探测器超高速进入火星过程的高温真实气体效应对飞行稳定性和防热系统影响极大,需要在初步设计阶段对探测器的气动力热特性进行精确预测。文章构建了采用流场直角与表面非结构混合网格以及网格自适应的直接模拟蒙特卡洛方法,模拟稀薄环境高温真实气体效应的依赖于温度的多原子分子振动激发和8组份54化学反应模型。通过计算“火星探路者”外形气动力系数随攻角的变化,并与文献提供的计算结果对比,有较好的一致性,验证了该文算法的可靠性。文章模拟了“火星科学实验室”在火星大气环境70km高度、进入速度为5.85km/s下的高温真实气体效应对气动力、气动热和流场特征的影响。通过与完全气体计算结果对比,表明高温真实气体效应影响下的激波脱体距离减小,表面热流降低,轴向力系数增加、配平攻角减小、压心位置随攻角变化显著。 The high-temperature real gas effect of the detector entering the Mars process at high speed has a great influence on flight stability and heat-protection system. It is necessary to accurately predict the aerodynamic thermal characteristics of the detector during the preliminary design stage. In this paper, a direct simulation Monte-Carlo method using a mixed-grid and unstructured meshes of flow field and a grid-adaptive method was constructed to simulate the temperature-dependent polyatomic molecular vibration excitation of the real gas effect in the lean environment. Response model. By calculating the change of the aerodynamic coefficient with the angle of attack of the “Mars Pathfinder” profile and comparing with the calculation results provided by the literature, there is a good consistency and the reliability of the algorithm is verified. The article simulates the influence of high temperature real gas effect on the aerodynamic, aerodynamic heat and flow field characteristics of Mars Science Laboratory at a height of 70 km in Mars atmospheric environment and at an entry velocity of 5.85 km / s. Comparing with the calculation results of complete gas, it is shown that the off-shingling distance decreases, the surface heat flux decreases, the axial force coefficient increases, the angle of attack decreases, and the position of pressure center changes significantly with the attack angle under the influence of high temperature true gas effect.