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飞行器表面气动载荷的柔性智能蒙皮多参量测量

郭栋梁 侯超 朱臣 熊文楠 陈爽 许晓斌 杨华 黄永安

郭栋梁,侯超,朱臣,等. 飞行器表面气动载荷的柔性智能蒙皮多参量测量[J]. 实验流体力学,2022,36(2):146-154 doi: 10.11729/syltlx20210115
引用本文: 郭栋梁,侯超,朱臣,等. 飞行器表面气动载荷的柔性智能蒙皮多参量测量[J]. 实验流体力学,2022,36(2):146-154 doi: 10.11729/syltlx20210115
GUO D L,HOU C,ZHU C,et al. Multi-parameter measurement of aerodynamic load via flexible sensing skin[J]. Journal of Experiments in Fluid Mechanics, 2022,36(2):146-154. doi: 10.11729/syltlx20210115
Citation: GUO D L,HOU C,ZHU C,et al. Multi-parameter measurement of aerodynamic load via flexible sensing skin[J]. Journal of Experiments in Fluid Mechanics, 2022,36(2):146-154. doi: 10.11729/syltlx20210115

飞行器表面气动载荷的柔性智能蒙皮多参量测量

doi: 10.11729/syltlx20210115
基金项目: 国家重点研发计划资助(2020YFA0405700);国家自然科学基金(51635007,51925503);中央高校基本科研业务费专项资金(2019kfyRCPY017)
详细信息
    作者简介:

    郭栋梁:(1992—),男,河北邢台人,博士研究生。研究方向:飞行器智能蒙皮技术,柔性传感技术,风洞测试技术。通信地址:湖北省武汉市洪山区珞喻路1037号华中科技大学(430074)。E-mail:78312889@qq.com

    侯超:(1996—),男,四川南充人,博士研究生。研究方向:飞行器智能蒙皮技术,柔性传感技术,形状重构技术。通信地址:湖北省武汉市洪山区珞喻路1037号华中科技大学(430074)。E-mail:809762746@qq.com

    通讯作者:

    E-mail:yahuang@hust.edu.cn

  • 中图分类号: TP212.9;V211.753

Multi-parameter measurement of aerodynamic load via flexible sensing skin

  • 摘要: 飞行器表面气动参数特征是飞行器结构设计和安全评估的重要依据,而风洞试验作为最有效的测试手段,通常面临破坏结构、测量物理量单一等问题。提出曲面共形的柔性智能蒙皮测量技术,集成了多种超薄柔性传感器阵列,通过剪纸–拼接的完全共形方式集成到飞行器结构表面,在不改变结构表面形貌的情况下同步实时测量壁面静态压力、脉动压力、温度、壁面剪应力等多种气动参数。在直流式风洞、射流平台和FL–9风洞中对NACA0012机翼和飞行器尾翼进行了变风速和变迎角试验,分析风洞试验中采集获得的多种气动参数,验证了该系统的可用性,为风洞试验中柔性智能蒙皮多参量同步测量气动特性研究提供参考。
  • 图  1  柔性智能蒙皮与感知

    Figure  1.  Flexible sensing skin and flow field perception

    图  2  柔性智能蒙皮系统

    Figure  2.  System of flexible sensing skin

    图  3  柔性传感器及测量原理示意图

    Figure  3.  Flexible sensors and schematic diagrams

    图  4  柔性智能蒙皮系统风洞试验

    Figure  4.  Wind tunnel experiment of sensing skin system

    图  5  NACA0012机翼小型风洞试验脉动压力结果

    Figure  5.  Results of pulsating pressure in wind tunnel test with different angles of attack

    图  6  静态差压标定和升力系数随NACA0012机翼迎角变化

    Figure  6.  Results of static pressure in wind tunnel test with different angles of attack

    图  7  柔性温度传感器试验结果图

    Figure  7.  Calibration of flexible temperature sensor and wind tunnel test results

    图  8  热膜传感器在尾翼不同位置的响应

    Figure  8.  Voltage signal vibration of hot film sensors in aircraft tail

    图  9  飞行器颤振信号联合分析

    Figure  9.  Analysis of multi-signals for aircraft flutter test

    表  1  传感器性能参数

    Table  1.   Performance parameters of sensors

    传感器类型敏感区尺寸厚度/μm响应时间/ms采样频率/Hz分辨率量程
    动压ϕ1.5 mm25550010
    静压ϕ3 mm6010010005 Pa0~6 kPa
    热膜1 mm×0.08 mm2021000
    温度1.5 mm×3.5 mm1010020.5 ℃–20~120 ℃
    下载: 导出CSV
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出版历程
  • 收稿日期:  2021-08-30
  • 修回日期:  2022-03-04
  • 录用日期:  2022-03-16
  • 网络出版日期:  2022-05-26
  • 刊出日期:  2022-05-19

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