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

doi:10.11729/syltlx20180137

气动热环境试验及测量技术研究进展

1.
中国运载火箭技术研究院, 北京 100076
2.
中国运载火箭技术研究院空间物理重点实验室, 北京 100076

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
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出版历程
- 收稿日期: 2018-10-08
- 修回日期: 2019-01-12
- 刊出日期: 2019-04-24

Research progress of aerodynamic thermal environment test and measurement technology

1.
China Academy of Launch Vehicle Technology, Beijing 100076, China
2.
Science and Technology on Space Physics Laboratory, China Academy of Launch Vehicle Technology, Beijing 100076, China

摘要

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。
- 临近空间 /
- 高超声速 /
- 气动热环境 /
- 测量技术
Abstract: Ground wind tunnel tests and flight tests are the primary means of obtaining pneumatic heating data. In this paper, the development of the domestic hypersonic aerodynamic test and the heat flux measurement technology is analyzed and discussed. Firstly, the shape characteristics, the flight profile, the boundary layer transition and the aerodynamic thermal environment characteristics of the adjacent space hypersonic vehicles are analyzed. On this basis, the wind tunnel test simulation theory of the aerodynamic thermal environment is analyzed, and the domestic application for aerodynamic thermal measurement, wind tunnel test equipment and its simulation capability are introduced, focusing on the analysis of the development and trend of wind tunnel aerodynamic thermal environment measurement technology, including point measurement technology based on sensor measurement and non-contact measurement technology such as phosphorescence heat map technology and infrared heat map technology. Finally, the measurement principle and engineering application of the "built-in" and "embedded" measure-ment technologies are introduced for the flight test thermal environment measurement. The problems faced by the flight test aerodynamic thermal environment measurement are discussed. Both further research and present problems for thermal environment measurement technologies are proposed.
- near space /
- hypersonic /
- aerodynamic thermal environment /
- measurement technology

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图 1 CAAA风洞马赫数/雷诺数模拟能力

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

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图 2 JF12风洞条件下传感器考核试验

Fig. 2 Sensor evaluation test in JF12 wind tunnel

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图 3 小型化热流传感器

Fig. 3 Miniaturized heat flow sensor

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图 4 一体化热流传感器

Fig. 4 Intergrated heat flow sensor

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图 5 空气舵风洞测热模型和表面热流

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

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图 6 风洞试验结果与数值计算结果对比

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

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图 7 不同催化条件下模型表面热流^[19]

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

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图 8 双色磷光热图系统示意图

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

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图 9 FLAP空气舵磷光测热结果

Fig. 9 FLAP air rudder phosphorescence heat test resultsS

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图 10 平板尖楔试验结果定量对比

Fig. 10 Quantitative comparison of flat wedge test results

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图 11 低密度风洞球锥模型热流测量结果

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

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图 12 低密度风洞试验结果与DSMC计算结果对比

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

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图 13 航天飞机气动热参数辨识结果

Fig. 13 Space shuttle aerodynamic heating identification results

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图 14 气动热辨识流程^[30]

Fig. 14 Heat flux identification process^[30]S

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图 15 热流辨识结果与测量结果对比

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

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图 16 热流传感器

Fig. 16 Heat flux sensors

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图 17 表面温度不连续示意图

Fig. 17 Surface temperature discontinuitys

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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

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

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图 19 哈尔滨工业大学的热流传感器^[32]

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

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图 20 气动热-结构响应耦合计算流程图^[33]

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

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图 21 圆箔式热流传感器内部及安装示意图

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

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图 22 传感器催化特性差异对气动热的影响^[35]

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

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图 23 空气舵干扰区热流分布

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

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