激波矢量S弯喷管红外辐射特性-流动控制与热管理专栏

doi:10.7527/S1000-6893.2026.33169

本期目录 | 过刊浏览 | 高级检索

前一篇 | 后一篇

激波矢量S弯喷管红外辐射特性-流动控制与热管理专栏

林文涛¹,史经纬²,惠中豪²,是介¹,周莉³,王占学¹

1. 西北工业大学
2. 西北工业大学，动力与能源学院
3. 西北工业大学动力与能源学院

收稿日期:2025-12-01 修回日期:2026-04-14 出版日期:2026-04-20 发布日期:2026-04-20
通讯作者: 史经纬
基金资助:
国家自然科学基金;国家科技重大专项

Infrared radiation characteristic of shock vectoring control serpentine nozzle

Received:2025-12-01 Revised:2026-04-14 Online:2026-04-20 Published:2026-04-20

摘要/Abstract

摘要： 激波矢量S弯喷管是支撑下一代战斗机实现高机动性与强隐身性的排气系统重要构型。为了获取激波矢量S弯喷管的红外辐射特性及产生机制，通过数值模拟方法计算了带辅助喷射通道的激波矢量S弯喷管后向红外辐射强度空间分布，结合流场特征分析了空间分布规律的形成机理，并对比了关闭辅助喷射/激波矢量时以及不同二次流压比下激波矢量S弯喷管的红外辐射特性。研究结果表明，总辐射中燃气辐射平均占比在水平探测面和垂直探测面上分别高达83.08%和76.95%，且基准工况下推力矢量角达到了19.24°，说明激波矢量S弯喷管能够在有效抑制壁面红外辐射的同时实现较好推力矢量效果；相比一般S弯喷管，激波矢量S弯喷管存在分离激波和尾喷流大幅偏转现象，二者分别通过诱导壁面热斑产生、改变燃气路径与尾喷流投影面积来影响喷管红外辐射特性，且辅助喷射与激波矢量均会导致红外隐身性能恶化；二次流压比通过影响分离激波角度和喷管出口压力来影响红外辐射特性，在二次流压比从1.0增大到1.4的过程中，分离激波与上壁面交汇区域扩大、出口压差增大，给喷管性能带来不利影响：推力系数降低1.22%，矢量角减小12.99%，燃气辐射在垂直探测面上除20°以外的各个角度平均增强了23.49%、在水平探测面上平均增强了18.38%。

关键词: 气动推力矢量, 激波矢量控制, S弯喷管, 红外辐射特性, 红外隐身, 二次流压比

Abstract: The shock vectoring control serpentine nozzle (SVCSN) is an important configuration of exhaust system that supports next-generation fighters in achieving high maneuverability and strong stealth capabilities. In order to investigate the infrared radiation characteristic and generation mechanism of SCVSN, numerical simulation was employed to calculate the spatial distribution of backward infrared radiation intensity of SVCSN with auxiliary injection channels. The formation mechanism of the spatial distribution pattern was analyzed by combining flow field characteristic, and the infrared radiation characteristics of SVCSN without auxiliary injection/shock vectoring and under different secondary flow pressure ratios (SPR) were compared. The results indicate that the average proportion of gas radiation in total radiation reaches as high as 83.08% and 76.95% on the horizontal plane and the vertical plane respectively. Additionally, the thrust vector angle reaches approximately 19.24° under the baseline condition, demonstrating that SVCSN can effectively suppress wall infrared radiation while achieving favorable thrust vectoring performance. Compared with the conventional serpentine nozzle, SVCSN exhibits the phenomena of separation shock and significant deflection of the plume. These two phenomena affect the infrared radiation characteristic of SVCSN by inducing the generation of wall hot spots and altering the gas path as well as the projected area of the plume, respectively. Moreover, both auxiliary injection and shock vectoring will degrade the infrared stealth performance. SPR influences the infrared radiation characteristic by altering the separation shock angle and the nozzle outlet pressure. As SPR increases from 1.0 to 1.4, the intersection area between the separation shock and the upper wall expands, and the outlet pressure difference increases, which exerts an adverse impact on the performance of SVCSN: the thrust coefficient decreases by 1.22%, the vector angle reduces by 12.99%, the gas radiation increases by an average of 23.49% on the vertical plane (excluding the 20° angle) and an average of 18.38% on the horizontal plane.

Key words: fluidic thrust vectoring, shock vector control, serpentine nozzle, infrared radiation characteristic, infrared stealth, secondary flow pressure ratio

中图分类号:

V231.1

林文涛史经纬惠中豪是介周莉王占学. 激波矢量S弯喷管红外辐射特性-流动控制与热管理专栏[J]. 航空学报, doi: 10.7527/S1000-6893.2026.33169.

