基于双向流-固耦合的大展弦比机翼疲劳寿命分析  

FATIGUE LIFE ANALYSIS OF WING WITH HIGH ASPECT RATIO BASED ON BIDIRECTIONAL FLUID-STRUCTURE COUPLING

作　　者：李金洋 王军利[1] 雷帅 冯钰茹 杜天玮 LI JinYang;WANG JunLi;LEI Shuai;FENG YuRu;DU TianWei(Mechanical Engineering College,Shaanxi University of Technology,Hanzhong 723000,China;Mechanical Engineering College,Tianjin University of Science&Technology,Tianjin 300222,China)

机构地区：[1]陕西理工大学机械工程学院,汉中723000 [2]天津科技大学机械工程学院,天津300222

出　　处：《机械强度》2022年第5期1207-1213,共7页Journal of Mechanical Strength

基　　金：陕西省技术创新引导专项基金(2021QFY05-03);陕西省科学技术厅一般项目(2020JM-600);陕西省教育厅科研项目(19JK0172);陕西省工业自动化重点实验室开放课题(SLGPT2019KF01-13)资助。

摘　　要：以大展弦比机翼为研究对象,基于Miner线性累积损伤理论并利用有限元分析方法计算了不同攻角下大展弦比机翼的疲劳寿命。首先,以N-S方程为基础,使用双向流-固耦合方法求解了巡航状态下机翼结构的位移,应力以及应变。其次,对机翼进行疲劳寿命分析,得到了机翼结构疲劳薄弱位置和不同攻角下的寿命情况。结果表明:大展弦比机翼疲劳薄弱位置易出现在翼尖前缘和翼根处,前缘的寿命从翼尖沿着机翼展向向翼根处增加;机翼的寿命情况与攻角的改变以及翼型参数密切相关,且在给定飞行工况下,一般会存在一个寿命最大攻角。Based on the Miner linear cumulative damage theory and the finite element analysis method, the fatigue life of the wing with high aspect ratio at different angles of attack was calculated.Firstly, based on the N-S equation, the displacement, stress and strain of the wing structure in cruise state are solved by using the bidirectional fluid-structure coupling method.Secondly, the fatigue life of the wing structure is analyzed, and the fatigue life of the wing structure at the weak position and different angles of attack is obtained.The results show that the fatigue weakness of the wing with high aspect ratio tends to occur at the leading edge and the wing root, and the life of the leading edge increases from the wing tip to the wing root along the wing span.The life of the wing is closely related to the change of Angle of attack and airfoil parameters, and there is generally a maximum life Angle of attack under a given flight condition.

关 键 词：大展弦比 有限元方法 双向流-固耦合 疲劳寿命 

分 类 号：V215.5[航空宇航科学与技术—航空宇航推进理论与工程]