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| Fatigue Test Technology of Helicopter Tail Rotor Airfoil Segment |
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| DOI：10.7643/issn.1672-9242.2023.05.008 |
| KeyWord:helicopter tail rotor airfoil segment fatigue test installation commissioning angle of attack |
| Author | Institution |
| SONG Yun |
China Helicopter Research and Development Institute, Jiangxi Jingdezhen , China |
| LI Bing-bo |
Military Representative Office of CSSC Wuhan Bureau in Nanchang, Jiangxi Nanchang , China |
| SUN Yun-wei |
China Helicopter Research and Development Institute, Jiangxi Jingdezhen , China |
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| Abstract: |
| The work aims to improve the installation and commissioning speed of the helicopter tail rotor airfoil segment in fatigue test, and accelerate the assessment on fatigue performance and fatigue life of the tail rotor airfoil segment. By calibrating the flapping and lag calibration coefficients and pre-torsion angle of tail rotor airfoil segment, a method to calculate the installation angle of attack by theory was analyzed. The angle of attack calculated by theory was used to guide the actual installation angle of attack and adjust the angle of attack value to the actual load value that met the test requirements. The fatigue test was carried out after the installation and commissioning of tail rotor airfoil segment. The angles of attack of four tail rotor airfoil segments calculated theoretically were compared with the actual angles of attack. The deviation between the theoretical value and the actual value of the installation angle of attack was within 1.5°, the load distribution error of the fatigue test for four tail rotor airfoil segments was less than 4%, and the fatigue performance met the fatigue life requirements of 6000 flight hours. The angle of attack of tail rotor airfoil segment calculated theoretically in fatigue test has the significance of accelerating the estimation of the installation angle of attack and can improve the efficiency of the fatigue test and ensure the distribution of test load is basically consistent during the commissioning. The fatigue performance of test piece is good and stable after the fatigue test verification of the tail rotor airfoil segment, which provides the basis for the subsequent scientific research test to turn into identity test. |
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