| Citation: | ZHOU Yuhang, GU Yunsong, LI Linkai. Research on the deflection control of supersonic jet under the constraint of 0° wall angle[J]. Journal of Aerospace Power, 2026, 41（6）：20240659 doi: 10.13224/j.cnki.jasp.20240659
|
Owing to its simple structure, light weight, fast response, and stealth performance, the fluidic thrust vectoring nozzle 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 focused on the passive fluidic thrust vectoring nozzle with the angle of the surface equal to 0°, and explored the evolution laws of the wave structure under a confined solid wall constraint through experimental method. The study showed that at a surface angle of 0° and a nozzle pressure ratio (NPR) of 2.0, the primary jet exhibited a shock wave string structure with multiple Mach stems. When the jet was controlled, the jet can be deflected to 3°. When the nozzle pressure ratio was 2.5, asymmetric expansion of the jet boundary appeared under controlled condition, which led to asymmetric separation of the jet on the upper and lower walls. The jet can be deflected by up to 3.5°. The research results can help to clarify the influence of the surface angle constraint on the wave structure of the supersonic jet, thus providing a new method of vector-assisted stabilization control for stealth wing layout aircraft.
| [1] |
BURSEY R, DICKINSON R. Flight test results of the F-15 SMTD thrust vectoring/thrust reversing exhaust nozzle: AIAA-1990-1906[R]. Reston, US: 26th Joint Propulsion Conference, 1990.
|
| [2] |
CLOUGH B. Short take-off and landing maneuver technology demonstrator (STOL/MTD) lessons learned-integrated flight/propulsion control (IFPC): AIAA 1990-3307 [R]. Reston, US: Aircraft Design, Systems and Operations Conference, 1990.
|
| [3] |
FRANCIS M S. Air vehicle management with integrated thrust-vector control[J]. AIAA Journal, 2018, 56(12): 4741-4751. doi: 10.2514/1.J056768
|
| [4] |
F-15 STOL and Maneuver Technology Demonstrator flight test progress report: AIAA-1990-1269 [R]. Reston, US: Orbital Debris Conference: Technical Issues andFuture Directions, 1990.
|
| [5] |
Fluidic thrust vectoring and throat control exhaust nozzle: AIAA-2002-4060[R]. Reston, US: Joint Propulsion Conference & Exhibit, 2002.
|
| [6] |
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. SHI Jingwei. Study on flow mechanism and performance evaluation technology of fixed geometry aerodynamic vector nozzle[D]. Xi’an: Northwestern Polytechnical University, 2015. (in Chinese
SHI Jingwei. Study on flow mechanism and performance evaluation technology of fixed geometry aerodynamic vector nozzle[D]. Xi’an: Northwestern Polytechnical University, 2015. (in Chinese)
|
| [7] |
王占学, 王玉男, 李志杰, 等. 基于激波控制的流体推力矢量喷管试验[J]. 推进技术, 2010, 31(6): 751-756. WANG Zhanxue, WANG Yunan, LI Zhijie, et al. Experiment on fluidic thrust-vectoring nozzle based on shock control concept[J]. Journal of Propulsion Technology, 2010, 31(6): 751-756. (in Chinese doi: 10.13675/j.cnki.tjjs.2010.06.003
WANG Zhanxue, WANG Yunan, LI Zhijie, et al. Experiment on fluidic thrust-vectoring nozzle based on shock control concept[J]. Journal of Propulsion Technology, 2010, 31(6): 751-756. (in Chinese) doi: 10.13675/j.cnki.tjjs.2010.06.003
|
| [8] |
MILLER D, CATT J. Conceptual development of fixed-geometry nozzles using fluidic injection for throat area control: AIAA-1995-2603[R]. Reston, US: 31st Joint Propulsion Conference and Exhibit, 1995.
