摘要
为研究临近空间表面波等离子体减阻效果,基于流体宏观模型的基本特征,分析了表面波等离子体流动控制机理的基础,以飞艇为模型,对其在0°攻角情况下的流场进行仿真计算,比较了不同激励器控制方案的减阻效果,研究了飞艇尾部区域的等离子体流动控制效果.结果表明,表面波等离子体具有增加飞艇升力、减小飞艇阻力的效果;单侧控制方案最大减阻效果达7%左右,对称控制方案减阻效果明显优于单侧控制方案,最大减阻效果可达32%左右;表面波等离子体对飞艇尾部的流动分离具有很好的消除抑制作用.
In order to investigate the drag reduction effect of surface wave plasma in near space,this paper analyzes the surface wave plasma flow control mechanism based on basic characteristics of the fluid control macro model,simulates its flow field in the 0 degree angle of attack based on the airship model.The drag reduction effect of different actuator control program is compared,and the plasma flow control effect on the airship tail is studied.Results show that the surface wave plasma can increase the airship lift and reduce its flight resistance.The airship Hft can be increased through the unilateral control scheme,while the symmetrical control scheme is invalid for the airship lift because of the airship force balance in the vertical direction.The maximum drag reduction effect of unilateral control scheme is about 7 percent,and the symmetrical control scheme is better than unilateral one with its maximum drag reduction effect up to about 32 percent.The surface wave plasma has good elimination and inhibition of flow separation in the airship tail.
出处
《空间科学学报》
CAS
CSCD
北大核心
2014年第3期304-312,共9页
Chinese Journal of Space Science
基金
国家高技术发展计划资助项目
