摘要
基于统计能量分析方法计算高超声速飞行器铝合金壁板高频声振响应,分析了在不同内损耗因子情况下壁板均方根应力和危险点响应集中因子。进而采用频域疲劳寿命方法,结合零阶矩应力谱法计算了壁板的高频疲劳寿命,研究了在不同内损耗因子情况下铝合金壁板高频疲劳寿命的变化规律。研究结果表明:随着内损耗因子的增大,壁板的均方响应逐渐减小,但响应集中因子逐渐增大,最终导致壁板疲劳寿命出现先变长后缩短的变化趋势;随着内损耗因子的增大,高频段应力响应对疲劳寿命的贡献量明显增大。
The high-frequency vibro-acoustic response of hypersonic aircraft aluminum alloy panel is calculated by statistic energy analysis.The RMS stress and critical point response concentration factor are analyzed under different internal loss factors.Then,the high-frequency fatigue life of the panel is researched by frequency-domain fatigue life method combined with zero moment stress spectrum method.The variation of high-frequency fatigue life of aluminum alloy panel under different internal loss factors is analyzed.The research results show that,with the increase of the internal loss factor,the mean square response of the panel will gradually decrease,but the response concentration factor will gradually increase.Ultimately,the trend of the fatigue life of the panel increases firstly and then decreases.It is also found that with the increase of the internal loss factor,the contribution of the high frequency stress response to the fatigue life is significantly increased.
作者
王晨
燕群
陈海波
秦强
Wang Chen;Yan Qun;Chen Haibo;Qin Qiang(Aircraft Strength Research Institute of China,710065,Xi’an,China;Department of Modern Mechanics,University of Science and Technology of China,230027,Hefei,China)
出处
《应用力学学报》
CAS
CSCD
北大核心
2019年第4期753-758,991,共7页
Chinese Journal of Applied Mechanics
基金
航空科学基金(2016AZ23003)
关键词
高频声振耦合
统计能量分析
内损耗因子
零阶矩应力谱
疲劳寿命
high-frequency structural-acoustic coupling
statistical energy analysis
internal loss factor
zero moment stress spectrum method
fatigue life
