飞机典型金属材料振动疲劳历程中模态阻尼比获取方法研究  

On the method of modal damping ratio acquisition of aviation typical metallic material in vibration fatigue process

作　　者：王建强[1] 周苏枫[1] 马君峰[1] 邵闯[1] WANG Jian-qiang, ZHOU Su-feng, MA Jun-feng, SHAO Chuang(Laboratory of Aeronautical Acoustics and Dynamics, Aircraft Strength Research Institute of China, Xi＇an 710065, Chin)

机构地区：[1]中国飞机强度研究所航空声学与振动强度航空科技重点实验室

出　　处：《实验力学》2018年第2期318-324,共7页Journal of Experimental Mechanics

摘　　要：结构模态阻尼比是影响振动疲劳特性的主要因素，获取模态阻尼比对于结构振动疲劳的分析和仿真计算有重要作用，对于揭示金属材料振动疲劳损伤形成机理有直接意义。本文选取典型航空金属材料2024-O铝合金，进行了大量的元件级振动疲劳试验及仿真分析计算，并提出了一种基于有限元分析计算的振动疲劳历程中结构模态阻尼比的获取方法，适合于元件级结构振动疲劳过程中模态阻尼比变化规律的获取。研究结果表明：本文方法可以在不中断振动疲劳试验的情况下，得到较精确的振动疲劳历程中的模态阻尼比，从而为进一步揭示金属材料振动疲劳损伤形成机理提供了良好的基础。Modal damping ratio is the main factor affecting vibration fatigue characteristics, so modal damping ratio acquisition plays an important role for structure vibration fatigue analysis and simulation calculation, therefore, it is of direct significance to reveal vibration fatigue damage formation mechanism of metallic material. Selecting 2024-0 aluminum alloy as typical aviation metallic material, a large number of component-level vibration fatigue experiments and simulation calculations were conducted. Then, based on finite element analysis, a method for obtaining modal damping ratio in vibration fatigue process is proposed in this paper, which is suitable for element level structure modal damping ratio acquisition. Study results show that this method can obtain accurate modal damping ratio without interrupting the vibration fatigue experiment, thereby, has laid the foundation for revealing vibration fatigue damage formation mechanism of metallic material.

关 键 词：振动疲劳 模态阻尼比 金属材料 有限元分析 

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]