大迎角前体涡控制方法综述
Reviews of forebody vortex control method at high angles of attack
查看参考文献79篇
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文摘
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大迎角下飞行器的常规舵面处于机身/弹身的尾涡中,偏航控制能力严重下降。同时,背风侧的非对称涡系导致压力非对称分布,从而诱发出一个几乎与法向力同量级的侧向力,并伴随着很大的偏航力矩。前体涡控制方法可以为细长飞行器提供所需的偏航力矩,在大迎角机动飞行领域具有广阔的应用前景。本文总结了国内外近十年发展的大迎角前体涡控制方面的新方法。其中,被动控制方法包括边界层转捩带、微鼓包、微凹坑、边条、自激振荡旗帜和涡流发生器等;主动控制方法包括等离子体激励器、单孔位微吹气、轴向吹气、合成射流激励器、非定常小摆振片和充气边条等。着重介绍了各种方法的控制效果、机理和适用范围。在这些方法中,涡流发生器、合成射流激励器、非定常小扰动片、等离子体激励器、单孔位微吹气等线性控制方法均有可能提高细长体飞行器大攻角时的机动能力,具有一定的工程应用价值。最后,对大迎角前体涡控制方法的应用前景和未来新的发展方向进行了展望。 |
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其他语种文摘
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At high angles of attack, the conventional rudders of fighters or tactical missiles are affected by the wake flow generated by the fuselage, and its yaw control power may dropdramatically together with leeward asymmetry vortices inducing asymmetry pressure distributions, provoking a side force with the same order of magnitude as that of normal force, and accompanying a strong yaw moment. Forebody vortex control methods can provide a desired yaw control moment for aircrafts at high angles of attack, and they have wide application prospect in the field of maneuver flight at high angles of attack. In this paper, the new methods developed in the past ten years were reviewed.The passive methods include boundary layer transition strips, bumps, dimples, strakes, nose bluntness, fluttering flag, and vortex generators etc. The active methods include plasma actuators, micro blowing, nose blowing, synthetic jet, fast-swing mini-tip strake and microballoon array actuators etc. The control effect, mechanism and applicable scope were emphatically introduced for various methods. The maneuverability of slender body at high angles of attack can be improved by the linear control methods including vortex generators, synthetic jet, fast-swing mini-tip strake, plasma actuators, micro blowing, which are practical in engineering application.Finally, the application prospect and development trend were discussed for the forebody vortex control method at high angles of attack. |
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来源
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空气动力学学报
,2017,35(3):354-367 【核心库】
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DOI
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10.7638/kqdlxxb-2017.0018
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关键词
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大迎角
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细长体
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前体涡控制
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侧向力
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非对称涡
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偏航控制
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地址
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1.
西北工业大学, 翼型叶栅空气动力学国家重点实验室;;高温气体动力学国家重点实验室, 陕西, 西安, 710072
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西北工业大学, 翼型叶栅空气动力学国家重点实验室, 陕西, 西安, 710072
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语种
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中文 |
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文献类型
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综述型 |
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ISSN
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0258-1825 |
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学科
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航空 |
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基金
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国家教育部高等学校学科创新引智计划项目
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文献收藏号
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CSCD:6063888
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