超低轨卫星气动阻力特性  

Aerodynamic Drag Characteristics of Ultra-Low Orbit Satellites

作　　者：王晓亮[1] 姚小松 高爽 刘国华 WANG Xiaoliang;YAO Xiaosong;GAO Shuang;LIU Guohua(School of Aeronautics and Astronautics,Shanghai Jiao Tong University,Shanghai 200240,China;Innovation Academy for Microsatellites of Chinese Academy of Sciences,Shanghai 201203,China)

机构地区：[1]上海交通大学航空航天学院,上海200240 [2]中国科学院微小卫星创新研究院,上海201203

出　　处：《上海交通大学学报》2022年第8期1089-1100,共12页Journal of Shanghai Jiaotong University

基　　金：中国科学院微小卫星创新研究院自主部署课题(Y9ZZBSYG01)。

摘　　要：以180~300 km超低轨卫星为研究对象,采用自由分子流模拟方法中可准确模拟三维复杂外形的直接模拟蒙特卡洛(DSMC)法研究了典型外形的气动阻力特性.通过不同速度率条件下圆球和平板的理论阻力系数及不同速度率下70°钝体外形的气动实验数据与DSMC计算结果的比较,验证了三维DSMC方法对外形和网格的适应性.针对几类典型的卫星外形的阻力特性进行了计算比较,得出压差阻力、剪切阻力、总阻力及无量纲阻力系数随高度和外形的变化特性.超低轨卫星通过外形的优化设计可降低阻力约10%,能够有效改善其在轨运行特性,且可降低对卫星自身相关系统的设计需求.Taking the 180~300 km ultra-low orbit satellite as the research object, the aerodynamic drag characteristics of the typical shapes were studied by using the direct simulation Monte Carlo(DSMC) method in the free molecular flow simulation method, which can accurately simulate the three-dimensional complex shapes. By comparing the theoretical drag coefficients of spheres and plates at different velocity rates and the aerodynamic experimental data of 70° bluff body shapes at different velocity rates with the DSMC calculation results, the adaptability of the three-dimensional DSMC method to shape and mesh is verified. The drag characteristics of several typical satellite shapes were calculated and compared, and the pressure difference drag, shear drag, total drag and dimensionless drag coefficients with altitude and shape were obtained. The optimized design of the shape of the ultra-low orbit satellite can reduce the drag by about 10%, which can effectively improve its on-orbit operation characteristics and reduce the design requirements of the own related systems of the satellite.

关 键 词：超低轨 卫星 气动阻力 直接模拟蒙特卡洛 70°钝体 

分 类 号：V211[航空宇航科学与技术—航空宇航推进理论与工程]