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两型超声速进气道平飞减速时的稳定性

符小刚 李俊浩 杨柳

符小刚, 李俊浩, 杨柳. 两型超声速进气道平飞减速时的稳定性[J]. 航空动力学报, 2024, 39(1):20210393 doi: 10.13224/j.cnki.jasp.20210393
引用本文: 符小刚, 李俊浩, 杨柳. 两型超声速进气道平飞减速时的稳定性[J]. 航空动力学报, 2024, 39(1):20210393 doi: 10.13224/j.cnki.jasp.20210393
FU Xiaogang, LI Junhao, YANG Liu. Stability of two types of supersonic inlets during a level deceleration flight[J]. Journal of Aerospace Power, 2024, 39(1):20210393 doi: 10.13224/j.cnki.jasp.20210393
Citation: FU Xiaogang, LI Junhao, YANG Liu. Stability of two types of supersonic inlets during a level deceleration flight[J]. Journal of Aerospace Power, 2024, 39(1):20210393 doi: 10.13224/j.cnki.jasp.20210393

两型超声速进气道平飞减速时的稳定性

doi: 10.13224/j.cnki.jasp.20210393
详细信息
    作者简介:

    符小刚(1983-),男,高级工程师,硕士,主要从事航空器进气道与发动机相容性飞行试验技术研究

  • 中图分类号: V217.1

Stability of two types of supersonic inlets during a level deceleration flight

  • 摘要:

    通过飞行试验,研究了一种二元斜板式及蚌式超声速进气道在马赫数1.5快收发动机油门平飞减速至马赫数为1.05过程中的畸变及稳定性水平。对比表明:减速过程中二元进气道总压畸变、稳定性裕度均随发动机换算转速的下降减小后保持稳定,而蚌式进气道畸变先上升再下降后保持稳定,稳定性裕度先下降再略微上升后保持稳定。减速过程前半段,蚌式进气道畸变更大,二元进气道稳定性裕度下降更快;减速过程后半段,两型进气道畸变水平接近,稳定性裕度均较低。分析也表明,仅使用流量系数的相对差值计算的进气道稳定裕度反映的进气道流通能力信息比使用总压恢复系数与流量系数之比的相对差值更全面,推荐采用前者作为进气道稳定性裕度评价指标。

     

  • 图 1  典型采用二元斜板可调式超声速进气道飞机(Su-35)及其进气道结构

    Figure 1.  Typical plane equipped with 2-D ramp adjustable supersonic inlet (Su-35) and structure of the inlet

    图 2  典型采用蚌式进气道飞机(F-35)及其进气道被动式流量调节

    Figure 2.  Typical plane equipped with bump inlet (F-35) and passive flow adjustment of the inlet

    图 3  进气道出口截面稳态及动态压力测点示意图

    Figure 3.  Sketch map of the steady and dynamic pressure measure point on exit section of the inlet

    图 4  两型进气道不同高度下超声速平飞减速时的出口截面总压畸变

    Figure 4.  Total pressure distortion of exit section of the two types of inlet during a supersonic level decelerate flight at different altitude

    图 5  平飞减速经过Ma=1.4,稳态及动态压力传感器测到的蚌式进气道出口压力值(Hp=H1

    Figure 5.  Level deceleration flying across Ma=1.4,pressure value measured with steady and dynamic pressure transducer at exit section of the bump inlet (Hp=H1

    图 6  平飞减速过程中两种进气道稳定性裕度的对比

    Figure 6.  Comparison of stability margins of the two types of inlet during a level decelerate flight

  • [1] 符小刚,李俊浩,许艳芝. 带辅助进气的二元超声速进气道低速特性[J]. 实验流体力学,2020,34(5): 36-43.

    FU Xiaogang,LI Junhao,XU Yanzhi. Characteristic of 2-D supersonic inlet with auxiliary intake at low flight speed[J]. Journal of Experiments in Fluid Mechanics,2020,34(5): 36-43. (in Chinese)
    [2] MIKI H, KAMEDA M, WATANABE Y. Low drag design and aerodynamic performance evaluation of supersonic air inlet[R]. AIAA-2014-3798, 2014.
    [3] DENNER B W, MCCALLUM B, TRUAX P. CFD prediction of inlet spill drag increments[R]. AIAA 98-3566, 1998.
    [4] CHUN K S,BURR R H. A control system concept for an axisymmetric supersonic inlet[J]. Journal of Aircraft,1969,6(4): 306-311. doi: 10.2514/3.44056
    [5] 于海涛,徐伟,臧旭. 大M数飞行时进气道爆音(喘振)的机理分析与规避措施[J]. 测控技术,2018,37(B09): 269-271, 276.

