摘要
本文针对卫星主要结构材料铝质蜂窝板的非线性动力特性现象进行了振动试验及分析。根据谐波平衡法原理 ,对各级等效线性系统进行模态参数辨识 ,进一步基于Duffing假设 ,对非线性刚度、阻尼系数进行了识别 ,并基于多自由度非线性系统理论进行了仿真检验。本文的方法可以推广到整星的非线性结构的研究中去。
The phenomena in test for nonlinear dynamic behavior of aluminum honeycomb sandwich plate in satellite structure are analysed. According to Harmonic equilibrium, the modal parameters are identified to form an equivalent linear system. In term of Duffing hypothesis, the nonlinear stiffness and damping coefficient are identified and the simulating examination is conducted as a multi-freedom nonlinear system. The method can be extended to study the whole nonlinear satellite structure.
出处
《振动与冲击》
EI
CSCD
北大核心
2004年第1期8-11,共4页
Journal of Vibration and Shock
关键词
卫星
结构材料
铝蜂窝板
非线性振动
参数辨识
Duffing假设
模态参数
Aluminum
Computer simulation
Damping
Identification (control systems)
Nonlinear systems
Stiffness
Vibration measurement