|
| [9] |
WANG Yangsheng, XU Jinglei, HUANG Shuai, et al. Design and preliminary analysis of the variable axisymmetric divergent bypass dual throat nozzle[J]. Journal of Fluids Engineering, 2020, 142(6): 061204. doi: 10.1115/1.4045996
|
| [10] |
蒋晶晶, 徐惊雷, 黄帅, 等. 平行四边形截面的旁路式双喉道气动矢量喷管数值研究[J]. 航空动力学报, 2020, 35(4): 805-814. JIANG Jingjing, XU Jinglei, HUANG Shuai, et al. Numerical study of bypass dual throat nozzle with parallelogram cross-section[J]. Journal of Aerospace Power, 2020, 35(4): 805-814. (in Chinese doi: 10.13224/j.cnki.jasp.2020.04.014
JIANG Jingjing, XU Jinglei, HUANG Shuai, et al. Numerical study of bypass dual throat nozzle with parallelogram cross-section[J]. Journal of Aerospace Power, 2020, 35(4): 805-814. (in Chinese) doi: 10.13224/j.cnki.jasp.2020.04.014
|
| [11] |
STRYKOWSKI P, WILCOXON R. Self-excitation and mixing in axisymmetric jets with counterflow: AIAA 1992-538 [R]. Reston, US: 30th Aerospace Sciences Meeting and Exhibit, 1992.
|
| [12] |
DORES D, MADRUGA SANTOS M, KROTHAPALLI A, et al. Characterization of a counterflow thrust vectoring scheme on a gas turbine engine exhaust jet: AIAA-2006-3516 [R]. Reston, US: 3rd AIAA Flow Control Conference, 2006.
|
| [13] |
MASON M, CROWTHER W. Fluidic thrust vectoring for low observable air vehicles: AIAA-2004-2210 [R]. Reston, US: 2nd AIAA flow control conference, 2004.
|
| [14] |
王全, 王强. 激波诱导二元矢量喷管内流特性数值研究[J]. 航空动力学报, 2006, 21(4): 681-685. WANG Quan, WANG Qiang. Computational analysis on static internal flow field of shock vector controlled vectoring exhaust nozzles[J]. Journal of Aerospace Power, 2006, 21(4): 681-685. (in Chinese doi: 10.3969/j.issn.1000-8055.2006.04.012
WANG Quan, WANG Qiang. Computational analysis on static internal flow field of shock vector controlled vectoring exhaust nozzles[J]. Journal of Aerospace Power, 2006, 21(4): 681-685. (in Chinese) doi: 10.3969/j.issn.1000-8055.2006.04.012
|
| [15] |
吴盟, 额日其太. 激波控制量喷管流动与工作特性研究[J]. 燃气涡轮试验与研究, 2012, 25(1): 29-34, 8. WU Meng, Eriqitai. Research on structure and performance of shock wave control vector nozzle flow field[J]. Gas Turbine Experiment and Research, 2012, 25(1): 29-34, 8. (in Chinese doi: 10.3969/j.issn.1672-2620.2012.01.009
WU Meng, Eriqitai. Research on structure and performance of shock wave control vector nozzle flow field[J]. Gas Turbine Experiment and Research, 2012, 25(1): 29-34, 8. (in Chinese) doi: 10.3969/j.issn.1672-2620.2012.01.009
|
| [16] |
DEERE K. PAB3D simulations of a nozzle with fluidic injection for yaw thrust-vector control: AIAA 1998-3254 [R]. Reston, US: 34th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, 1998.
|
| [17] |
GU Rui, XU Jinglei, GUO Shuai. Experimental and numerical investigations of a bypass dual throat nozzle[J]. Journal of Engineering for Gas Turbines and Power, 2014, 136(8): 084501. doi: 10.1115/1.4026943
|
| [18] |
WANG Yangsheng, XU Jinglei, HUANG Shuai, et al. Experimental and numerical investigation of an axisymmetric divergent dual throat nozzle[J]. Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering, 2020, 234(3): 563-572. doi: 10.1177/0954410019872089
|
| [19] |
汪明生, 杨建军. 逆流矢量喷管流动自身导致的非定常现象[J]. 航空学报, 2009, 30(4): 630-636. WANG Mingsheng, YANG Jianjun. Flow-induced unsteady phenomena in counterflow vectoring nozzles[J]. Acta Aeronautica et Astronautica Sinica, 2009, 30(4): 630-636. (in Chinese doi: 10.3321/j.issn:1000-6893.2009.04.009
WANG Mingsheng, YANG Jianjun. Flow-induced unsteady phenomena in counterflow vectoring nozzles[J]. Acta Aeronautica et Astronautica Sinica, 2009, 30(4): 630-636. (in Chinese) doi: 10.3321/j.issn:1000-6893.2009.04.009
|
| [20] |
杨建军, 汪明生. 逆流推力矢量喷管基本流动特征的数值研究[J]. 航空学报, 2008, 29(4): 769-775. YANG Jianjun, WANG Mingsheng. Numerical research on basic flow characteristics of counterflow thrust vectoring nozzle[J]. Acta Aeronautica et Astronautica Sinica, 2008, 29(4): 769-775. (in Chinese doi: 10.3321/j.issn:1000-6893.2008.04.001
YANG Jianjun, WANG Mingsheng. Numerical research on basic flow characteristics of counterflow thrust vectoring nozzle[J]. Acta Aeronautica et Astronautica Sinica, 2008, 29(4): 769-775. (in Chinese) doi: 10.3321/j.issn:1000-6893.2008.04.001
|
| [21] |
CHIPPINDALL J M. Coflow fluidic thrust vectoring of supersonic jets with a fixed geometry convergent divergent nozzle[D]. Manchester, UK: University of Manchester, 2009.
