An appropriate tabulation space is introduced to store useful thermochemical variables as well as Jacobian terms used for time-integration. Jump conditions are also rewritten to cope with tabulated chemistry formalism. Several 1-D validations are performed on classical propellant compositions. Detailed comparisons with available experimental data demonstrate the ability of the proposed methodology to tackle inner flame structure (temperature and species) as well as the evolution of the burning rate with pressure and composition. Finally, 2-D laminate propellant simulations are conducted showing the ability of the methodology to capture complex flame regimes and associated burning rate modifications.

由于微观结构涉及气相中庞大而僵硬的化学方案，因此在微观结构规模上对异质固体推进剂燃烧进行详细的化学模拟非常昂贵。通常的解决方法是使用全局化学方法近似气相反应。该方法的缺点是需要先验校准，该先验校准需要参考数据并且经常限制有效的操作条件范围。本文提出了一种基于一维燃烧器稳定火焰列表的替代方法。详细的理论和数值框架。引入了适当的表格空间来存储有用的热化学变量以及用于时间积分的雅可比项。跳转条件也被重写以应对列表化学形式主义。对经典推进剂成分进行了几次一维验证。与现有实验数据的详细比较表明，所提出的方法具有解决内部火焰结构（温度和物质）以及燃烧速率随压力和成分变化的能力。最后，进行了二维层压板推进剂模拟，显示了该方法能够捕获复杂的火焰状况和相关的燃烧速率修改的能力。