A Flight Load Test Method for Helicopter Rotor Blade

Jiahong Zheng

doi:doi:10.11648/j.ijmea.20210905.11

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A Flight Load Test Method for Helicopter Rotor Blade

Jiahong Zheng

Published in International Journal of Mechanical Engineering and Applications (Volume 9, Issue 5)

Received: 26 September 2021 Accepted: 18 October 2021 Published: 29 October 2021

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Abstract

This paper studies a flight load test method for helicopter blade, including the structural force of helicopter blade, strain gauge bridge modification, load calibration method and the establishment of load calibration equation in the typical maneuvers. First, blade structure of the helicopter was analyzed and the strain gauges were pasted in the load profile which were considered to be important positions to analysis the flight safe of helicopter. Second, Load calibration equations were obtained by ground calibration test, which would be used to convert the strain time curve to the load time curve. The helicopter flighted in different maneuvers, such as hovering, horizontal flight and climbing. At the same time, flight parameters were recorded, such as helicopter altitude, pitch angle, roll angle and yaw Angle. The flight parameters can be used to analysis the flight conditions. Then the blade flight load in different flight maneuvers was analyzed. The result was that the time-domain waveform was neat, good periodicity, strong regularity, no hybrid interference and jump point. It was illustrated that the blade load test flight data were accurate and reliable, which met the accuracy requirements of Engineering. The blade load data obtained through different flight maneuvers can be used to structural modification, fatigue analysis and blade design.

Published in	International Journal of Mechanical Engineering and Applications (Volume 9, Issue 5)
DOI	10.11648/j.ijmea.20210905.11
Page(s)	75-78
Creative Commons	This is an Open Access article, distributed under the terms of the Creative Commons Attribution 4.0 International License (http://creativecommons.org/licenses/by/4.0/), which permits unrestricted use, distribution and reproduction in any medium or format, provided the original work is properly cited.
Copyright	Copyright © The Author(s), 2024. Published by Science Publishing Group

Keywords

Helicopter, Rotor Blade, Flight Test, Load Measurement

References

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[4]	Liu Mingming, Liu Bingkun, Dai Qiang. Helicopter rotor blade load measurement method [J]. Electronic technology and software engineering. 2020 (03): 97-99.
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[6]	Wang huanjin, Gao Zheng. Calculation method of dynamic aerodynamic load of helicopter rotor blade [J]. Journal of Nanjing University of Aeronautics and Astronautics. 1999 (01).
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[12]	Han Yuwang, Zhu Guangming, Chen Gongli. Study on a new method of helicopter rotor blade load calibration [J]. Helicopter technology. 2012 (03): 29-33.
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APA Style

Jiahong Zheng. (2021). A Flight Load Test Method for Helicopter Rotor Blade. International Journal of Mechanical Engineering and Applications, 9(5), 75-78. https://doi.org/10.11648/j.ijmea.20210905.11

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ACS Style

Jiahong Zheng. A Flight Load Test Method for Helicopter Rotor Blade. Int. J. Mech. Eng. Appl. 2021, 9(5), 75-78. doi: 10.11648/j.ijmea.20210905.11

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AMA Style

Jiahong Zheng. A Flight Load Test Method for Helicopter Rotor Blade. Int J Mech Eng Appl. 2021;9(5):75-78. doi: 10.11648/j.ijmea.20210905.11

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@article{10.11648/j.ijmea.20210905.11,
  author = {Jiahong Zheng},
  title = {A Flight Load Test Method for Helicopter Rotor Blade},
  journal = {International Journal of Mechanical Engineering and Applications},
  volume = {9},
  number = {5},
  pages = {75-78},
  doi = {10.11648/j.ijmea.20210905.11},
  url = {https://doi.org/10.11648/j.ijmea.20210905.11},
  eprint = {https://article.sciencepublishinggroup.com/pdf/10.11648.j.ijmea.20210905.11},
  abstract = {This paper studies a flight load test method for helicopter blade, including the structural force of helicopter blade, strain gauge bridge modification, load calibration method and the establishment of load calibration equation in the typical maneuvers. First, blade structure of the helicopter was analyzed and the strain gauges were pasted in the load profile which were considered to be important positions to analysis the flight safe of helicopter. Second, Load calibration equations were obtained by ground calibration test, which would be used to convert the strain time curve to the load time curve. The helicopter flighted in different maneuvers, such as hovering, horizontal flight and climbing. At the same time, flight parameters were recorded, such as helicopter altitude, pitch angle, roll angle and yaw Angle. The flight parameters can be used to analysis the flight conditions. Then the blade flight load in different flight maneuvers was analyzed. The result was that the time-domain waveform was neat, good periodicity, strong regularity, no hybrid interference and jump point. It was illustrated that the blade load test flight data were accurate and reliable, which met the accuracy requirements of Engineering. The blade load data obtained through different flight maneuvers can be used to structural modification, fatigue analysis and blade design.},
 year = {2021}
}

