【摘要】 针对火星进入器的复杂催化加热作用,基于自研CFD平台,以进入器70°球锥防热大底为研究对象,求解三维可压缩Navier-Stokes方程,获得基于火星大气的考虑多种催化作用的高超声速非平衡气动加热数值模拟结果。结果表明,气体通过激波后发生大规模离解,激波层内尤其驻点区域呈现化学非平衡状态,高温真实气体效应显著,壁面催化效应对化学非平衡气动加热影响显著,完全催化壁预测值最为保守,而完全非催化壁结果最低,不同模型差别高达数倍。分析认为,CO₂和O₂复合作用是火星进入器壁面催化加热主要作用因素,需要根据热防护材料对壁面催化机理作有效表征,进而实现气动加热的精细化预测。更多还原

【Abstract】 Three-dimensional compressible Navier-Stokes equations are numerically solved for the 70° sphere-cone heatshield to predict the hypersonic chemical non-equilibrium aeroheating with catalytic effects. Numerical results show that a substantive amount of inflow gas dissociates in the shock layer,which causes chemical non-equilibrium flow with remarkable high-temperature real-gas effect,particularly near the stagnation. The surface catalysis markedly influences the total heating load,and the heatfluxes for non- and fully catalytic walls are predicted to bear the lowest and highest aeroheating bounds. The determination of O₂ and CO₂recombination is expected to be the significant sources of the catalytic heating,and the characterization of the catalytic mechanism of the thermal protection materials is needed so as to precisely predict the Mars entry aeroheating.更多还原