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在非设计点，传统的高超声速进气道通常会出现性能下降甚至不起动的现象，这使得吸气式高超声速飞行器难以实现宽速域飞行。可调进气道能较好地解决这一问题，其可满足飞行器在不同速域下的进气需求，从而实现高超声速飞行器的宽速域推阻平衡。详细介绍了宽速域高超声速可调进气道的研究现状，系统梳理了各类典型的定几何调节方式和变几何调节方式，深入剖析了各调节方式的原理和优劣，总结了宽速域高超声速可调进气道研究中存在的重难点问题，为后续开展宽速域进气道的设计提供有益借鉴与启示。
Abstract：At off-design points, traditional hypersonic inlets often experience performance degradation or even failure to start, which poses a challenge for air-breathing hypersonic vehicles to achieve wide-speedrange flight. Adjustable inlets can effectively address this issue by meeting the air-breathing requirements of vehicles across different speed ranges, thereby achieving thrust-drag balance for hypersonic vehicles in a wide speed range. A detailed overview of the current research status of wide-speed-range adjustable hypersonic inlets is provided, systematically categorizes various typical fixed-geometry adjustment methods and variablegeometry adjustment methods are systematically categorized, the principles, advantages, and disadvantages of each adjustment method are deeply analyzed, and the key challenges and difficulties in the research of widespeed-range adjustable hypersonic inlets are summarized. The aim is to offer valuable insights and inspiration for subsequent design efforts in wide-speed-range inlets.
[1]罗世彬.高超声速飞行器机体/发动机一体化设计[M].北京：科学出版社，2018.
[2]王鹏飞，王洁，白炎，等.高超声速进气道技术研究现状综述[J].飞航导弹，2014(10):23-28.
[3]孟宇鹏，杨晖，满延进.高超声速进气道飞行器一体化设计技术的发展[J].气体物理，2021,6(4):66-83.
[4]Huang H,Tan H,Li F,et al.A review of the shockdominated flow in a hypersonic inlet/isolator[J].Progress in Aerospace Sciences,2023:100952.
[5]Zuo F Y,M?lder S.Hypersonic wavecatcher intakes and variable-geometry turbine based combined cycle engines[J].Progress in Aerospace Sciences,2019,106:108-144.
[6]赵健.超声速边界层抽吸孔隙流场结构研究[D].长沙：国防科学技术大学，2016.
[7]黄伟，吴瀚，钟翔宇，等.激波/湍流边界层干扰中的自适应控制技术[J].国防科技大学学报，2024,46(2):49-61.
[8]Qin Y,Huang H,Li F,et al.Experiment of an auxiliary restart method for hypersonic inlet with variable-bleed system[J].AIAA Journal,2023,61(8):3713-3719.
[9]Hamed A,Shih S,Yeuan J.A parametric study of bleed in shock boundary layer interactions[C].31st Aerospace Sciences Meeting,Reno,NV,USA,1993-11-01.
[10]Anders S,Sellers III W,Washburn A.Active flow control activities at NASA Langley[C].2nd AIAA Flow Control Conference,Portland,Oregon,USA,2004-06-28.
[11]陈卫明.二元高超声速进气道自起动特性的影响因素分析[D].南京：南京航空航天大学，2013.
[12]刘媛.宽范围定几何高超声速进气道自适应泄压控制技术研究[D].南京：南京航空航天大学，2012.
[13]金志光，张堃元，刘媛.一种定几何高超声速进气道自适应泄压控制概念与试验验证[J].空气动力学学报，2014,32(4):475-480.
[14]丁晨，刘猛，张继华，等.变马赫数条件下进气道边界层吹除法数值模拟[J].推进技术，2013,34(10):1310-1315.
[15]Bur R,Corbel B.Experimental study of transonic interaction with shock and boundary-layer control[C].Fluids2000 Conference and Exhibit,Denver,CO,USA,2000-06-19.
