超声速颌下乘波进气道一体化设计

推进技术 ›› 2018, Vol. 39 ›› Issue (8): 1720-1727.

超声速颌下乘波进气道一体化设计

孟宇鹏,高雄,朱守梅,李宏东

北京动力机械研究所高超声速冲压发动机技术重点实验室，北京 100074,北京动力机械研究所高超声速冲压发动机技术重点实验室，北京 100074,北京动力机械研究所高超声速冲压发动机技术重点实验室，北京 100074,北京动力机械研究所高超声速冲压发动机技术重点实验室，北京 100074

发布日期:2021-08-15

Integration Design of Supersonic Waverider Chin Inlet

Science and Technology on Scramjet Laboratory，Beijing Power Machinery Institute，Beijing 100074，China,Science and Technology on Scramjet Laboratory，Beijing Power Machinery Institute，Beijing 100074，China,Science and Technology on Scramjet Laboratory，Beijing Power Machinery Institute，Beijing 100074，China and Science and Technology on Scramjet Laboratory，Beijing Power Machinery Institute，Beijing 100074，China

Published:2021-08-15

摘要/Abstract

摘要： 为实现冲压发动机进气道/飞行器前体融合化设计，采用轴对称弯曲激波压缩基准流场和等熵压缩基准流场的锥导乘波设计方法，设计出工作范围Ma=2.5～4.5的超声速颌下乘波进气道方案，利用三维流场数值模拟获得了进气道基本性能，并对等熵压缩颌下乘波进气道进行了风洞吹风试验，验证了进气道的性能特性。研究结果表明:(1)设计的颌下进气道可以在Ma=2.5～4.5工作，在设计点Ma=4.0实现前体乘波，并具有大捕获流量、高压缩特性及高升阻比的优点；(2)进气道总压恢复系数和流量系数随着攻角增大而提高，在Ma=4.0，6°攻角状态，该进气道总压恢复系数可以达到0.47，流量系数达到1.20；(3)在更大攻角下由于捕获流量大幅增大，颌下进气道会出现不起动现象，但流场结构和性能稳定。

关键词: 冲压发动机；超声速进气道；计算流体动力学；风洞试验

Abstract: For ramjet inlet-forebody integration， on the basis flow field of axisymmetric curved shock compression and axisymmetric isentropic compression， an integration waverider design of supersonic chin inlet was presented.The chin inlet has a working range from Mach number 2.5 to 4.5. Inlet performance has gained by 3D CFD simulation， and wind tunnel test has developed on the isentropic-compression-waverider chin inlet. The results showed that:(1)The chin inlet can be worked from Mach 2.5 to 4.5， the forebody shock realized waverider on design Mach number 4.0.The principle advantages of waverider chin inlet are the higher compression efficiency and higher capture massflow ratio and higher lift-to-drag ratio. (2)The total pressure recovery and mass flow ratio of the chin inlet were rised with the increasing of incidence angle. The total pressure recovery reached 0.47 and massflow ratio reached 1.20 on condition of Mach number 4.0 at incidence angle 6°. (3)The chin inlet has unstarted at higher incidence angle because of increasing capture massflow， the flow field structure was still steady and performance was stable.

Key words: Ramjet；Supersonic inlet；Computation fluid dynamics；Wind tunnel test

孟宇鹏,高雄,朱守梅,李宏东. 超声速颌下乘波进气道一体化设计[J]. 推进技术, 2018, 39(8): 1720-1727.

MENG Yu-peng,GAO Xiong,ZHU Shou-mei,LI Hong-dong. Integration Design of Supersonic Waverider Chin Inlet[J]. Journal of Propulsion Technology, 2018, 39(8): 1720-1727.

