摘要
在某梁体模拟件疲劳试验的基础上,对疲劳仿真模型进行了细致的有限元计算,系统地分析了不同孔半径下孔边的寿命和同一孔半径下孔的径向寿命变化规律,讨论了不同铰孔次数、不同铰孔时机和铰孔量下的寿命变化规律。结果表明,在模拟件孔边损伤达到极限时为最佳铰孔时机,最佳铰孔量为0.5mm;若铰孔次数由零次增加到一次,总寿命将增加64%;若铰孔次数由一次增加到两次,总寿命增幅仅为25%;若铰孔时机提前,或者铰孔量过大、过小都会降低模拟件的总寿命。
On the base of the fatigue test for thesimulated member of beam structure, the refined finite element calculation was carried out for fatigue imitated former, the variation rule for the hole edge life at the different hole radii and the radial life at the same hole radiusis analyzed systematically, the life variation rule under the different frequencies, timings and quantities of reaming is discussed. The result shows that, when the damage on the hole edge of simulated member is up to the limitation, it is an optimum timing for reaming, and the optimum reaming quantity is 0.5mm; if the reaming frequency is added from 0 to 1, the total service life will be increased to 64%; if the reaming frequency is added from 1 to 2, the amplitude of the total service life is just 25%; if the reaming timing is advanced or the reaming quantity is too big/small, the total service life of the simulated member will be reduced.
作者
王刚化
李明鸿
Wang Ganghua;Li Minghong(Aircraft Design Institute of Guizhou Aviation industry Corporation,Anshun 561000,China)
出处
《航空科学技术》
2018年第11期14-19,共6页
Aeronautical Science & Technology
关键词
铰孔寿命
铰孔时机
铰孔量
铰孔次数
模拟件
reaming life
reaming timing
reaming quantity
reaming frequency
simulation