临近空间表面波等离子体减阻性能分析

蔡红华; 聂万胜; 丰松江

doi:10.11728/cjss2014.03.304

临近空间表面波等离子体减阻性能分析

doi: 10.11728/cjss2014.03.304

装备学院航天装备系北京 101416

基金项目: 国家高技术发展计划资助项目

详细信息

通讯作者:
蔡红华,E-mail:honghuacai@aliyun.com

聂万胜,E-mail:nws1969@126.com

中图分类号: V411
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- 被引次数: 0
出版历程
- 收稿日期: 2013-08-11
- 修回日期: 2013-10-29
- 刊出日期: 2014-05-15

Analysis of Surface Wave Plasma Drag Reduction Properties in Near Space

Department of Space Equipment, the Academy of Equipment, Beijing 101416

摘要

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.
- 临近空间 /
- 飞艇 /
- 表面波等离子体 /
- 流动控制
Abstract: 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 lift 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.
- Near space /
- Airship /
- Surface wave plasma /
- Flow control

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参考文献(15)

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