[16]Tindell R,Willis B,Tindell R,et al.Experimental investigation of blowing for controlling oblique shock/boundary layer interactions[C].33rd Joint Propulsion Conference and Exhibit,Seattle,WA,USA,1997-07-06.
[17]White M E,Lee R E,Thompson M W,et al.Tangential mass addition for shock/boundary-layer interaction control in scramjet inlets[J].Journal of Propulsion and Power,1991,7(6):1023-1029.
[18]孙润鹏，朱卫兵，黄舜，等.吹除法对斜激波/边界层干扰控制数值模拟[J].哈尔滨工程大学学报，2012,33(2):166-173.
[19]Haws R G,Noall J S,Daines R L.Computational investigation of a method to compress air fluidically in supersonic inlets[J].Journal of Spacecraft and Rockets,2001,38(1):51-59.
[20]谭慧俊，陈智，李光胜.基于激波形状控制的定几何高超声速可调进气道概念及初步验证[J].中国科学E辑，2007,37(11):1469-1479.
[21]罗金玲，李超，徐锦.高超声速飞行器机体/推进一体化设计的启示[J].航空学报，2015,36(1):39-48.
[22]赵慧勇，周瑜，倪鸿礼，等.高超声速进气道边界层强制转捩试验[J].实验流体力学，2012,26(1):1-6.
[23]王卫星，郭荣伟.基于边界层转捩的高超声速进气道特性研究[J].航空学报，2012,33(10):1772-1780.
[24]张红军，朱志斌，尚庆，等.锯齿形转捩片触发高超声速进气道边界层转捩的大涡模拟[J].航空学报，2019,40(10):94-104.
[25]郝志鹏.高超音速边界层转捩的数值模拟[D].哈尔滨：哈尔滨工业大学，2010.
[26]陈逖.高超声速进气道内激波/边界层干扰及射流式涡流发生器的流动控制方法研究[D].长沙：国防科学技术大学，2012.
[27]Berry S A,Auslender A H,Dilley A D,et al.Hypersonic boundary-layer trip development for Hyper-X[J].Journal of Spacecraft and Rockets,2001,38(6):853-864.
[28]Borg M P,Schneider S P.Effect of freestream noise on roughness-induced transition for the X-51A forebody[J].Journal of Spacecraft and Rockets,2008,45(6):1106-1116.
[29]Berry S A,Horvath T J.Discrete-roughness transition for hypersonic flight vehicles[J].Journal of Spacecraft and Rockets,2008,45(2):216-227.
[30]Johnston J,Nishi M.Vortex generator jets-a means for passive and active control of boundary layer separation[C].27th Aerospace Sciences Meeting,Reno,NV,USA,1989-01-09.
[31]Lin J,Howard F,Selby G.Exploratory study of vortexgenerating devices for turbulent flow separation control[C].29th Aerospace Sciences Meeting,Reno,NV,USA,1991-01-07.
[32]Berry S A,Di Fulvio M,Kowalkowski M K.Forced boundary-layer transition on X-43(Hyper-X) in NASALa RC 31-inch Mach 10 air tunnel[R].NASA/TM-2000-210315,2000.
[33]Berry S,Daryabeigi K,Wurster K,et al.Boundarylayer transition on X-43A[J].Journal of Spacecraft and Rockets,2010,47(6):922-934.
[34]李益文，王宇天，庞垒，等.进气道等离子体/磁流体流动控制研究进展[J].力学学报，2019,51(2):311-321.
[35]吴云，李应红.等离子体流动控制研究进展与展望[J].航空学报，2015,36(2):381-405.
[36]Falempin F,Firsov A A,Yarantsev D A,et al.Plasma control of shock wave configuration in off-design mode of M=2 inlet[J].Experiments in Fluids,2015,56:1-10.
[37]Leonov S B,Yarantsev D A.Near-surface electrical discharge in supersonic airflow:properties and flow control[J].Journal of Propulsion and Power,2008,24(6):1168-1181.
[38]Falempin F,Firsov A,Goldfeld M,et al.Plasma effect on shocks configuration in compression ramp[J].AIAA Paper,2011:2362.
