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基于等离子体合成射流的高超声速飞行器标模激波控制实验

谢玮,  胡国暾,  石伟,  周岩,  卢洪波,  罗振兵

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谢玮, 胡国暾, 石伟, 周岩, 卢洪波, 罗振兵. 基于等离子体合成射流的高超声速飞行器标模激波控制实验[J]. 气体物理. doi: 10.19527/j.cnki.2096-1642.1065
引用本文: 谢玮, 胡国暾, 石伟, 周岩, 卢洪波, 罗振兵. 基于等离子体合成射流的高超声速飞行器标模激波控制实验[J]. 气体物理. doi: 10.19527/j.cnki.2096-1642.1065
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XIE Wei, HU Guo-tun, SHI Wei, ZHOU Yan, LU Hong-bo, LUO Zhen-bing. Experiment on Shock Wave Control of a Hypersonic Vehicle Standard Model Based on Plasma Synthetic Jet[J]. PHYSICS OF GASES. doi: 10.19527/j.cnki.2096-1642.1065
Citation: XIE Wei, HU Guo-tun, SHI Wei, ZHOU Yan, LU Hong-bo, LUO Zhen-bing. Experiment on Shock Wave Control of a Hypersonic Vehicle Standard Model Based on Plasma Synthetic Jet[J]. PHYSICS OF GASES. doi: 10.19527/j.cnki.2096-1642.1065
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基于等离子体合成射流的高超声速飞行器标模激波控制实验

doi: 10.19527/j.cnki.2096-1642.1065

  • 1. 国防科技大学空天科学学院, 湖南长沙 410073;

  • 2. 中国运载火箭技术研究院, 北京 100076;

  • 3. 中国航天空气动力技术研究院, 北京 100074

基金项目: 

国家自然科学基金(12202488, 12002377, 52075538, 12072352, T2221002)

湖南省自然科学基金(2020JJ5670,2020JJ2031, 2021JJ40672)

详细信息
    作者简介:

    谢玮(1998-) 男, 博士, 主要研究方向为高速主动流动控制。E-mail:nudtxiewei@163.com

  • 中图分类号: V211.7

Experiment on Shock Wave Control of a Hypersonic Vehicle Standard Model Based on Plasma Synthetic Jet

  • 1. College of Aeronautics and Astronautics, National University of Defense Technology, Changsha 410073, China;

  • 2. China Academy of Launch Vehicle Technology, Beijing 100076, China;

  • 3. China Academy of Aerospace Aerodynamics, Beijing 100074, China

    摘要
  • 摘要: 基于等离子体合成射流(plasma synthetic jet,PSJ)的新型主动流动控制技术由于具有无需气源、控制力强、激励频带宽等优势,在激波控制领域极具应用潜力。在高超声速风洞中实验研究了单脉冲PSJ对高超声速飞行器标模头部弓形激波及侧翼激波的控制效果及对飞行器的减阻作用。结果表明,逆向PSJ可使高超声速飞行器标模头部弓形激波脱体距离显著增大,横向PSJ可使侧翼激波基本完全消除,动态力传感器测得飞行器最大瞬时减阻率约为15.5%,但传感器测得的阻力变化存在大约250 μs的延迟。研究了放电能量、来流总压、出口直径以及腔体体积对头部弓形激波控制效果的影响。

     

    Abstract: The novel active flow control technology based on plasma synthetic jet (PSJ) has great application potential in the field of shock wave control due to its advantages such as no gas source, strong control ability and wide excitation frequency band. The control effect of single-pulsed PSJ on head bow shock and wing shock of a hypersonic vehicle model and the drag reduction effect were experimentally studied in a hypersonic wind tunnel. The results show that the opposing PSJ can significantly increase the standoff distance of the head bow shock, and the transverse PSJ can basically eliminate the wing shock completely. The maximum instantaneous drag reduction rate of the vehicle measured by the dynamic force sensor is about 15.5%, but the drag change measured by the sensor has a delay of about 250 μs. The influence of discharge energy, incoming flow total pressure, exit diameter and cavity volume on the control effect of the head bow shock was also studied.

     

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出版历程
  • 收稿日期:  2023-06-08
  • 修回日期:  2023-06-18
  • 网络出版日期:  2023-08-21

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