火星进入的气动力特性预测模型分析

发布时间：2018-12-12 03:45

【摘要】：针对火星探测器的高超声速进入问题,利用三维并行程序求解流体力学Navier-Stokes方程,分别考虑真实气体模型和完全气体模型,分析模型及参数对气动力特性预测的影响,旨在得到准确、高效和可靠的火星进入器气动力特性预测模型.采用真实气体模型对海盗号进行了沿飞行轨道的数值模拟,气动力特性预测结果与飞行数据一致,验证了火星大气热化学模型及数值方法.分别采用真实气体模型和完全气体模型对海盗号升力式进入和探路者号零攻角进入进行了气动力特性预测,结果表明采用等效比热比的完全气体模型的预测值非常接近真实气体模型,偏差均在1%左右,配平攻角相差约0.4°,来流比热比模型的气动力特性预测值偏差很大.火星进入器的气动力预测建议采用真实气体模型和等效比热比完全气体模型.
[Abstract]:In order to solve the hypersonic entry problem of the Mars probe, a three-dimensional parallel program is used to solve the hydrodynamic Navier-Stokes equation. The real gas model and the complete gas model are considered, respectively, and the influence of the model and parameters on the prediction of aerodynamic characteristics is analyzed. The aim is to obtain accurate, efficient and reliable prediction model of aerodynamics characteristics of Mars entry vehicle. The real gas model is used to simulate the Pirates in orbit. The prediction results of aerodynamic characteristics are consistent with the flight data and verify the Martian atmospheric thermochemical model and numerical method. The real gas model and the complete gas model are used to predict the aerodynamic characteristics of the Viking lift entry and the Pathfinder at zero angle of attack respectively. The results show that the predicted values of the complete gas model using the equivalent specific heat ratio are very close to the real gas model, the deviations are all about 1%, the angle of attack is about 0.4 掳, and the prediction value of the aerodynamic characteristics of the specific heat ratio model is very large. Real gas model and equivalent specific heat ratio complete gas model are recommended for aerodynamics prediction of Mars entry vehicle.
【作者单位】：中国航天空气动力技术研究院;
【基金】：国家自然科学基金项目资助(11402251)
【分类号】：V476.4;V411

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