|
| [22] |
BANAZADEH A, SAGHAFI F, GHOREYSHI M, et al. Experimental and computationalinvestigation into the use of co-flow fluidic thrustvectoring on a small gas turbine[J]. The Aeronautical Journal, 2008, 112(1127): 17-25. doi: 10.1017/S0001924000001950
|
| [23] |
肖中云, 顾蕴松, 江雄, 等. 一种基于引射效应的流体推力矢量新技术[J]. 航空学报, 2012, 33(11): 1967-1974. XIAO Zhongyun, GU Yunsong, JIANG Xiong, et al. A new fluidic thrust vectoring technique based on ejecting mixing effects[J]. Acta Aeronautica et Astronautica Sinica, 2012, 33(11): 1967-1974. (in Chinese
XIAO Zhongyun, GU Yunsong, JIANG Xiong, et al. A new fluidic thrust vectoring technique based on ejecting mixing effects[J]. Acta Aeronautica et Astronautica Sinica, 2012, 33(11): 1967-1974. (in Chinese)
|
| [24] |
曹永飞, 顾蕴松, 程克明, 等. 基于被动二次流的射流偏转比例控制[J]. 航空学报, 2015, 36(3): 757-763. CAO Yongfei, GU Yunsong, CHENG Keming, et al. Proportional control of jet deflection with passive secondary flow[J]. Acta Aeronautica et Astronautica Sinica, 2015, 36(3): 757-763. (in Chinese doi: 10.7527/S1000-6893.2014.0116
CAO Yongfei, GU Yunsong, CHENG Keming, et al. Proportional control of jet deflection with passive secondary flow[J]. Acta Aeronautica et Astronautica Sinica, 2015, 36(3): 757-763. (in Chinese) doi: 10.7527/S1000-6893.2014.0116
|
| [25] |
龚东升, 顾蕴松, 周宇航, 等. 基于微型涡喷发动机热喷流的无源流体推力矢量喷管的控制规律[J]. 航空学报, 2020, 41(10): 101-112. GONG Dongsheng, GU Yunsong, ZHOU Yuhang, et al. Control law of passive fluid thrust vector nozzle based on thermal jet of micro turbojet engine[J]. Acta Aeronautica et Astronautica Sinica, 2020, 41(10): 101-112. (in Chinese
GONG Dongsheng, GU Yunsong, ZHOU Yuhang, et al. Control law of passive fluid thrust vector nozzle based on thermal jet of micro turbojet engine[J]. Acta Aeronautica et Astronautica Sinica, 2020, 41(10): 101-112. (in Chinese)
|
| [26] |
SHI Nanxing, GU Yunsong, ZHOU Yuhang, et al. Experimental investigation on the transient process of jet deflection controlled by passive secondary flow[J]. Journal of Visualization, 2022, 25(5): 967-981. doi: 10.1007/s12650-022-00841-y
|
| [27] |
SHI Nanxing, GU Yunsong, ZHOU Yuhang, et al. Mechanism of hysteresis and uncontrolled deflection in jet vectoring control based on Coanda effect[J]. Physics of Fluids, 2022, 34(8): 084107. doi: 10.1063/5.0101994
|
| [28] |
ZHOU Yuhang, GU Yunsong, XUE Longsheng, et al. Research on the control of supersonic jet under different boundary conditions[J]. Journal of Visualization, 2024, 27(1): 19-32. doi: 10.1007/s12650-023-00948-w
|
DownLoad:
