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高超声速大动压下整流罩分离测力风洞试验

钟俊 林敬周 解福田 赵健

钟俊,林敬周,解福田,等. 高超声速大动压下整流罩分离测力风洞试验[J]. 实验流体力学,2022,36(X):1-9 doi: 10.11729/syltlx20210194
引用本文: 钟俊,林敬周,解福田,等. 高超声速大动压下整流罩分离测力风洞试验[J]. 实验流体力学,2022,36(X):1-9 doi: 10.11729/syltlx20210194
ZHONG J,LIN J Z,XIE F T,et al. Wind tunnel force test of fairing separation in hypersonic and high dynamic pressure situation[J]. Journal of Experiments in Fluid Mechanics, 2022,36(X):1-9. doi: 10.11729/syltlx20210194
Citation: ZHONG J,LIN J Z,XIE F T,et al. Wind tunnel force test of fairing separation in hypersonic and high dynamic pressure situation[J]. Journal of Experiments in Fluid Mechanics, 2022,36(X):1-9. doi: 10.11729/syltlx20210194

高超声速大动压下整流罩分离测力风洞试验

doi: 10.11729/syltlx20210194
详细信息
    作者简介:

    钟俊:(1986—),男,四川内江人,硕士,工程师。研究方向:高超声速喷流干扰试验技术,级间分离试验技术,压力测量试验方法。通信地址:四川省绵阳市涪城区二环路南段6号15信箱505分信箱(621000)。E-mail:zhongjun@cardc.cn

    通讯作者:

    E-mail:jzou2000@sina.com

  • 中图分类号: V211.71

Wind tunnel force test of fairing separation in hypersonic and high dynamic pressure situation

  • 摘要: 针对高超声速试验模型整体式整流罩的反推火箭拔罩分离问题,开展了反推火箭喷流模拟方法和风洞测力试验装置设计研究,试验模拟了马赫数5、动压33 kPa时整流罩反推喷流干扰效应和分离距离影响,获得了反推喷流和分离距离影响下的整流罩气动特性。试验研究表明:反推火箭拔罩分离过程中,喷流干扰作用主导了整流罩的气动特性,使得法向力系数、轴向力系数和俯仰力矩系数出现了最大分别为44.5%、32.4%和198.6%的变化量;在负迎角下,整流罩压心前移显著,使得静稳定设计的整流罩呈现出静不稳定性,不利于整流罩安全分离;分离距离越大,分离距离变化对整流罩气动特性的影响越弱;将分离初始迎角限定为小的正迎角,整流罩在分离过程中容易保持姿态稳定,有利于整流罩安全分离。
  • 图  1  某高超声速试验模型及整流罩反推火箭喷管出口示意图

    Figure  1.  Sketch of hypersonic test demonstrator and reverse-thrust jet's orifices on fairing

    图  2  CARDC的Φ1 m高超声速风洞

    Figure  2.  Φ1 m hypersonic wind tunnel of CARDC

    图  3  反推喷管短边出口横截面示意图

    Figure  3.  Cross-section of shot side exit of reverse-thrust jets

    图  4  串联级间分离的通常支撑方式

    Figure  4.  Conventional support method of stage separation

    图  5  不同分离距离下的一体化试验装置

    Figure  5.  Integrated test models with different separation distances

    图  6  缩比飞行器原型前体和4个修形前体

    Figure  6.  Original and redesigned fore-body of scaled test demonstrator

    图  7  整流罩模型和喷流模拟装置照片

    Figure  7.  Photos of fairing model and jet simulation device

    图  8  2.2 D分离距离下有/无喷流试验的纹影照片

    Figure  8.  Schlieren comparison between jets off and on conditions in xd=2.2 D

    图  9  数值计算网格示意图

    Figure  9.  Sketch of CFD grid

    图  10  有/无喷流时整流罩表面的压力云图

    Figure  10.  Comparison of fairing surface pressure between jets off and on

    图  11  2.2 D分离距离、有/无喷流时的试验结果

    Figure  11.  Data comparison between jets off and on conditions in xd=2.2 D

    图  12  0 D~2.2 D分离距离下随迎角变化的有喷流试验结果

    Figure  12.  Jets-on test result with attack angles in separation distance from 0 D to 2.2 D

    图  13  迎角±3°时随分离距离变化的有喷流试验结果

    Figure  13.  Jets-on test result with separation distance at α=−3° and 3°

    表  1  天平主要技术参数

    Table  1.   Main parameters of balance

    天平分量设计载荷精度/(% FS)准度/(% FS)
    轴向力A150 N0.20.4
    法向力N500 N0.20.4
    侧向力Z100 N0.20.4
    俯仰力矩Mz20 N·m0.20.4
    偏航力矩My4 N·m0.20.4
    滚转力矩Mx1 N·m0.20.4
    下载: 导出CSV

    表  2  冷喷流模拟参数

    Table  2.   Parameters of Cooling jets

    pj /ppj /kPaMjp0j /MPaγ
    286541.31.9824.121.4
    下载: 导出CSV

    表  3  试验结果与数值计算结果对比

    Table  3.   Comparison between test result and CFD data

    迎角数值计算结果风洞试验结果计算与试验的相对偏差
    CNCACMzCNCACMzΔCNΔCAΔCMz
    α= –0.000012 0.100925 0 0.00056 0.10657 –0.00006 0.59% 2.69% –4.08%
    α= 0.056205 0.102275 –0.000217 0.05275 0.10737 –0.00016 –3.58% 2.43% 3.88%
    α=9°(基准) 0.09639 0.20973 0.00147
    注:基准为α=9°、无喷流工况下气动载荷系数试验值的绝对值。
    下载: 导出CSV
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  • 收稿日期:  2021-12-28
  • 录用日期:  2022-04-20
  • 修回日期:  2022-04-14
  • 网络出版日期:  2022-05-27

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