A Test Method for Helicopter Landing Gear Load

Jiahong Zheng

doi:doi:10.11648/j.ijmea.20210901.14

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A Test Method for Helicopter Landing Gear Load

Jiahong Zheng

Published in International Journal of Mechanical Engineering and Applications (Volume 9, Issue 1)

Received: 18 January 2021 Accepted: Published: 4 March 2021

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Abstract

In this paper, a load test method of landing gear during take-off and landing of helicopter was proposed and the structure of helicopter landing gear, the modification of strain gauge bridge, the establishment of load calibration equation and the flight test of helicopter were studied. Firstly, according to the structure of helicopter landing gear, the stress analysis of landing gear was carried out, and the load position and force form of landing gear were determined during take-off and landing. Then, the measuring principle of the strain bridge was studied. According to the technical requirements, structural characteristics of the landing gear load test and the properties and principles of the strain bridge, the distribution and load measurement form of the strain bridge of the dangerous structure of the landing gear were designed. Then, studying load calibration test scheme of landing gear and carrying out load calibration test, the load calibration equation of landing gear was obtained, and the accuracy of load calibration equation was verified by comparing the expected load and actual load. Through the flight test, the landing gear load during the take-off and landing of the helicopter was obtained. Finally, the valid analysis of flight load data was carried out. The results show that the proposed method is feasible, and the flight test data of landing gear load are accurate and reliable, which can provide data support for the structure modification, fatigue analysis and the life evaluation of landing gear.

Published in	International Journal of Mechanical Engineering and Applications (Volume 9, Issue 1)
DOI	10.11648/j.ijmea.20210901.14
Page(s)	19-24
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, Landing Gear, Flight Test, Load Measurement

References

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[3]	ZbigniewSkorupka. Laboratory Investigations on Landing Gear Ground Reactions (Load) Measurement. Journal of KONES. 2017, 24 (2): 225-230.
[4]	Kou Fujun. The load measurement technology of landing gear in helicopter. The Twenty-eight. Annual Session of Helicopter. Shangyu, China, 2012, pp: 100-106.
[5]	TianJiajie, Mu Po, Cheng Suhua, Feng Xi. Drop Simulation and Drop Test of Aircraft Main Landing Gear with High Sinking Velocity. Chinese Hydraulics and Pneumatics, 2020, (10): 174-180.
[6]	Huaitao Wang, Dafang Wu, Feng Wang, HaoyuanRen. A method for determining the horizontal impact load based on the rotational speed of the aircraft's wheel in a landing gear drop test. International Journal of Crashworthiness, 2018, 23 (6): 627-634.
[7]	ZuoYihong, HE Hongli, FENG Qiaoning, Tian Wei-feng. Application of High Speed Video in Load Test for Aircraft Landing Gear. Electro-opticatechnology Application. 2011, 26 (3): 82-84.
[8]	Currey N S. Aircraft landing gear design: principles and practice. Washington, D. C.: AIAA, 1998: 1-20.
[9]	Cao jingtao. The load measurement technology of landing gear in aircraft. Applied Technology, 2014; 6 (15): 176-178.
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[11]	Kligko M P, Aphaytob E B. Aircraft strength flight test (static). xi’an: ASST System. Engineering Office of Ministry of Aeronautics and Astronautics, 1992. 23~26.
[12]	Kadarno P, Barrinaya M. A, Manurung A. O. Mechanism analysis of a main landing gear of transporting aircraft: A design learning perspective. Engineering Failure Analysis. 2021, 119.
[13]	AdityaArmaan, Sharma Keshav, G. Srinivas. A step towards safety: Material failure analysis of landing gear. Materials Today: Proceedings. 2020, 27 (1): 402-409.
[14]	Li Yongshou, Tang Lifang. Study on Load Measurement of Transmission System in Helicopter Flight. Science and Technology Innovation Herald. 2011, 6: 2-3.
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[16]	Tang Ani. Analysis of usage landing gears loads spectrum for an aircraft’s landing gears. Structure and Environment Engineering. 2007, 34 (4): 43-48.
[17]	GAO Zhengtong. Fatigue application statistics. Beijing: National Defense Industry Press, 1986. 336~344.
[18]	A. Iele, M. Leone, M. Consales, G. V. Persiano. Load monitoring of aircraft landing gears using fiber optic sensors. Sensors and Actuators A: Physical, 2018, 281: 31-41.

