摘要
针对具有轻质柔性、局部抗弯刚度低、几何非线性、高阻尼等特点的新一代大型空间薄膜结构主要支撑部件—薄膜充气环动态特性,建立柔性结构动态测试系统。用改进的激励方式,得到薄膜充气环面内、外振动频响函数。通过复模态指示函数识别极点数目,用多项式拟合识别出结构固有频率、阻尼比、振型。分析不同充气压力下结构动态特性变化规律,并对薄膜充气结构动态特性测试相关问题进行讨论,实验结果为空间薄膜结构有限元模型有效性验证提供依据。
Thin film inflatable toruses are main supporting structures for next generation of large space membrane spacecrafts, they have intrinsic properties of high flexibility, low bending stiffness, nonlinear geometrical deformation and strong damping et al. Here, a dynamic measurement system was assembled to investigate the dynamic properties of a thin film inflatable torus. Due to traditional hammer excitation with local deformation, the excitation method was modified. In plane and out of plane frequency response functions of the thin film inflatable torus were obtained, the pole number was identified with a complex modal index, and the structural natural frequencies, damping ratios and modal shapes were identified through a polynomial fitting process. The dynamic properties of the structure under different internal gas pressures were analyzed and the problems related to the dynamic measurement were discussed. It was shown that the test results can be used for validation of finite element models of space thin film structures.
出处
《振动与冲击》
EI
CSCD
北大核心
2013年第7期11-16,共6页
Journal of Vibration and Shock
基金
国家自然科学基金资助项目(10902032)
教育部"新世纪优秀人才支持计划"(NCET-08-0150)
种环境复合材料技术国防科技重点试验室开放基金项目(HIT.KLOF.2009035)
关键词
空间薄膜结构
动态测试
模态分析
space membrane structures
dynamic measurement
modal analysis
作者简介
余建新男，博士生，1984年生
通讯作者谭惠丰男，教授，1969年生