[39]王子运，于航，张悦，等.空天飞行器可调进气系统关键问题研究进展[J].航空学报，2024,45(11):21-57.
[40]罗世彬，孙雨航，刘俊，等.高超声速乘波前体/进气道一体化设计综述[J].空天技术，2022(6):24-48.
[41]罗仕超，柳军，胡守超，等.高超声速进气道自起动特性磁流体动力学控制机理[J].中国科学：物理学力学天文学，2024,54(3):138-149.
[42]Fraishtadt V L,Kuranov A L,Sheikin E G.Use of MHD systems in hypersonic aircraft[J].Technical Physics,1998,43(11):1309-1313.
[43]Sheikin E,Kuranov A.MHD control in hypersonic aircraft[C].43rd AIAA Aerospace Sciences Meeting and Exhibit,Reno,NV,USA,2005-01-10.
[44]王殿恺，洪延姬，李倩.激光能量主动控制高超声速进气道研究现状[J].激光杂志，2012,33(5):1-2.
[45]李倩，赵伟，王殿恺，等.脉冲激光控制高超声速进气道来流捕获[J].强激光与粒子束，2015,27(8):289-294.
[46]李晶，洪延姬，王殿恺.激光能量注入位置对进气道马赫反射影响数值研究[J].激光杂志，2012,33(4):17-19.
[47]Shneyder M,Macheret S,Zaidi S,et al.Steady and unsteady supersonic flow control with energy addition[C].34th AIAA Plasma dynamics and Lasers Conference,Orlando,Florida,USA,2003-06-23.
[48]Macheret S O,Shneider M N,Miles R B.Scramjet inlet control by off-body energy addition:A virtual cowl[J].AIAA journal,2004,42(11):2294-2302.
[49]宁啸天，辜天来，田亚洲，等.一种轴对称变几何进气道气动设计及性能分析[J].固体火箭技术，2021,44(6):783-792.
[50]李永洲，马元，张堃元.二元曲面可调进气道流量系数精确预测方法[J].航空动力学报，2019,34(7):1409-1415.
[51]阳未.与飞行器前体一体化的可调进气道研究[D].南京：南京航空航天大学，2020.
[52]蒲永彬.一体化二元变几何进气道设计及气动性能研究[D].南京：南京航空航天大学，2018.
[53]齐海涛，刘旭，刘咄，等.飞行器二元变几何进气道调节机构多目标优化设计[J/OL].航空动力学报，1-15.[2025-01-10].https：//doi.org/10.13224/j.cnki.jasp.20230118.
[54]Taguchi H,Futamura H,Shimodaira K,et al.Design study on hypersonic engine components for TBCC space planes[C].12th AIAA International Space Planes and Hypersonic Systems and Technologies,Norfolk,Virginia,USA,2003-12-05.
[55]潘鹏宇.二元变几何TBCC进气道气动性能研究及风洞试验[D].南京：南京航空航天大学，2020.
[56]Scherrer R,Gowen F E.Preliminary experimental investigation of a variable-area,variable-internal-contraction air inlet at Mach numbers between 1.42 and 2.44[R].NACA RM A55F23,1955.
[57]Scherrer R,Anderson W E.Investigation of the performance and internal flow of a variable-area,variable-internal-contraction inlet at Mach numbers of 2.00,2.50,and 2.92[R].NACA RM A58C24,1958.
[58]黄庆平.Ma0-2几何可调进气道特性分析及数学建模[D].哈尔滨：哈尔滨工业大学，2020.
[59]赵昊，谢旅荣，郭荣伟，等.一种宽马赫数变几何超声速进气道气动性能研究[J].航空动力学报，2015,30(07):1678-1684.
[60]Huang H H,Huang G,Zuo F Y,et al.Research on a novel internal waverider TBCC inlet for ramjet mode[C].52nd AIAA/SAE/ASEE Joint Propulsion Conference,Salt Lake City,UT,USA,2016-07-25.
