直升机尾桨叶翼型段疲劳试验技术研究  

Fatigue Test Technology of Helicopter Tail Rotor Airfoil Segment

作　　者：宋云 李炳伯 孙云伟 SONG Yun;LI Bing-bo;SUN Yun-wei(China Helicopter Research and Development Institute,Jiangxi Jingdezhen 333001,China;Military Representative Office of CSSC Wuhan Bureau in Nanchang,Jiangxi Nanchang 330000,China)

机构地区：[1]航空工业直升机设计研究所,江西景德镇333001 [2]海装武汉局驻南昌地区军事代表室,南昌330000

出　　处：《装备环境工程》2023年第5期51-56,共6页Equipment Environmental Engineering

摘　　要：目的 提升尾桨叶翼型段疲劳试验安装和调试速率,加快考核出尾桨叶翼型段疲劳性能和疲劳寿命。方法 通过标定出尾桨叶翼型段挥舞与摆振标定系数和预扭角,分析出一种通过理论计算出安装攻角的方法,利用理论计算出的攻角指导实际安装攻角,调整攻角值到实际加载满足试验要求的载荷值,在尾桨叶翼型段安装和调试完成后进行了疲劳试验。结果 4件尾桨叶翼型段理论计算攻角值与实际安装攻角进行对比,安装攻角理论值与实际值偏差范围在1.5°以内,并且4件尾桨叶翼型段疲劳试验载荷分布误差小于4%,疲劳性能满足6000飞行小时的疲劳寿命要求。结论 尾桨叶翼型疲劳试验中,理论计算攻角值具有加快估算安装攻角的意义,提升疲劳试验效率,试验调试载荷分布基本一致。经过尾桨叶翼型段疲劳试验验证后,试验件疲劳性能良好且稳定,为后续科研试验转入鉴定试验提供了基础。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 installa-tion 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 estima-tion 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 iden-tity test.

关 键 词：直升机 尾桨叶翼型段 疲劳试验 安装 调试 攻角 

分 类 号：V216.3[航空宇航科学与技术—航空宇航推进理论与工程]