摘要
基于结构振动疲劳寿命分析方法,采用有限元分析软件对某型导弹吊挂在挂飞过程中承受随机振动载荷产生的疲劳破坏问题进行了研究。利用有限元软件对全弹的前3阶弯曲模态进行了分析,并和地面试验数据进行对比发现误差在15%以内,表明所建立的模型符合工程要求;其次,基于振动疲劳寿命频域法中的Dirlik雨流分布模型,采用Dirlik经验公式对导弹吊挂在耐久振动和机动抖振下的疲劳损伤和疲劳寿命进行了研究和估算。结果表明:导弹吊挂在耐久振动和机动抖振下均满足飞行寿命需求,且在机动抖振下的寿命比在耐久抖振的寿命要短。
In this paper, the fatigue damage problem was investigated by using finite element analysis software based on the vibration fatigue life prediction method of structures, and the fatigue life of a certain missile hanging in the process of hanging aviation was analyzed under the random vibration load. Firstly, the first three order bending vibration modes of the whole missile were analyzed by using finite element analysis software and the error percentage was less than 15% by contrast with the ground experimental data. The results show that the established model is consistent with the requirements of the project. Secondly, the fatigue damage and fatigue life were researched and predicted in durability vibration and dithering vibration by using Dirlik experiential expressions based on the Dirlik rain-flow distributing model in the frequency domain method of vibration fatigue life prediction. The results show that the missile hanging is satisfied with the aviation life requirement both in durability vibration and dithering vibra- tion, and the fatigue life in dithering vibration is less than in durability vibration. For the follow-up design work, the result of simulation analysis has a certain guiding significance.
出处
《机械科学与技术》
CSCD
北大核心
2013年第11期1675-1679,共5页
Mechanical Science and Technology for Aerospace Engineering
关键词
吊挂
随机振动
有限元分析
疲劳寿命估算
air to air missiles
bending（deformation）
computer software
experiments
fatigue damage
fatigue of materials
finite element method
frequency domain analysis
functions
mathematical models
missiles
Monte Carlo methods
stresses
power spoctral density
vibrations （mechanical）
missile hanging
random vibration
finite element analysis
fatigue life prediction
