头部钝化的无翼航天器气动性能研究  

Study on aerodynamic performance of wingless spacecraft with head blunted

作　　者：张帅 方蜀州[1] 郭建 ZHANG Shuai;FANG Shuzhou;GUO Jian(School of Aerospace Engineering,Beijing Institute of Technology,Beijing 100081,China)

机构地区：[1]北京理工大学宇航学院,北京100081

出　　处：《飞行力学》2020年第6期56-62,69,共8页Flight Dynamics

摘　　要：分别采用N-S方法与DSMC方法对头部钝化的无翼航天器及相应的人工钝头(ABLE)构型进行计算分析,对比了ABLE构型在超声速低空连续流与高超声速高空稀薄流中的气动性能,研究了ABLE构型的减阻增升原理及其在稀薄流中的减阻增升效率。研究结果表明:在超声速低空连续流中,ABLE构型能以较小的热流增加为代价,显著提高升阻比,其增升效率随着迎角的增大而提高,而减阻效率受迎角的影响较小;在高超声速高空稀薄流中,ABLE构型的热流增量较大,但仍能显著提高升阻比,其增升效率随着迎角的增大而提高,且增升效率更高。不同于连续流中的情况,虽然ABLE构型能有效减小波阻,但是增加的湿润面积使得摩擦阻力剧增,从而使得总阻力增大。A research had been made to analyze aerodynamic performance of the blunt cone applying the ABLE concept in both low-altitude supersonic continuous flow and high-altitude hypersonic rarefied flow by solving N-S equation and DSMC method respectively. The purpose of the study is to explain the improved aerodynamics principle of ABLE configuration and further explore the aerodynamics performance in hypersonic rarefied flow. The results show that in supersonic continuous flow, with a slight increase of stagnation heat transfer, the ABLE configuration can significantly increase the lift-to-drag ratio. The lift increment efficiency of ABLE configuration improves with the increase of the angle of attack, while the drag reduction efficiency is less affected. In hypersonic rarefied flow, the lift-to-drag ratio is still significantly increased with a larger heat transfer increment. The lift increment efficiency of ABLE configuration increases with the increase of the angle of attack. Although the ABLE configuration can reduce the wave drag effectively, the increased wetting area makes the friction drag increase sharply, thus increasing the total drag.

关 键 词：人工钝头 N-S方法 DSMC方法 气动性能 

分 类 号：V411.4[航空宇航科学与技术—航空宇航推进理论与工程]