整流帽布局对全动舵附近流动结构及热环境分布规律的影响

doi:10.3969/j.issn.1000-1093.2021.08.009

摘要/Abstract

摘要： 基于局部外形优化改善空气舵附近区域局部热环境，可明显提升高马赫数飞行器热防护系统在恶劣环境下的适应性和生存能力。整流帽的应用作为高马赫数飞行器全动舵流动与气动热特性优化的有效手段，在近年来备受关注。建立一种适用于高马赫数完全气体可压缩流动的数值模拟方法，采用该方法开展整流帽布局及几何参数对全动舵附近流动结构及热环境分布规律的影响研究，并通过带整流帽布局的平板-全动舵模型激波风洞测热试验对数值模拟方法的准确性进行验证。结果表明：高速来流流经整流帽时将产生激波减速，在整流帽下游激波迅速膨胀分离，空气流动速度和加热能力均显著降低；从整体上看，设置整流帽能够显著降低整流帽展向宽度范围内的全动舵及附近平板气动热环境；随着整流帽楔角减小，全动舵气动加热整体呈恶化趋势；随着整流展宽增加，全动舵气动加热进一步减轻。

关键词: 全动舵, 整流帽, 流动结构, 热环境, 数值模拟

Abstract: The aerodynamic heating around aerodynamic rudder by local-configuration optimization is reduced to effectively enhance the livability and adaptability of high-Mach-number flight vehicle. The rectifying wedge is an effective means for optimizing the flow and aerodynamic heating characteristics for high Mach number flight vehicle. A numerical method is proposed to investigate the flow and aero-heating characteristics under a configuration of high-Mach-number plate/rudder. The proposed numerical method was used to study the influence of rectifying wedge on the flow structure and aerodynamic heating environment around all-movable rudder and validated through thermal measurement test in shock wave tunnel. The results show that the usage of rectifying wedge contributes to the reduction in both flow speed and aero-heating capability. This could attribute to the reduction effect of rectifying wedge shock wave on flow speed by the speedily expand and separation. Moreover, the aerodynamic heating environment around all-movable rudder within the span width region is found lower with rectifying wedge in general. With the decrease in rectifying wedge angle, all-movable rudder heating environment gets worse. Meanwhile, with the increase in span width, all-movable rudder heating environment gets better.

Key words: all-movablerudder, rectifyingwedge, flowstructure, heatingenvironment, numericalsimulation

中图分类号:

V211.74⁺5

檀妹静，杨光，李宇，周禹，曹占伟，闫昊，檀姊静. 整流帽布局对全动舵附近流动结构及热环境分布规律的影响[J]. 兵工学报, 2021, 42(8): 1648-1659.

TAN Meijing， YANG Guang， LI Yu， ZHOU Yu， CAO Zhanwei， YAN Hao， TAN Zijing. Influence of Rectifying Wedge on the Flow Structure and Aerodynamic Heating Environment around All-movable Rudder[J]. Acta Armamentarii, 2021, 42(8): 1648-1659.

