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| 引用本文： | 周岩,夏智勋,罗振兵,彭文强,邓雄,王林.目次[J].国防科技大学学报,2019,41(6):12-18. |
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| 作者姓名： | 周岩 夏智勋 罗振兵 彭文强 邓雄 王林 |
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| 作者单位： | 国防科技大学空天科学学院,湖南长沙,410073 |
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| 基金项目： | 国家自然科学基金资助项目（11872374、11602299、11572349）；国防科技大学科研计划项目（ZK18-03-11） |
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| 摘 要： | 为改善等离子体合成射流激励器在稀薄空气环境中的控制效果,增强其临近空间环境适应性,开展了腔体增压条件下激励器工作特性的研究。建立了腔体增压效果理论分析模型,计算结果表明:采用高压气源供气可以较好地提升激励器腔体气压,并且腔体气压对高压气源气压具有较好的跟随性,从而为射流强度调节提供了一种新的方式。搭建了腔体增压等离子体合成射流激励器实验系统,开展了腔体增压压力和射流流场特性测量,实验测量结果与计算结果吻合良好,误差小于2.6%。高速纹影观测显示:在腔体增压作用下,激励器控制力得到显著改善,射流锋面峰值速度由256 m/s提升至507 m/s。
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| 关 键 词： | 等离子体合成射流 腔体增压 临近空间飞行器 主动流动控制 |
| 收稿时间： | 2018/7/16 0:00:00 |
| 修稿时间： | 2019/7/3 0:00:00 |
Characterization of plasma synthetic jet actuator with cavity pressurization |
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| ZHOU Yan,XIA Zhixun,LUO Zhenbing,PENG Wenqiang,DENG Xiong and WANG Lin.Characterization of plasma synthetic jet actuator with cavity pressurization[J].Journal of National University of Defense Technology,2019,41(6):12-18. |
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| Authors: | ZHOU Yan XIA Zhixun LUO Zhenbing PENG Wenqiang DENG Xiong and WANG Lin |
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| Institution: | College of Aeronautics and Astronautics, National University of Defense Technology, Changsha 410073, China,College of Aeronautics and Astronautics, National University of Defense Technology, Changsha 410073, China,College of Aeronautics and Astronautics, National University of Defense Technology, Changsha 410073, China,College of Aeronautics and Astronautics, National University of Defense Technology, Changsha 410073, China,College of Aeronautics and Astronautics, National University of Defense Technology, Changsha 410073, China and College of Aeronautics and Astronautics, National University of Defense Technology, Changsha 410073, China |
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| Abstract: | Plasma synthetic jet actuator has shown wide and promising application prospects in future flight vehicle/aerospace engine aerodynamic control, on account of its superiorities of wide frequency band, rapid response, high exhaust speed and no moving parts. To increase its authority in rarefied air and improve its environmental suitability in near space flow control, the characteristics of plasma synthetic jet actuator with cavity pressurization are investigated. A simplified model is proposed to analyze the cavity pressurization performance. The calculation shows that the chamber pressure is effectively improved by the high pressure air supply. Besides, the chamber pressure shows good following characteristics, which provide a novel method to control plasma synthetic jet intensity. The experimental system of plasma synthetic jet actuator with cavity pressurization is built. The measured chamber pressure is in good agreement with the calculated result, with a maximum error of 2.6 %. The high-speed schlieren visualization shows that the jet front velocity is significantly improved with cavity pressurization. The peak velocity increases from 256m/s to 507m/s. |
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| Keywords: | plasma synthetic jet cavity pressurization near space aircraft active flow control |
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