Multi-parameter measurement of aerodynamic load via flexible sensing skin

GUO Dongliang; HOU Chao; ZHU Chen; XIONG Wennan; CHEN Shuang; XU Xiaobin; YANG Hua; HUANG Yong,an

doi:10.11729/syltlx20210115

Volume 36 Issue 2

May 2022

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Journal of Experiments in Fluid Mechanics > 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

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Multi-parameter measurement of aerodynamic load via flexible sensing skin

GUO Dongliang^{1, 2,},
HOU Chao^{1, 2,},
ZHU Chen^{1, 2},
XIONG Wennan^{1, 2},
CHEN Shuang³,
XU Xiaobin⁴,
YANG Hua¹,
HUANG Yong,an^{1, 2, ,}

1.
State Key Laboratory of Digital Manufacturing Equipment and Technology, Huazhong University of Science and Technology, Wuhan 　430074, China
2.
Flexible Electronics Research Center, Huazhong University of Science and Technology, Wuhan 　430074, China
3.
Facility Design and Instrumentation Institute, China Aerodynamics Research and Development Center, Mianyang 　621000, China
4.
Hypervelocity Aerodynamic Institute of China, China Aerodynamics Research and Development Center, Mianyang 　621000, China

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Received Date: August 29, 2021
Revised Date: March 03, 2022
Accepted Date: March 15, 2022
Available Online: May 25, 2022

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Abstract

Abstract

Aerodynamic characteristics of aircraft are critical for the design and security evaluation of aircraft structures. Wind tunnel test is the most effective experimental method, which is faced with the problems of structure damage and fewer parameters measurement. Herein, we propose a conformal measurement technique based on flexible sensing skin integrated with variety of ultra-thin flexible sensors, that are attached on surface of aircrafts consistently by kirigami assembly strategy. The sensing skin can simultaneously obtain multiple aerodynamic parameters like static pressure, pulsating pressure, temperature and wall shear force, without changing the surface morphology of the structure. Experiments on NACA0012 wing and aircraft tail under variable wind speed and variable angle of attack are carried out in the direct wind tunnel, jet platform and FL–9 wind tunnel. The characteristics of parameters collected in the wind tunnel are analyzed, which proves the availability of the system, paving a way for simultaneous measurement of various aerodynamic characteristics by flexible sensing skin in wind tunnel experiments.
- multi-parameter sensing,
- wind tunnel test,
- aerodynamic load,
- flexible electronics,
- flexible sensing skin

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