[61]Colville J,Lewis M.An aerodynamic redesign of the SR-71 inlet with applications to turbine based combined cycle engines[C].40th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit,Fort Lauderdale,Florida,USA,2004-07-11.
[62]Colville J,Starkey R,Lewis M.Extending the flight Mach number of the SR-71 inlet[C].AIAA/CIRA 13th International Space Planes and Hypersonics Systems and Technologies Conference,Capua,Italy,2005-05-16.
[63]李程鸿.一类流体式高超声速可调进气道的气动原理及验证研究[D].南京：南京航空航天大学，2015.
[64]Kojima T,Tanatsugu N,Sato T,et al.Development study on axisymmetric air inlet for ATREX engine[C].10th AIAA/NAL-NASDA-ISAS International Space Planes and Hypersonic Systems and Technologies Conference,Kyoto,Japan,2001-04-24.
[65]李建.高超声速轴对称进气道变几何方案研究[D].南京：南京航空航天大学，2012.
[66]Conners J F,Meyer R C.A variable-geometry axisymmetric supersonic inlet with telescoping centerbody[R].NACA RM E55F30,1955.
[67]Saunders J D,Linne A A.Status of the variable diameter centerbody inlet program[C].NASA,First Annual HighSpeed Research Workshop,Cleveland,Ohio,USA,1991-05-14.
[68]王肖.一种二元超声速变几何进气道研究[D].南京：南京航空航天大学，2019.
[69]郭程伟.宽范围轴对称变几何进气道设计方法与调节规律研究[D].南京：南京航空航天大学，2014.
[70]Weir L,Sanders B,Vachon J.A new design concept for supersonic axisymmetric inlets[C].38th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit,Indianapolis,Indiana,USA,2002-07-07.
[71]Maru Y,Tanatsugu N,Sato T,et al.Multi-row disk arrangement concept for spike of axisymmetric air inlet[C].40th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit,Fort Lauderdale,Florida,USA,2004-07-11.
[72]Kobayashi H,Tanatsugu N,Sato T,et al.Experimental study of multi-row disk inlets for hypersonic air breathing propulsion[C].42nd AIAA Aerospace Sciences Meeting and Exhibit,Reno,NV,USA,2004-01-05.
[73]王翼，范晓樯，梁剑寒，等.开启式高超声速进气道启动性能试验[J].航空动力学报，2008,23(6):1014-1018.
[74]陈秋华.喉道顶板可调侧压式进气道初步研究[D].南京：南京航空航天大学，2006.
[75]Hohn O,Gülhan A.Experimental investigation on the influence of sidewall compression on the flowfield of a scramjet inlet at Mach 7[C].17th AIAA International Space Planes and Hypersonic Systems and Technologies Conference,San Francisco,California,USA,2011-04-11.
[76]杨顺凯，张堃元，王磊.高超可调进气道弹性压缩面自适应无源控制概念研究[J].推进技术，2015,36(11):1633-1639.
[77]杨顺凯，张堃元，王磊，等.流量系数可控弹性自适应高超进气道研究[J].推进技术，2014,35(12):1592-1597.
[78]杨顺凯，张堃元，王磊，等.多点集中力下高超进气道弹性变几何研究[J].航空动力学报，2015,30(10):2516-2522.
[79]甘宁钢.宽马赫数凹曲激波压缩进气道型面变几何研究[D].南京：南京航空航天大学，2012.
[80]Zhang Y,Tan H J,Li J F,et al.Ramp shock regulation of supersonic inlet with shape memory alloy plate[J].AIAA Journal,2018,56(4):1696-1702.
[81]谭慧俊，王子运，张悦.形状记忆合金在飞行器进气道中的应用研究进展[J].南京航空航天大学学报，2019,51(4):438-448.
[82]渠磊，闫泽红，饶智祥，等.形状记忆合金在航空航天领域的应用研究综述[J].航空动力学报，2022,37(10):2127-2141.
