摘要
基于虚拟激励法和分块迭代耦合方法提出一种高温作用下飞行器舱体的振动特性数值分析方法,研究不同温度条件对飞行器舱体振动特性的影响.采用包含防热层、隔热层以及金属框架的多层复合结构建立符合真实情况的飞行器舱体有限元数值模型.结构振动特性分析时考虑了非平稳激励输入条件以及瞬态温度变化情况.计算过程中利用虚拟激励法进行了动力学计算的简化,大大提高了计算效率.计算结果表明,不论在低频区还是高频区,温度的变化都显著影响飞行器舱体结构的振动特性.本文的计算方法可广泛应用于飞行器结构在飞行过程中受到高温和随机振动联合作用时的动力学特性分析.
A numerical method of dynamic analysis of the aircraft cabin related to the effects of high temperature is proposed based on Pseudo Excitation Method（PEM） and the block-iterative coupling algorithm. The influence of the different temperature on dynamic characteristics of the aircraft cabin is investigated. An actual aircraft cabin composite structure including a heat resistant layer,an adiabatic layer and metal frameworks is modeled with the finite element method. Non-stationary excitation conditions and transient temperature change are both included for structure dynamic analysis. The usage of PEM simplifies the dynamic computation and improves the computational efficiency obviously. It can be concluded from the computed results that the change of the temperature influences dynamic characteristics of the aircraft cabin significantly in both the low frequency range and the high frequency range. The numerical method proposed in this paper can be widely applied for dynamic analysis of the aircraft structures suffering from the coupling effects of high temperature and random vibration.
出处
《应用基础与工程科学学报》
EI
CSCD
北大核心
2017年第6期1170-1182,共13页
Journal of Basic Science and Engineering
基金
中央高校基本科研业务费资助项目(DUT162D(G)03&DUT16RC(4)29)
关键词
飞行器舱体
振动特性分析
瞬态高温作用
虚拟激励法
aircraft cabin
analysis of dynamic characteristics
effect of transient temperature
pseudo excitation method
