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针对低轨卫星高空自由分子流区的飞行环境特征,采用GOCE卫星典型弹道下的气动数据对DSMC仿真方法进行了算例验证,并就CLL模型下不同物面反射系数对GOCE卫星流场特征及气动特性的预测差异进行了对比分析,给出不同物面反射系数对卫星阻力预测的定量差异.结果表明,本文方法所得气动阻力与文献结果吻合较好,能够在此飞行区域给出合理的气动阻力;当反射系数从0.1逐渐变化至1.0时,卫星流场的驻点区域、尾部方向舵区域压力分布逐渐从带状结构向扇形结构过渡;在所研究的工况下,随着物面反射系数的增加,摩阻系数预测结果偏大,压阻系数预测结果偏小,总阻力先增加后减小,约在反射系数0.8附近达到最大.
Aiming at the characteristics of the flight environment of LEO satellite free-jet region, the DSMC simulation method is validated by the aerodynamic data of typical GOCE satellite trajectory. The differences of prediction of aerodynamic characteristics are analyzed and the quantitative differences of the prediction of satellite drag are given. The results show that the aerodynamic drag obtained by this method is in good agreement with the literature results and can give a reasonable aerodynamic Resistance; when the reflection coefficient gradually changes from 0.1 to 1.0, the pressure distribution in the stagnation area and the tail rudder area of the satellite flow field gradually transitions from the ribbon structure to the fan-shaped structure; under the studied conditions, with the reflection coefficient The predicted results of the friction coefficient are larger, the predicted results of the piezoresistive coefficient are smaller, the total resistance first increases and then decreases, and reaches the maximum around the reflection coefficient of 0.8.