参考文献

［1］李素循.激波与边界层主导的复杂流动［M］.北京：科学出版社，2007.
LI S X. Complicated flow governed by shock and boundary layer［M］.Beijing: Science Press, 2007.(in Chinese)
［2］ BABINSKY H，HARVEY J K. Shock wave-boundary-layer interactions ［M］. Cambridge, NY, US:Cambridge University Press，2011.
［3］张志成.高马赫数气动热和热防护［M］.北京：国防工业出版社，2003.
ZHANG Z C. Hypersonic aerothermodynamic and thermal protection［M］.Beijing: National Defense Industry Press, 2003.(in Chinese)
［4］ BERTIN J J, CUMMINGS R M. Critical hypersonic aerothermodynamic phenomena［J］. Annual Review of Fluid Mechanics，2006，38:129-157.
［5］ SCHURICHT P H, ROBERTS G T. Hypersonic interference heating induced by a blunt fin［C］∥ Proceedings of the 8th AIAA International Space Planes and Hypersonic Systems and Technologies Conference. Norfolk,VA,US: AIAA,1998.
［6］栗继伟，汪球，赵伟.高马赫数绕平板直立舵干扰气动热研究［J］.中北大学学报，2017，38（5）：609-613.
LI J W,WANG Q,ZHAO W. Investigation on aerodynamic heating characteristics of hypersonic flat plate/cylinder juncture flow［J］.Journal of North University of China,2017, 38（5）：609-613.(in Chinese)
［7］贾文利，罗金玲，康宏琳.飞行器翼舵缝隙气动热研究［C］∥第十八届全国激波与激波管学术会议论文集.北京:中国力学学会, 2018.
JIA W L,LUO J L,KANG H L. Aerodynamic heating of the gap between aircraft wing and rudder［C］∥Proceedings of the 18th National Conference on Shock Wave and Shock Tube. Beijing: The Chinese Society of Theoretical and Applied Mechanics,2018.(in Chinese)
［8］吴宁宁，康宏琳，罗金玲. 高速飞行器翼舵缝隙激波风洞精细测热试验研究［J］. 空气动力学学报, 2019,37(1):133-139.
WU N N, KANG H L, LUO J L. Experimental study on fine thermal measurement of high-speed aircraft wing rudder gap in shock wave tunnel［J］. Acta Aerodynamica Sinica, 2019,37(1):133-139. (in Chinese)
［9］ LI Q, NIE L, ZHANG K L, et al. Experimental investigation on aero-heating of rudder shaft within laminar/turbulent hypersonic boundary layers［J］. Chinese Journal of Aeronautics, 2019, 32(5): 1215-1221.
［10］ HINDERKS M，GLHAN A，RADESPIEL R . Simulation of hypersonic gap flow with consideration of fluid structure interaction ［C］∥Proceedings of the 34th AIAA Fluid Dynamics Conference and Exhibit. Portland, OR， US: AIAA, 2004.
［11］陈嘉阳，阎超.舵轴缝隙内流的数值模拟研究［C］∥第十五届全国计算流体力学会议论文集.北京：中国力学学会，2012：777-781.
CHEN J Y, YAN C. Numerical simulation of flow in rudder gap［C］∥Proceeding of the 15th Computational Fluid Dynamics Symposium. Beijing: Chinese Society of Theoretical and Applied Mechanics, 2012：777-781.(in Chinese)
［12］司于.飞行器控制舵局部区域热环境与热防护研究［M］.北京：北京航空航天大学，2013.
SI Y. Thermal environment and thermal protection research of local area between control-flap and maneuver vehicle［M］.Beijing: Beihang University,2013. (in Chinese)
［13］周佳.超声速飞行器钝舵缝隙气动热环境研究［D］.绵阳：西南科技大学，2014.
ZHOU J. Study of aerodynamic heating environment on blunt-fin gap of hypersonic vehicle［D］.Mianyang: Southwest University of Science and Technology,2014. (in Chinese)
［14］谭杰，孙晓峰，刘芙群，等. 高超声速平板/空气舵热环境数值模拟研究［J］. 空气动力学学报, 2019, 37（1）：153-159.
TAN J, SUN X F, LIU F Q, et al. Numerical simulation of aerodynamic heating environment of a hypersonic plate/rudder confi- guration［J］. Acta Aerodynamica Sinica,2019, 37（1）：153-159.(in Chinese)
［15］黄尚坤，肖素梅，庞宇飞，等.高超声速飞行器钝舵缝隙流动数值模拟研究［J］.航空工程进展，2019，10(2)：163-170，186.
HUANG S K,XIAO S M,PANG Y F, et al. Numerical investigation of flow in blunt-fin gap of hypersonic vehicle［J］. Advances in Aeronautical Science and Engineering，2019，10(2)：163-170,186.(in Chinese)
［16］阎超. 计算流体力学方法及应用［M］. 北京: 北京航空航天大学出版社,2007.
YAN C. Method and application of computational fluid dyna- mics ［M］. Beijing: Beihang University Press, 2007.(in Chinese)

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