[83]Falempin F,Wendling E,Goldfeld M,et al.Experimental investigation of starting process for a variable geometry air inlet operating from Mach 2 to Mach 8[C].42nd AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit,Sacramento,California,USA,2006-07-09.
[84]Francois F,Laurent S.French flight testing program LEA status in 2009[C].16th AIAA/DLR/DGLR International Space Planes and Hypersonic Systems and Technologies Conference,Bremen,Germany,2009-10-19.
[85]唐晗，高振勋.高马赫数变几何进气道发展现状[J].飞航导弹，2016(11):82-92.
[86]Steelant J,Varvill R,Walton C,et al.Achievements obtained for sustained hypersonic flight within the LAP-CAT-II project[C].20th AIAA international space planes and hypersonic systems and technologies conference,Glasgow,Scotland,UK,2015-07-06.
[87]潘瑾，张堃元.移动唇口变收缩比侧压式进气道反压特性和自起动性能[J].航空动力学报，2009,24(1):104-109.
[88]Jacobsen L,Tam C J,Behdadnia R,et al.Starting and operation of a streamline-traced Busemann inlet at Mach 4[C].42nd AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit,Sacramento,California,USA,2006-07-09.
[89]Lawrence D H,Kenneth E R,Edward G R,et al.Hyper-X flight engine ground testing for X-43 flight risk reduction[J].Journal of Spacecraft and Rockets,2001,38(6):844-852.
[90]Serre L,Falempin F.Promethee:the French military hypersonic propulsion program[C].12th AIAA International Space Planes and Hypersonic Systems and Technologies,Norfolk,Virginia,USA,2003-12-15.
[91]金志光，张堃元.高超侧压式进气道简单唇口调节方案设计[J].推进技术，2008,29(1):43-48.
[92]马涛.宽域内收缩进气道一体化设计的关键技术研究[D].南京：南京航空航天大学，2019.
[93]Sanders B W,Weir L J.Aerodynamic design of a dualflow Mach 7 hypersonic inlet system for a turbine-based combined-cycle hypersonic propulsion system[R].NASA/CR-2008-215214,2008.
[94]Walker S,Tang M,Morris S,et al.Falcon HTV-3X-a reusable hypersonic test bed[C].15th AIAA International Space Planes and Hypersonic Systems and Technologies Conference,Dayto,Ohio,USA,2008-04-28.
[95]左逢源，黄国平，陈杰，等.基于内乘波概念的TBCC进气道过渡模态研究[J].工程热物理学报，2015,36(2):274-278.
[96]Bulman M,Siebenhaar A.Combined cycle propulsion:aerojet innovations for practical hypersonic vehicles[C].17th AIAA international space planes and hypersonic systems and technologies conference,San Francisco,California,USA,2011-04-11.
[97]Siebenhaar A,Bogar T.Integration and vehicle performance assessment of the aerojet"trijet"combined-cycle engine[C].16th AIAA/DLR/DGLR International Space Planes and Hypersonic Systems and Technologies Conference,Bremen,Germany,2009-10-19.
[98]陈兵，谷良贤，龚春林.加速型高超飞行器变几何进气道设计分析[J].固体火箭技术，2013,36(4):431-436.
[99]Varvill R,Bond A.A comparison of propulsion concepts for SSTO reusable launchers[J].Journal of the British Interplanetary Society,2003,56:108-117.
[100]Varvill R,Bond A.The skylon spaceplane[J].Journal of the British Interplanetary Society,2004,57:22-32.
[101]袁化成，刘君，郭荣伟.变来流马赫数条件下组合动力可调进气道流动特性初步研究[J].气动研究与试验，2024,2(3):60-68.
基本信息:
DOI：10.16338/j.issn.2097-0714.20240108
中图分类号:V211.48
引用信息:
[1]罗世彬,郑盛贤,刘俊,等.宽速域高超声速可调进气道研究进展[J].空天技术,2025,No.463(01):1-19.DOI:10.16338/j.issn.2097-0714.20240108.