跨流区超低轨航天器快速气动力计算方法  

Fast Aerodynamic Calculation Method for Ultra-Low Orbit Spacecrafts in Multi-Flow Regions

作　　者：郭晨林 陈方[1] 赵艳彬[2] 尤超蓝[2] 钱勇[2] 李文龙[2] 杨丽丽 GUO Chenlin;CHEN Fang;ZHAO Yanbin;YOU Chaolan;QIAN Yong;LI Wenlong;YANG Lili(School of Aeronautics and Astronautics,Shanghai Jiao Tong University,Shanghai 200240,China;Research and Development Center,Shanghai Institute of Satellite Engineering,Shanghai 201109,China)

机构地区：[1]上海交通大学航空航天学院,上海200240 [2]上海卫星工程研究所研发中心,上海201109

出　　处：《上海航天（中英文）》2022年第5期124-133,共10页Aerospace Shanghai（Chinese&English）

基　　金：国家自然科学基金(11672183)。

摘　　要：超低轨飞行器常工作在过渡流区中,过渡流区中气动特性多变,建模困难,目前缺少较好的快速气动力计算方法。在面元法的基础上,提出了设计迎风单元筛选算法与logistics-log桥函数,对连续流区与自由流区结果进行加权,实现超低轨卫星的气动力估算。在方法验证中,对圆柱与钝头双楔体在宽努森数(Kn)范围下的气动力进行测算,发现结果与直接模拟蒙特卡洛法(DSMC)数据一致。对典型超低轨飞行器地球重力场和海洋环流探测卫星(GOCE)的气动力进行分析,发现GOCE随着姿态变化阻力变化明显,需要舵面或陀螺仪进行姿态控制;在不同高度下的阻力量级变化大,在超低轨运行时需要动力系统维持高度。Ultra-low orbit spacecrafts often work in transitional flow regions. Since the aerodynamic characteristics in transitional flow regions are changeable,the modeling of ultra-low orbit spacecrafts is complex. At present,there is a lack of good fast aerodynamic calculation tools. Therefore,in this paper,a revised panel method is proposed to deal with the problem,which contains an upwind unit selection algorithm and a logistics-log bridge function. In the method verification,the aerodynamic forces of the cylinder and the blunt-headed double-wedge body are measured under a wide range of Knudsen number(Kn). The obtained results agree well with the data obtained by the direct simulation Monte Carlo(DSMC)method. The aerodynamic force of gravity field and steady-state ocean circulation explorer(GOCE)is analyzed. It is found that the drag of GOCE changes apparently with the change of attitude,and thus rudder surface or gyroscope is needed for the attitude control;the magnitude of the aerodynamic force varies significantly at different altitudes,and thus a reasonable power system is required to maintain the altitude.

关 键 词：超低轨飞行器 过渡流区 面元法 桥函数 重力场和环流探测卫星(GOCE) 

分 类 号：V411[航空宇航科学与技术—航空宇航推进理论与工程]