参考文献

[1] Sekar T C, Kushari A, Mody B, et al. Fluidic thrust vectoring using transverse jet injection in a converging nozzle with aft-deck[J]. Experimental Thermal and Fluid Science, 2017, 86: 189–203. [2] Kong F S, Jin Y Z, Kim H D. Thrust vector control of supersonic nozzle flow using a moving plate[J]. J Mech Sci Technol, 2016, 30(3): 1209–1216. [3] Trancossi M, Madonia M, Dumas A, et al. A new aircraft architecture based on the ACHEON Coanda effect nozzle: Flight model and energy evaluation[J]. Eur Transp Res Rev, 2016, 8(2): 11. [4] 王海峰. 战斗机推力矢量关键技术及应用展望[J]. 航空学报, 2020, 41(6): 20–43. WANG H F. Key Technologies and application prospects of thrust vectoring for fighter jets[J]. Acta Aeronautica et Astronautica Sinica, 2020, 41(6): 20–43(in Chinese). [5] 徐惊雷, 黄帅, 潘睿丰, 等. 气动推力矢量喷管研究近况和发展趋势[J]. 航空学报, 2025, 46(8): 7–26. XU J L, HUANG S, PAN R F, et al. Recent research progress and development trends of aerodynamic thrust vectoring nozzles[J]. Acta Aeronautica et Astronautica Sinica, 2025, 46(8): 7–26(in Chinese). [6] Huang S, Xu J L, Yu K K, et al. Design and experimental study of a bypass dual throat nozzle with the ability of short/vertical takeoff and landing[J]. Aerospace Science and Technology, 2022, 121. [7] 王玉新. 喷气发动机轴对称推力矢量喷管[M]. 北京: 国防工业出版社, 2006. WANG Y X. Axisymmetric thrust vectoring nozzle for jet engines[M]. Beijing: National Defense Industry Press, 2006(in Chinese). [8] Huang S, Xu J L, Yu K K, et al. Numerical study of a trapezoidal bypass dual throat nozzle[J]. Chin J Aeronaut, 2023, 36(3): 42–62. [9] Xu B X, Hu D P, Feng L H. Dynamic characteristics and application of dual throat fluidic thrust vectoring nozzle[J]. Chin J Aeronaut, 2024, 37(9): 85–99. [10] Zhang Y Q, Xu J L, Cao M L, et al. Numerical investigation of dynamic characteristics of dual throat nozzle and bypass dual throat nozzle in thrust vectoring starting process[J]. Chin J Aeronaut, 2024, 37(10): 184–206. [11] 史经纬, 王占学, 梁爽. 激波矢量控制喷管技术分析[J]. 航空动力, 2023, (2): 71–74. SHI J W, WANG Z X, LIANG S. Technical analysis of shock vector control nozzle[J]. Aerospace Power, 2023, (2): 71–74(in Chinese). [12] 史经纬. 固定几何气动矢量喷管流动机理及性能评估技术研究[D]. 西安: 西北工业大学, 2015: 39–41. SHI J W. Research on flow mechanism and performance evaluation technology of fixed-geometry aerodynamic vectoring nozzle[D]. Xi'an: Northwestern Polytechnical University, 2015: 39–41(in Chinese). [13] 是介, 周莉, 史经纬, 等. 复杂来流条件下设计参数对S弯喷管红外辐射特征影响[J]. 航空学报, 2024, 45(17): 300–316. SHI J, ZHOU L, SHI J W, et al. Influence of design parameters on infrared radiation characteristics of serpentine nozzle under complex inflow conditions[J]. Acta Aeronautica et Astronautica Sinica, 2024, 45(17): 300–316(in Chinese). [14] 邓洪伟, 尚守堂, 金海, 等. 航空发动机隐身技术分析与论述[J]. 航空科学技术, 2017, 28(10): 1–7. DENG H W, SHANG S T, JIN H, et al. Analysis and discussion on stealth technology of aero-Engines[J]. Aeronautical Science and Technology, 2017, 28(10): 1–7(in Chinese). [15] 王海峰. 高性能战斗机与发动机协同设计中的关键技术[EB/OL]. 北京: 航空学报, 2024.(2024-01-17)[2024-01-20]. WANG H F. Key technologies in collaborative design of high-performance fighter jets and engines[EB/OL]. Beijing: Acta Aeronautica et Astronautica Sinica, 2024.(2024-01-17)[2024-01-20](in Chinese). [16] Zmijanovic V, Leger L, Lago V, et al. Experimental and numerical study of thrust-vectoring effects by transverse gas injection into a propulsive axisymmetric C-D nozzle: AIAA-2012-3874[R]. Reston: AIAA, 2012. [17] Zmijanovic V, Leger L, Depussay E, et al. Experimental-Numerical Parametric Investigation of a Rocket Nozzle Secondary Injection Thrust Vectoring[J]. Journal of Propulsion and Power, 2016, 32(1): 196–213. [18] Zmijanovic V, Lago V, Sellam M, et al. Thrust shock vector control of an axisymmetric conical supersonic nozzle via secondary transverse gas injection[J]. Shock Waves, 2014, 24(1): 97–111. [19] 史经纬, 王占学, 刘增文, 等. 二次流喷口形状对激波矢量控制喷管推力矢量特性影响[J]. 航空动力学报, 2013, 28(12): 2678–2684. SHI J W, WANG Z X, LIU Z W, et al. Influence of secondary flow nozzle shape on thrust vector characteristics of shock vector control nozzle[J]. Journal of Aerospace Power, 2013, 28(12): 2678–2684(in Chinese). [20] 史经纬, 王占学, 周莉, 等. 激波矢量喷管二次流喷口形态影响研究[J]. 