0°壁面角度约束下超声速射流偏转控制研究

周宇航; 顾蕴松; 李琳恺

doi:10.13224/j.cnki.jasp.20240659

0°壁面角度约束下超声速射流偏转控制研究

doi: 10.13224/j.cnki.jasp.20240659

南京航空航天大学航空学院非定常空气动力学与流动控制工信部重点实验室，南京 210016

基金项目: 国家自然基金面上项目（12472274）

详细信息

作者简介:
周宇航（1997-），男，博士，研究方向为流体推力矢量技术。E-mail：zhouyuhang@nuaa.edu.cn

通讯作者:
顾蕴松（1971-），男，教授，博士，研究方向为主动流动控制和新概念飞行器设计。E-mail：yunsonggu@nuaa.edu.cn

中图分类号: V231.3
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出版历程
- 收稿日期: 2024-09-25
- 网络出版日期: 2026-03-30

Research on deflection control of supersonic jet under the constraint of 0° wall angle

Laboratory of Unsteady Aerodynamics and Flow Control，Ministry of Industry and Information Technology，College of Aerospace Engineering，Nanjing University of Aeronautics and Astronautics，Nanjing 210016，China

摘要

摘要:
流体推力矢量喷管因其结构简单、质量轻、响应快以及隐身性好成为低可探测飞行器的关键部件之一。目前射流的矢量控制往往依赖于喷管扩张段或弯曲型面，而额外的型面结构势必会带来飞行器结构增重以及后体阻力，同时降低了飞行器的隐身性。因此本文立足于0°壁面角度约束下的被动式流体推力矢量喷管，通过实验研究方法探究了有限固壁约束下超声速射流在有无控制下的波系结构特征及演化规律。研究表明：在壁面角度为0°约束条件下，压比为2.0的主射流表现为多级马赫杆的类激波串波系结构，施加控制后可以实现3°的流动矢量角；当主流压比为2.5时，施加控制后射流边界的非对称膨胀导致射流在壁面发生非对称分离，最终驱动射流达到3.5°的矢量偏转角。研究结果有助于明晰壁面角度约束对超声速射流波系结构的影响规律，可为隐身飞翼布局飞行器提供矢量辅助增稳控制新方法。
- 流体式推力矢量 /
- 射流控制 /
- 诱导激波 /
- 分离激波 /
- 固壁约束
Abstract:
The fluidic thrust vectoring nozzle, with its simple structure, light weight, fast response, and good stealth, has become one of the key components for low detectable aircraft. The vectoring control of the jet is often dependent on the expansion section or curved surface of the nozzle, which inevitably leads to additional structural weight and drag on the aircraft, as well as a decrease in stealth. Therefore, this study focuses on the passive fluidic thrust vectoring nozzle with the angle of the surface equal to 0°, and explores the evolution laws of the wave structure under the confined solid wall constraint through experimental method. The study shows that under the constraint of the surface angle equal to 0°, the primary jet under nozzle pressure ratio 2.0 exhibits a multi Mach stem as shock wave string structure. When the jet is controlled, the jet can be deflected to 3°. When the nozzle pressure ratio is 2.5, the asymmetric expansion of the jet boundary appeared under controlled, which leads to the asymmetric separation of the jet on the upper and down walls. The jet can be achieved to 3.5° deflection angle. The research results help clarify the influence of the surface angle constraint on the wave structure of the supersonic jet and can provide a new method of vector assisted stabilization control for stealth wing layout aircraft.
- fluidic thrust vector /
- jet control /
- induced shock wave /
- separation shock wave /
- wall constraint

HTML

图 1 被动流体式推力矢量喷管模型示意图（单位：mm）

Figure 1. Schematic diagram of passive fluidic thrust vectoring nozzle model （unit：mm）

下载: 全尺寸图片幻灯片

图 2 0°壁面角度约束下流体推力矢量喷管实验台（纹影采集系统）

Figure 2. Fluidic thrust vectoring nozzle experimental platform under 0° wall constraints （schlieren visualization system）

下载: 全尺寸图片幻灯片

图 3 0°壁面角度约束下R_NPR=2.0无控制超声速射流流动结构

Figure 3. Flow structure of uncontrolled supersonic jet of 0° wall constraints under R_NPR=2.0

下载: 全尺寸图片幻灯片

图 4 0°壁角约束下R_NPR=2.5无控制超声速射流流动结构

Figure 4. Flow structure of uncontrolled supersonic jet of 0° wall constraints under R_NPR=2.5

下载: 全尺寸图片幻灯片

图 5 不同压比无控制情况下壁面压力分布

Figure 5. Pressure distribution of the wall with different R_NPR of uncontrolled station

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图 6 0°壁面角度约束下R_NPR=2.0控制下超声速射流流动结构

Figure 6. Flow structure of controlled supersonic jet of 0° wall constraints under R_NPR=2.0

下载: 全尺寸图片幻灯片

图 7 R_NPR=2.0控制情况下壁面压力分布

Figure 7. Pressure distribution of the wall with R_NPR=2.0 of controlled condition

下载: 全尺寸图片幻灯片

图 8 0°壁面角度约束下R_NPR=2.5控制超声速射流流动结构

Figure 8. Flow structure of controlled supersonic jet of 0° wall constraints under R_NPR=2.5

下载: 全尺寸图片幻灯片

图 9 R_NPR=2.5控制情况下壁面压力分布

Figure 9. Pressure distribution of the wall with R_NPR=2.5 of controlled condition

下载: 全尺寸图片幻灯片

表 1 喷管结构参数表

Table 1. Table of the nozzle structure parameter

参数数值

主喷流喷管高度H/mm 10

主喷流喷管宽度W/mm 40

控制缝h/mm 1.4

壁板长度L/mm 20

壁板倾角θ/（°） 0

下载: 导出CSV

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