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TY - JOUR
T1 - A Flight Load Test Method for Helicopter Rotor Blade
AU - Jiahong Zheng
Y1 - 2021/10/29
PY - 2021
N1 - https://doi.org/10.11648/j.ijmea.20210905.11
DO - 10.11648/j.ijmea.20210905.11
T2 - International Journal of Mechanical Engineering and Applications
JF - International Journal of Mechanical Engineering and Applications
JO - International Journal of Mechanical Engineering and Applications
SP - 75
EP - 78
PB - Science Publishing Group
SN - 2330-0248
UR - https://doi.org/10.11648/j.ijmea.20210905.11
AB - This paper studies a flight load test method for helicopter blade, including the structural force of helicopter blade, strain gauge bridge modification, load calibration method and the establishment of load calibration equation in the typical maneuvers. First, blade structure of the helicopter was analyzed and the strain gauges were pasted in the load profile which were considered to be important positions to analysis the flight safe of helicopter. Second, Load calibration equations were obtained by ground calibration test, which would be used to convert the strain time curve to the load time curve. The helicopter flighted in different maneuvers, such as hovering, horizontal flight and climbing. At the same time, flight parameters were recorded, such as helicopter altitude, pitch angle, roll angle and yaw Angle. The flight parameters can be used to analysis the flight conditions. Then the blade flight load in different flight maneuvers was analyzed. The result was that the time-domain waveform was neat, good periodicity, strong regularity, no hybrid interference and jump point. It was illustrated that the blade load test flight data were accurate and reliable, which met the accuracy requirements of Engineering. The blade load data obtained through different flight maneuvers can be used to structural modification, fatigue analysis and blade design.
VL - 9
IS - 5
ER -

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Author Information

Jiahong Zheng

Institute of Flight Test Technology, Chinese Flight Test Establishment, Xi’an, China

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Plain Text BibTeX RIS

APA Style

Jiahong Zheng. (2021). A Flight Load Test Method for Helicopter Rotor Blade. International Journal of Mechanical Engineering and Applications, 9(5), 75-78. https://doi.org/10.11648/j.ijmea.20210905.11

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ACS Style

Jiahong Zheng. A Flight Load Test Method for Helicopter Rotor Blade. Int. J. Mech. Eng. Appl. 2021, 9(5), 75-78. doi: 10.11648/j.ijmea.20210905.11

Copy | Download

AMA Style

Jiahong Zheng. A Flight Load Test Method for Helicopter Rotor Blade. Int J Mech Eng Appl. 2021;9(5):75-78. doi: 10.11648/j.ijmea.20210905.11

Copy | Download

@article{10.11648/j.ijmea.20210905.11,
  author = {Jiahong Zheng},
  title = {A Flight Load Test Method for Helicopter Rotor Blade},
  journal = {International Journal of Mechanical Engineering and Applications},
  volume = {9},
  number = {5},
  pages = {75-78},
  doi = {10.11648/j.ijmea.20210905.11},
  url = {https://doi.org/10.11648/j.ijmea.20210905.11},
  eprint = {https://article.sciencepublishinggroup.com/pdf/10.11648.j.ijmea.20210905.11},
  abstract = {This paper studies a flight load test method for helicopter blade, including the structural force of helicopter blade, strain gauge bridge modification, load calibration method and the establishment of load calibration equation in the typical maneuvers. First, blade structure of the helicopter was analyzed and the strain gauges were pasted in the load profile which were considered to be important positions to analysis the flight safe of helicopter. Second, Load calibration equations were obtained by ground calibration test, which would be used to convert the strain time curve to the load time curve. The helicopter flighted in different maneuvers, such as hovering, horizontal flight and climbing. At the same time, flight parameters were recorded, such as helicopter altitude, pitch angle, roll angle and yaw Angle. The flight parameters can be used to analysis the flight conditions. Then the blade flight load in different flight maneuvers was analyzed. The result was that the time-domain waveform was neat, good periodicity, strong regularity, no hybrid interference and jump point. It was illustrated that the blade load test flight data were accurate and reliable, which met the accuracy requirements of Engineering. The blade load data obtained through different flight maneuvers can be used to structural modification, fatigue analysis and blade design.},
 year = {2021}
}

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