工程热物理学报, 2014, 35(11): 2173–2177. SHI J W, WANG Z X, ZHOU L, et al. Research on influence of secondary flow nozzle morphology of shock vector control nozzle[J]. Journal of Engineering Thermophysics, 2014, 35(11): 2173–2177(in Chinese). [21] Johansson M, Dalenbring M. Calculation of IR signatures from airborne vehicles[C]//Modeling and Simulation for Military Applications. Bellingham: Society of Photo-Optical Instrumentation Engineers, 2006: 369–380. [22] Mahesh B. Nozzle Design for Reducing Infrared Signature[R]. Kharagpur: Cyient, 2017. [23] Rao A N, Boomadevi S, Kushari A, et al. IR signature studies of Serpentine nozzle with elliptic exit[C]//ICTACEM-2017. Kanpur: Indian Institute of Technology, 2017: 393–399. [24] Lee Y R, Lee J W, Shin C M, et al. Characteristics of flow field and IR of double serpentine nozzle plume for varying cross sectional areas and flight conditions in UCAV[J]. Journal of the Korean Society for Aeronautical & Space Sciences, 2021, 49(8): 689–698. [25] Shan Y, Zhou X, Tan X, et al. Parametric design method and performance analysis of double S-Shaped nozzles[J]. International Journal of Aerospace Engineering, 2019, 2019(1): 4694–4718. [26] 周孝明, 单勇, 宫禹, 等. 低可探测双S弯喷管红外辐射特征研究[J]. 重庆理工大学学报(自然科学), 2018, 32(12): 54–61. ZHOU X M, SHAN Y, GONG Y, et al. Research on infrared radiation characteristics of low-detectable double serpentine nozzle[J]. Journal of Chongqing University of Technology(Natural Science), 2018, 32(12): 54–61(in Chinese). [27] 桑学仪, 吉洪湖, 王丁. 长径比和偏径比对双S形二元喷管性能的影响[J]. 红外技术, 2019, 41(5): 443–449. SANG X Y, JI H H, WANG D. Influence of aspect ratio and offset diameter on performance of double serpentine 2-D nozzle[J]. Infrared Technology, 2019, 41(5): 443–449(in Chinese). [28] 王宇恒, 吉洪湖, 程稳, 等. 收扩喷管设计对双S形二元排气系统气动与红外特征的影响[J]. 红外与激光工程, 2021, 50(11): 95–104. WANG Y H, JI H H, CHENG W, et al. Influence of convergent-divergent nozzle design on aerodynamic and infrared characteristics of double serpentine 2-D exhaust system[J]. Infrared and Laser Engineering, 2021, 50(11): 95–104(in Chinese). [29] Cheng W, Wang Z, Zhou L, et al. Investigation of infrared signature of serpentine nozzle for turbofan[J]. Journal of Thermophysics and Heat Transfer, 2019, 33(1): 170–178. [30] 程稳, 周莉, 王占学, 等. 几何参数对S弯喷管红外辐射特性的影响[J]. 推进技术, 2018, 39(9): 1974–1985. CHENG W, ZHOU L, WANG Z X, et al. Influence of geometric parameters on infrared radiation characteristics of serpentine nozzle[J]. Journal of Propulsion Technology, 2018, 39(9): 1974–1985(in Chinese). [31] 程稳. S弯喷管红外辐射特性预测及优化设计方法[D]. 西安: 西北工业大学, 2019: 89–95. CHENG W. Prediction and optimization design method of infrared radiation characteristics of serpentine nozzle[D]. Xi'an: Northwestern Polytechnical University, 2019: 89–95(in Chinese). [32] Liang S, Shi J W, Wang Z X. Influence of aft deck on the flow characteristics of a serpentine shock vector control nozzle[J]. Transactions of Nanjing University of Aeronautics and Astronautics, 2023, 40(1): 13–24. [33] Hui Z H, Shi J W, Lin W T, et al. Experimental investigation and numerical analysis on high-efficiency shock vectoring control serpentine nozzles[J]. Chinese Journal of Aeronautics, 2024, 37(12): 296–324. [34] 孙啸林, 王占学, 周莉, 等. 基于多参数耦合的S弯隐身喷管设计方法研究[J]. 工程热物理学报, 2015, 36(11): 2371–2375. SUN X L, WANG Z X, ZHOU L, et al. Research on design method of serpentine stealth nozzle based on multi-parameter coupling[J]. Journal of Engineering Thermophysics, 2015, 36(11): 2371–2375(in Chinese). [35] 徐建宇, 周莉, 是介, 等. 多股流S弯喷管红外辐射特性研究[J]. 航空动力学报, 2025, 40(2): 68–78. XU J Y, ZHOU L, SHI J, et al. Research on infrared radiation characteristics of multi-jet serpentine nozzle[J]. Journal of Aerospace Power, 2025, 40(2): 68–78(in Chinese). [36] Manna P, Dharavath M, Sinha P K, et al. Optimization of a flight-worthy scramjet combustor through CFD[J]. Aerosp Sci Technol, 2013, 27(1): 138–146. [37] 是介, 周莉, 史经纬, 等. S弯喷管与飞机后机身一体化构型红外辐射特性研究[J]. 推进技术, 2024, 45(8): 85–98. SHI J, ZHOU L, SHI J W, et al. Research on infrared radiation characteristics of integrated configuration of serpentine nozzle and aircraft rear fuselage[J]. Journal of Propulsion Technology, 2024, 45(8): 85–98(in Chinese).

