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 ,
  • 史经纬 ,
  • 惠中豪 ,
  • 是介 ,
  • 周莉 ,
  • 王占学
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  • 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

  网络出版日期: 2026-04-20

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

  • LIN Wen-Tao ,
  • SHI Jing-Wei ,
  • HUI Zhong-Hao ,
  • SHI Jie ,
  • ZHOU Li ,
  • WANG Zhan-Xue
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Received date: 2025-12-01

  Revised date: 2026-04-14

  Online published: 2026-04-20

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%。

本文引用格式

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, 0 : 1 -0 . DOI: 10.7527/S1000-6893.2026.33169

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.

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