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| Development and Application of Fatigue and Flaw Tolerance Test Device on Helicopter Tail Structure |
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| DOI：10.7643/issn.1672-9242.2023.05.007 |
| KeyWord:tail structure fatigue and flaw tolerance test method impact nondestructive testing |
| Author | Institution |
| LI Qing-rong |
China Helicopter Research and Development Institute, Jiangxi Jingdezhen, , China |
| BAO Ming |
China Helicopter Research and Development Institute, Jiangxi Jingdezhen, , China |
| JIANG Hong-liu |
Nanchang Hangkong University, Nanchang , China |
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| Abstract: |
| The work aims to study the fatigue and flaw tolerance test technology of composite tail structure, in order to obtain the fatigue life and check interval of tail structure, meet the airworthiness verification requirements of civil helicopters and ensure the flight safety of helicopters. The design and development of the specialized test bench, pneumatic impact equipment, flexible automatic scanning and imaging nondestructive testing system for the fatigue and flaw tolerance test of tail structure were described. With the whole set of test devices, the connecting restriction and load boundary of the tail structure specimen were simulated fully, the complex load spectrum was controlled accurately, the impact flaws were prefabricated and the flaws were detected automatically. The experimental results indicated that the load error was less than 2%, the impact energy error was less than 2% and the error of flaw detection was less than 1 mm. All indicators satisfied the research objectives and technical indicators of the project. The research results have been successfully applied in the development of civil helicopters, which can provide a good reference for other helicopter tail structure fatigue and flaw tolerance tests, and has important engineering application value. |
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