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气动热环境试验及测量技术研究进展

朱广生 聂春生 曹占伟 袁野

朱广生, 聂春生, 曹占伟, 等. 气动热环境试验及测量技术研究进展[J]. 实验流体力学, 2019, 33(2): 1-10. doi: 10.11729/syltlx20180137
引用本文: 朱广生, 聂春生, 曹占伟, 等. 气动热环境试验及测量技术研究进展[J]. 实验流体力学, 2019, 33(2): 1-10. doi: 10.11729/syltlx20180137
Zhu Guangsheng, Nie Chunsheng, Cao Zhanwei, et al. Research progress of aerodynamic thermal environment test and measurement technology[J]. Journal of Experiments in Fluid Mechanics, 2019, 33(2): 1-10. doi: 10.11729/syltlx20180137
Citation: Zhu Guangsheng, Nie Chunsheng, Cao Zhanwei, et al. Research progress of aerodynamic thermal environment test and measurement technology[J]. Journal of Experiments in Fluid Mechanics, 2019, 33(2): 1-10. doi: 10.11729/syltlx20180137

气动热环境试验及测量技术研究进展

doi: 10.11729/syltlx20180137
详细信息
    作者简介:

    朱广生(1963-), 男, 江苏徐州人, 博士, 研究员。研究方向:飞行器空气动力学和总体设计。通信地址: 北京9200信箱89分箱(100076). E-mail:zgs_0128@163.com

    通讯作者:

    朱广生, E-mail:zgs_0128@163.com

  • 中图分类号: V231.2

Research progress of aerodynamic thermal environment test and measurement technology

  • 摘要: 地面风洞试验和飞行试验是研究高超声速飞行器气动加热的主要手段。针对临近空间复杂气动外形高超声速飞行器气动热环境研究的需要,分析探讨了国内气动热试验及测量技术的发展情况。分析了临近空间高超声速飞行器外形特征以及飞行剖面、边界层转捩和气动热环境特性等,进而分析了气动热环境风洞试验模拟理论,介绍了适用于气动热研究的风洞试验设备及其模拟能力,重点讨论了适用于不同类型风洞的热流测量技术发展近况、存在的问题和发展趋势;在以长时间、高热流、高壁温为主要特征的高超声速飞行试验中,无法应用风洞环境下的热流测量技术,因而介绍了目前飞行试验中采用的气动热测量技术,讨论了根据结构温度反辨识表面热流存在的问题,以及热流传感器表面的"冷点效应"、表面催化特性等因素对飞行试验气动热测量的影响,提出了后续工作中应重点研究和解决的临近空间飞行器气动热环境测量技术问题。
  • 图  1  CAAA风洞马赫数/雷诺数模拟能力

    Figure  1.  Mach number/Reynolds number simulation capability of CAAA wind tunnel

    图  2  JF12风洞条件下传感器考核试验

    Figure  2.  Sensor evaluation test in JF12 wind tunnel

    图  3  小型化热流传感器

    Figure  3.  Miniaturized heat flow sensor

    图  4  一体化热流传感器

    Figure  4.  Intergrated heat flow sensor

    图  5  空气舵风洞测热模型和表面热流

    Figure  5.  Air rudder wind tunnel heat measurement model and surface heat flux

    图  6  风洞试验结果与数值计算结果对比

    Figure  6.  Comparison of wind tunnel test results and numerical calculation results

    图  7  不同催化条件下模型表面热流[19]

    Figure  7.  Model surface heat flux under different catalytic conditions[19]

    图  8  双色磷光热图系统示意图

    Figure  8.  Schematic diagram of two-color phosphorescent heat map system

    图  9  FLAP空气舵磷光测热结果

    Figure  9.  FLAP air rudder phosphorescence heat test resultsS

    图  10  平板尖楔试验结果定量对比

    Figure  10.  Quantitative comparison of flat wedge test results

    图  11  低密度风洞球锥模型热流测量结果

    Figure  11.  Heat flux measurement results of spherical cone model under low density wind tunnel conditions

    图  12  低密度风洞试验结果与DSMC计算结果对比

    Figure  12.  Comparison of low density wind tunnel test results with DSMC calculation results

    图  13  航天飞机气动热参数辨识结果

    Figure  13.  Space shuttle aerodynamic heating identification results

    图  14  气动热辨识流程[30]

    Figure  14.  Heat flux identification process[30]S

    图  15  热流辨识结果与测量结果对比

    Figure  15.  Comparison of heat flux identification results with measurement results

    图  16  热流传感器

    Figure  16.  Heat flux sensors

    图  17  表面温度不连续示意图

    Figure  17.  Surface temperature discontinuitys

    图  18  静温250K、速度5550m/s状态下热流传感器敏感端面附近流场参数

    Figure  18.  Flow field parameters of heat flux sensor's sensitive end face at static temperature 250K and speed 5550m/s

    图  19  哈尔滨工业大学的热流传感器[32]

    Figure  19.  Heat flux sensor of Harbin Institute of Technology[32]

    图  20  气动热-结构响应耦合计算流程图[33]

    Figure  20.  Flow chart of aeroheating-structure response coupling calculation[33]

    图  21  圆箔式热流传感器内部及安装示意图

    Figure  21.  Internal structure and installation diagram of round foil heat flux sensor

    图  22  传感器催化特性差异对气动热的影响[35]

    Figure  22.  Effect of sensor catalytic characteristics on surface heat flux[35]S

    图  23  空气舵干扰区热流分布

    Figure  23.  Heat flux distribution in the air rudder interference zone

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  • 收稿日期:  2018-10-09
  • 修回日期:  2019-01-13
  • 刊出日期:  2019-04-25

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