    YU Haitao,XU Wei,ZANG Xu. Working principle and evasive measures of inlet surge in the high ma flight[J]. Measurement & Control Technology,2018,37(B09): 269-271, 276. (in Chinese)
    [6] SORENSEN N E,SMELTZER D B,CUBBISON R W. Study of a family of supersonic inlet systems[J]. Journal of Aircraft,1969,6(3): 184-188. doi: 10.2514/3.44033
    [7] 饶彩燕,谭慧俊,张启帆. 超额定状态下二元超声速进气道的流动特性[J]. 航空动力学报,2017,32(5): 1160-1167.

    RAO Caiyan,TAN Huijun,ZHANG Qifan. Flow characteristics of a rectangular supersonic inlet under over-speed state[J]. Journal of Aerospace Power,2017,32(5): 1160-1167. (in Chinese)
    [8] 丁晨,刘猛,张继华,等. 变马赫数条件下进气道边界层吹除法数值模拟[J]. 推进技术,2013,34(10): 1310-1315.

    DING Chen,LIU Meng,ZHANG Jihua,et al. Numerical simulation on blowing method for controlling boundary layer interaction in supersonic inlet at different Mach number[J]. Journal of Propulsion Technology,2013,34(10): 1310-1315. (in Chinese)
    [9] 杜瑶,张海波. 超声速进气道正激波位置动态辨识与控制方法研究[J]. 推进技术,2018,39(4): 888-897.

    DU Yao,ZHANG Haibo. Research on dynamic identification and control method of normal shock position of supersonic inlet[J]. Journal of Propulsion Technology,2018,39(4): 888-897. (in Chinese)
    [10] 赵昊,谢旅荣,郭荣伟,等. 超声速进气道加速/减速过程起动/不起动现象研究[J]. 航空动力学报,2015,30(8): 1841-1852.

    ZHAO Hao,XIE Lürong,GUO Rongwei,et al. Study of start/unstart phenomenon of supersonic inlet in acceleration/deceleration process[J]. Journal of Aerospace Power,2015,30(8): 1841-1852. (in Chinese)
    [11] 寿圣德. 一种快速评定进气道/发动机稳态匹配工作点及稳定裕度的方法[J]. 航空学报,1987,8(10): 549-552.

    SHOU Shengde. A method for fast estimation of steady inlet/engine matching state and stability margin[J]. Acta Aeronautica et Astronautica Sinica,1987,8(10): 549-552. (in Chinese)
    [12] 赵海刚,屈霁云,史建邦,等. 高机动飞行下进气道/发动机相容性试验[J]. 航空动力学报,2010,25(9): 2077-2082.

    ZHAO Haigang,QU Jiyun,SHI Jianbang,et al. Filghtting test of inlet/engine compatibility during rapidly changing aircraft maneuvers[J]. Journal of Aerospace Power,2010,25(9): 2077-2082. (in Chinese)
    [13] 王玉峰,杨宝娥. 超声速进气道喘振的机理研究[J]. 火箭推进,2008,34(1): 17-22.

    WANG Yufeng,YANG Baoe. Study of the buzz mechanism of supersonic inlets[J]. Journal of Rocket Propulsion,2008,34(1): 17-22. (in Chinese)
    [14] 张堃元,MEIER G E A. 二元进气道非均匀超音来流试验研究[J]. 推进技术,1993,14(1): 9-15.

    ZHANG Kunyuan,MEIER G E A. Experimental investigation of 2-D inlet model in non-uniform supersonic flow[J]. Journal of Propulsion Technology,1993,14(1): 9-15. (in Chinese)
    [15] 杨应凯. 枭龙飞机Bump进气道设计[J]. 南京航空航天大学学报,2007,39(4): 449-452. doi: 10.3969/j.issn.1005-2615.2007.04.007

    YANG Yingkai. Design of bump inlet of thunder/JF-17 aircraft[J]. Journal of Nanjing University of Aeronautics & Astronautics,2007,39(4): 449-452. (in Chinese) doi: 10.3969/j.issn.1005-2615.2007.04.007
    [16] 张堃元,余少志,彭成一. 滑流层对轴对称外压式进气道稳定性的影响[J]. 航空学报,1983,4(3): 56-62.

    ZHANG Kunyuan,YU Shaozhi,PENG Chengyi. Effect of a shear layer on stability of an axisymmetric external compression air intake[J]. Acta Aeronautica et Astronautica Sinica,1983,4(3): 56-62. (in Chinese)
    [17] 王伟,田丰光. 进气道喘振诱发因素及其可靠性分析[J]. 沈阳航空工业学院学报,2004,21(4): 12-14.

    WANG Wei,TIAN Fengguang. Inducing factors and its reliability analysis of the air inlet surge[J]. Journal of Shenyang Institute of Aeronautcal Engineering,2004,21(4): 12-14. (in Chinese)
    [18] 廉筱纯, 吴虎. 航空发动机原理[M]. 西安: 西北工业大学出版社, 2005.
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出版历程
  • 收稿日期:  2021-07-25
  • 网络出版日期:  2023-10-16

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