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APA Style

Jiahong Zheng. (2021). A Test Method for Helicopter Landing Gear Load. International Journal of Mechanical Engineering and Applications, 9(1), 19-24. https://doi.org/10.11648/j.ijmea.20210901.14

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ACS Style

Jiahong Zheng. A Test Method for Helicopter Landing Gear Load. Int. J. Mech. Eng. Appl. 2021, 9(1), 19-24. doi: 10.11648/j.ijmea.20210901.14

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AMA Style

Jiahong Zheng. A Test Method for Helicopter Landing Gear Load. Int J Mech Eng Appl. 2021;9(1):19-24. doi: 10.11648/j.ijmea.20210901.14

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@article{10.11648/j.ijmea.20210901.14,
  author = {Jiahong Zheng},
  title = {A Test Method for Helicopter Landing Gear Load},
  journal = {International Journal of Mechanical Engineering and Applications},
  volume = {9},
  number = {1},
  pages = {19-24},
  doi = {10.11648/j.ijmea.20210901.14},
  url = {https://doi.org/10.11648/j.ijmea.20210901.14},
  eprint = {https://article.sciencepublishinggroup.com/pdf/10.11648.j.ijmea.20210901.14},
  abstract = {In this paper, a load test method of landing gear during take-off and landing of helicopter was proposed and the structure of helicopter landing gear, the modification of strain gauge bridge, the establishment of load calibration equation and the flight test of helicopter were studied. Firstly, according to the structure of helicopter landing gear, the stress analysis of landing gear was carried out, and the load position and force form of landing gear were determined during take-off and landing. Then, the measuring principle of the strain bridge was studied. According to the technical requirements, structural characteristics of the landing gear load test and the properties and principles of the strain bridge, the distribution and load measurement form of the strain bridge of the dangerous structure of the landing gear were designed. Then, studying load calibration test scheme of landing gear and carrying out load calibration test, the load calibration equation of landing gear was obtained, and the accuracy of load calibration equation was verified by comparing the expected load and actual load. Through the flight test, the landing gear load during the take-off and landing of the helicopter was obtained. Finally, the valid analysis of flight load data was carried out. The results show that the proposed method is feasible, and the flight test data of landing gear load are accurate and reliable, which can provide data support for the structure modification, fatigue analysis and the life evaluation of landing gear.},
 year = {2021}
}

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TY  - JOUR
T1  - A Test Method for Helicopter Landing Gear Load
AU  - Jiahong Zheng
Y1  - 2021/03/04
PY  - 2021
N1  - https://doi.org/10.11648/j.ijmea.20210901.14
DO  - 10.11648/j.ijmea.20210901.14
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  - 19
EP  - 24
PB  - Science Publishing Group
SN  - 2330-0248
UR  - https://doi.org/10.11648/j.ijmea.20210901.14
AB  - In this paper, a load test method of landing gear during take-off and landing of helicopter was proposed and the structure of helicopter landing gear, the modification of strain gauge bridge, the establishment of load calibration equation and the flight test of helicopter were studied. Firstly, according to the structure of helicopter landing gear, the stress analysis of landing gear was carried out, and the load position and force form of landing gear were determined during take-off and landing. Then, the measuring principle of the strain bridge was studied. According to the technical requirements, structural characteristics of the landing gear load test and the properties and principles of the strain bridge, the distribution and load measurement form of the strain bridge of the dangerous structure of the landing gear were designed. Then, studying load calibration test scheme of landing gear and carrying out load calibration test, the load calibration equation of landing gear was obtained, and the accuracy of load calibration equation was verified by comparing the expected load and actual load. Through the flight test, the landing gear load during the take-off and landing of the helicopter was obtained. Finally, the valid analysis of flight load data was carried out. The results show that the proposed method is feasible, and the flight test data of landing gear load are accurate and reliable, which can provide data support for the structure modification, fatigue analysis and the life evaluation of landing gear.
VL  - 9
IS  - 1
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 Test Method for Helicopter Landing Gear Load. International Journal of Mechanical Engineering and Applications, 9(1), 19-24. https://doi.org/10.11648/j.ijmea.20210901.14

