飞行器进入火星大气的流场预测

针对火星着陆探测器进入-下降-着陆过程的高超声速进入阶段, 利用三维并 行程序求解流体动力学Navier-Stokes方程与化学反应动力学模型, 分析火星 科学实验室进入火星大气时探测器周围的流场结构、化学非平衡效应影响和气 动特性变化规律. 结果表明, 对于完全气体模型, 来流的热力学性质参数选 取影响激波位置和强度. 在化学非平衡效应影响下, 探测器头部激波脱体距离 大幅减小, 驻点压力变化不大, 波后温度显著降低. CO₂在激波后大量分解, 消耗相当能量. 流线结构显示, 探测器尾迹流动中存在复杂的旋涡运动等流动 分离现象. 

Flow Field Prediction of an Orbiter Entering the Mars Atmosphere

Based on the hypersonic entry in the Entry-Descending-Landing procedure, the three-dimensional Navier-Stokes equations are solved by a parallel code to analyze the flow field structures, aerodynamic characteristics and their variation patterns of the Mars Science Laboratory entering the Martian atmosphere with and without the chemical reaction models. The analysis shows that parameters of the thermal dynamics and the transportation have an effect on the position and intensity of the shock wave. As a result of the chemical non-equilibrium effect, the shock layer is strongly compressed, the stagnation pressure decreases and the maximum temperature behind the shock is highly reduced where large number of CO₂ is dissociated. Results of the streamlines on symmetric plane and in space reflect the complicated three-dimensional separation flows in the wake.