参考文献

[1] 刘兴洲. 飞航导弹动力装置[M]. 北京:宇航出版社,1992.
[2] Eugene L Fleeman. Tactical Missile Design[M]. Virginia: American Institute of Aeronautics and Astronautics,2006.
[3] Frank F Webster, Bucy J A. ASALM-PTV Chin Inlet Technology Overview[R]. AIAA 79-1240.
[4] Frank F Webster. Evaluation of the ASALM-PTV Propulsion System Flight Data Correlation Results and Anylasis Techniques[R]. AIAA 81-1606.
[5] 王新月, 廉小纯. 超声速颌下式进气道/前机身一体化方案设计[J]. 推进技术, 2002, 23(2): 142-145. (WANG Xin-yue , LIAN Xiao-chun. Supersonic Chin Inlet/Airframe Integration Design[J]. Journal of Propulsion Technology, 2002, 23(2): 142-145.)
[6] 谢文忠, 郭荣伟. 4种布局形式下超声速飞行器进气道气动特性实验对比[J]. 南京航空航天大学学报, 2011, 43(1): 13-17.
[7] 靖建朋, 郭荣伟, 孙小平, 等. Ma4一级颌下式混压进气道试验[J]. 航空动力学报, 2012, 27(2): 387-394.
[8] 孟宇鹏, 朱守梅, 李宏东. 马赫数4.0颌下等熵混合压缩进气道技术研究[J]. 战术导弹技术, 2014, (6):69-74.
[9] 李宏东, 朱守梅, 朱璞, 等. 超声速颌下进气道亚临界振荡特性试验研究[J]. 推进技术, 2015, 36(11): 1601-1609. (LI Hong-dong, ZHU Shou-mei, ZHU Pu, et al. Experimental Investigation on Sub-Critical Oscillation Characteristics of Supersonic Chin Inlet[J]. Journal of Propulsion Technology, 2015, 36(11):1601-1609.)
[10] Haney J W, Beaulieu W D. Wave Rider Inlet, Integration Issues[R]. AIAA 94-0383.
[11] LobbiaM, Suzuki K. Design and Analysis of Payload Op timized Waveriders[R]. AIAA 2001-1849.
[12] Ryan P Starkey, Falcon Rankins, Darryll Pines. Coupled Waverider/Trajectory Optimization for Hypersonic Cruise[R]. AIAA 2005-530.
[13] Kashif H J, Varnavas C S. Airframe-Propulsion Integration Methodology for Waverider-Derived Hypersonic Cruise Aircraft Design Concepts[R]. AIAA 2004-1201.
[14] Sannu M. Internal Axismmetric Conical Flow[J]. AIAA Joural, 1967, 5(7): 1043-1047.
[15] Adam Siebenhaar, Thomas J Bogar. Integration and Vehicle Performance Assessment of the Aerojet “TriJet” Combined-Cycle Engine[R]. AIAA 2009-7420.
[16] 耿永兵, 刘宏, 丁海河, 等. 轴对称近似等熵压缩流场的乘波前体优化设计[J]. 推进技术, 2006, 27(5): 404-409. (GENG Yong-bing, LIU Hong, DING Hai-he, et al. Optimized Design of Waverider Forebody Derived from a Symmetric Near-Isentropic Compression Flow Fields[J]. Journal of Propulsion Technology, 2006, 27(5): 404-409.)
[17] 南向军, 张堃元. 压缩面升压规律可控的高超进气道轴对称基准流场设计方法研究[C]. 昆明:中国航空学会航空动力分会火箭发动机专业委员会2009 年推进技术学术年会, 2009.
[18] 许少华, 侯中喜, 葛爱学, 等. 锥导乘波构型设计、优化与分析 [J]. 推进技术, 2008, 29(4): 448-453. (XU Shao-hua, HOU Zhong-xi, GE Ai-xue, et al. Design, Optimization and Analysis of Cone Derived Waverider[J]. Journal of Propulsion Technology, 2008, 29(4):448-453.)
[19] 贺旭照, 秦思, 周正, 等. 一种乘波前体进气道的一体化设计及性能分析[J]. 航空动力学报, 2013, 28(6): 1270-1276.　　　　　　　　　　　　　*　收稿日期:2017-11-24；修订日期:2018-02-23。通讯作者:孟宇鹏,男,硕士,高级工程师,研究领域为发动机进气道。E-mail: xxshchwshry@sina.com