Copy | Download

ACS Style

Jiahong Zheng. A Test Method for Helicopter Landing Gear Load. Int. J. Mech. Eng. Appl. 2021, 9(1), 19-24. doi: 10.11648/j.ijmea.20210901.14

Copy | Download

AMA Style

Jiahong Zheng. A Test Method for Helicopter Landing Gear Load. Int J Mech Eng Appl. 2021;9(1):19-24. doi: 10.11648/j.ijmea.20210901.14

Copy | Download

@article{10.11648/j.ijmea.20210901.14,
  author = {Jiahong Zheng},
  title = {A Test Method for Helicopter Landing Gear Load},
  journal = {International Journal of Mechanical Engineering and Applications},
  volume = {9},
  number = {1},
  pages = {19-24},
  doi = {10.11648/j.ijmea.20210901.14},
  url = {https://doi.org/10.11648/j.ijmea.20210901.14},
  eprint = {https://article.sciencepublishinggroup.com/pdf/10.11648.j.ijmea.20210901.14},
  abstract = {In this paper, a load test method of landing gear during take-off and landing of helicopter was proposed and the structure of helicopter landing gear, the modification of strain gauge bridge, the establishment of load calibration equation and the flight test of helicopter were studied. Firstly, according to the structure of helicopter landing gear, the stress analysis of landing gear was carried out, and the load position and force form of landing gear were determined during take-off and landing. Then, the measuring principle of the strain bridge was studied. According to the technical requirements, structural characteristics of the landing gear load test and the properties and principles of the strain bridge, the distribution and load measurement form of the strain bridge of the dangerous structure of the landing gear were designed. Then, studying load calibration test scheme of landing gear and carrying out load calibration test, the load calibration equation of landing gear was obtained, and the accuracy of load calibration equation was verified by comparing the expected load and actual load. Through the flight test, the landing gear load during the take-off and landing of the helicopter was obtained. Finally, the valid analysis of flight load data was carried out. The results show that the proposed method is feasible, and the flight test data of landing gear load are accurate and reliable, which can provide data support for the structure modification, fatigue analysis and the life evaluation of landing gear.},
 year = {2021}
}

Copy | Download

TY  - JOUR
T1  - A Test Method for Helicopter Landing Gear Load
AU  - Jiahong Zheng
Y1  - 2021/03/04
PY  - 2021
N1  - https://doi.org/10.11648/j.ijmea.20210901.14
DO  - 10.11648/j.ijmea.20210901.14
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  - 19
EP  - 24
PB  - Science Publishing Group
SN  - 2330-0248
UR  - https://doi.org/10.11648/j.ijmea.20210901.14
AB  - In this paper, a load test method of landing gear during take-off and landing of helicopter was proposed and the structure of helicopter landing gear, the modification of strain gauge bridge, the establishment of load calibration equation and the flight test of helicopter were studied. Firstly, according to the structure of helicopter landing gear, the stress analysis of landing gear was carried out, and the load position and force form of landing gear were determined during take-off and landing. Then, the measuring principle of the strain bridge was studied. According to the technical requirements, structural characteristics of the landing gear load test and the properties and principles of the strain bridge, the distribution and load measurement form of the strain bridge of the dangerous structure of the landing gear were designed. Then, studying load calibration test scheme of landing gear and carrying out load calibration test, the load calibration equation of landing gear was obtained, and the accuracy of load calibration equation was verified by comparing the expected load and actual load. Through the flight test, the landing gear load during the take-off and landing of the helicopter was obtained. Finally, the valid analysis of flight load data was carried out. The results show that the proposed method is feasible, and the flight test data of landing gear load are accurate and reliable, which can provide data support for the structure modification, fatigue analysis and the life evaluation of landing gear.
VL  - 9
IS  - 1
ER  -

Copy | Download