E-mail：hkxb@buaa.edu.cn

关于我们

期刊社服务

专业学科

封面文章

友情链接

主管单位：中国科学技术协会主办单位：中国航空学会北京航空航天大学

激波矢量S弯喷管红外辐射特性-流动控制与热管理专栏

Infrared radiation characteristic of shock vectoring control serpentine nozzle

PDF (PC)

可视化

摘要/Abstract

引用本文

使用本文

参考文献

相关文章 14

编辑推荐

Metrics

本文评价

[1]	徐惊雷, 黄帅, 潘睿丰, 张玉琪. 气动推力矢量喷管研究近况和发展趋势[J]. 航空学报, 2025, 46(8): 631216-631216.
[2]	陈玲玲, 张杨, 施永强, 杨青真. 气膜冷却矢量喷管冷却/气动/红外辐射特性[J]. 航空学报, 2025, 46(8): 631139-631139.
[3]	李程珂, 王革, 杨泽南, 李祎. 微孔注氦型固-气混合火箭发动机比冲增益机制[J]. 航空学报, 2025, 46(16): 131693-131693.
[4]	王承熙, 周莉, 孙啸林, 张晓博, 王占学. 基于神经网络的S弯喷管-涡扇发动机多维度仿真[J]. 航空学报, 2025, 46(15): 130791-130791.
[5]	孟钰博, 史经纬, 周莉, 张诣, 王占学. 异型喷口的多维偏转S弯喷管设计方法[J]. 航空学报, 2024, 45(8): 128930-128930.
[6]	是介, 周莉, 史经纬, 王占学. 复杂来流条件下设计参数对S弯喷管红外辐射特征影响[J]. 航空学报, 2024, 45(17): 530082-530082.
[7]	是介, 周莉, 史经纬, 王占学. S弯喷管正后向红外辐射特征快速预测模型[J]. 航空学报, 2024, 45(14): 129639-129639.
[8]	李秋琳, 周莉, 孙鹏, 史经纬, 王占学. 出口宽高比对S弯喷管流固耦合特性影响[J]. 航空学报, 2023, 44(14): 628204-628204.
[9]	李书, 王黎, 吴烁, 申东, 黄瑞, 王强. 面向飞/发一体化设计的高温尾喷口流场分析[J]. 航空学报, 2016, 37(1): 364-370.
[10]	韦第升;王小群;杜善义. 复合材料在红外隐身技术中的应用[J]. 航空学报, 2009, 30(12): 2462-2468.
[11]	韦第升;王小群;杜善义. 飞行器红外隐身效能工程评价方法[J]. 航空学报, 2008, 30(6): 1592-1597.
[12]	帅永;董士奎;谈和平. 数值模拟喷焰2.7微米红外辐射特性[J]. 航空学报, 2005, 26(4): 402-405.
[13]	杨宜禾;白长城. 飞行器的红外隐身问题[J]. 航空学报, 1988, 10(12): 549-554.
[14]	张考. 21世纪初军用飞行器战术技术要求的新内容——隐身能力[J]. 航空学报, 1987, 8(2): 1-10.