Measurement Technique and Result Analysis of Helicopter Rotor Blade Structural Vibration Load
The measurement of helicopter rotor blade structural load amid flight has always been the difficulty in flight test. In this paper, the principle of the existing blade structural load measurement method (electrical measurement method) was analyzed, and the problem of physical decoupling in the use o...
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| Main Authors: | , , |
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| Format: | Article |
| Language: | English |
| Published: |
Wiley
2023-01-01
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| Series: | Shock and Vibration |
| Online Access: | http://dx.doi.org/10.1155/2023/6234753 |
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| _version_ | 1849700107894652928 |
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| author | Honglin Zhang Zefeng Wang Pinqi Xia |
| author_facet | Honglin Zhang Zefeng Wang Pinqi Xia |
| author_sort | Honglin Zhang |
| collection | DOAJ |
| description | The measurement of helicopter rotor blade structural load amid flight has always been the difficulty in flight test. In this paper, the principle of the existing blade structural load measurement method (electrical measurement method) was analyzed, and the problem of physical decoupling in the use of this method was expounded. As a weak signal measurement, the electrical measurement method also has electromagnetic interference problems, which will affect the flight test period of blade structural load measurement. Therefore, a numerical decoupling measurement method based on fiber Bragg grating (FBG) was proposed. Then, the new method was applied and verified in the load equation modeling test and the flight test under the real atmospheric environment was carried out. Through comparing and analyzing the measured data of the new method and the electrical measurement one, the correctness of the FBG data decoupling method was validated. The results indicate that the method proposed in this paper can effectively improve the efficiency of blade load equation modeling engineering and has good application value. |
| format | Article |
| id | doaj-art-2db659cc8478443490e7206c927f9aeb |
| institution | DOAJ |
| issn | 1875-9203 |
| language | English |
| publishDate | 2023-01-01 |
| publisher | Wiley |
| record_format | Article |
| series | Shock and Vibration |
| spelling | doaj-art-2db659cc8478443490e7206c927f9aeb2025-08-20T03:18:23ZengWileyShock and Vibration1875-92032023-01-01202310.1155/2023/6234753Measurement Technique and Result Analysis of Helicopter Rotor Blade Structural Vibration LoadHonglin Zhang0Zefeng Wang1Pinqi Xia2Institute of Flight Test TechnologyInstitute of Flight Test TechnologyCollege of Aerospace EngineeringThe measurement of helicopter rotor blade structural load amid flight has always been the difficulty in flight test. In this paper, the principle of the existing blade structural load measurement method (electrical measurement method) was analyzed, and the problem of physical decoupling in the use of this method was expounded. As a weak signal measurement, the electrical measurement method also has electromagnetic interference problems, which will affect the flight test period of blade structural load measurement. Therefore, a numerical decoupling measurement method based on fiber Bragg grating (FBG) was proposed. Then, the new method was applied and verified in the load equation modeling test and the flight test under the real atmospheric environment was carried out. Through comparing and analyzing the measured data of the new method and the electrical measurement one, the correctness of the FBG data decoupling method was validated. The results indicate that the method proposed in this paper can effectively improve the efficiency of blade load equation modeling engineering and has good application value.http://dx.doi.org/10.1155/2023/6234753 |
| spellingShingle | Honglin Zhang Zefeng Wang Pinqi Xia Measurement Technique and Result Analysis of Helicopter Rotor Blade Structural Vibration Load Shock and Vibration |
| title | Measurement Technique and Result Analysis of Helicopter Rotor Blade Structural Vibration Load |
| title_full | Measurement Technique and Result Analysis of Helicopter Rotor Blade Structural Vibration Load |
| title_fullStr | Measurement Technique and Result Analysis of Helicopter Rotor Blade Structural Vibration Load |
| title_full_unstemmed | Measurement Technique and Result Analysis of Helicopter Rotor Blade Structural Vibration Load |
| title_short | Measurement Technique and Result Analysis of Helicopter Rotor Blade Structural Vibration Load |
| title_sort | measurement technique and result analysis of helicopter rotor blade structural vibration load |
| url | http://dx.doi.org/10.1155/2023/6234753 |
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