摘要
结合航天工程中卫星结构普遍进行的振动台振动试验,提出了一种基于基础激励试验数据的设计参数型有限元模型修正方法,用数值差分代替灵敏度分析,提高了计算效率,整个修正步骤更加适合工程应用。然后利用该算法对某型号卫星整星结构进行了修正,并提出了两步修正策略。修正后,有限元模型的加速度响应计算结果更加接近于试验测量值,均方根误差也比修正前有了不同程度的降低,证实了该算法对卫星结构的修正是行之有效的。
A finite element model updating method for design parameters based on the basic excitation vibration test data is presented in combined with the basic excitation test of satellite structures generally carried out in the practice of aerospace engineering. The difference method instead of sensitivity analysis is used to improve computational efficiency, and will be convenient for engineering applications. And then, the FE model for a satellite structure is updated according to the basic excitation response data, and a two-step model updating strategy is put forward. After the model is updated, the correlation between the analyzed vibration response and experiment result of the finite element model is improved a lot, which confirmed that the model updating algorithm is effective for complex satellite structure.
出处
《宇航学报》
EI
CAS
CSCD
北大核心
2013年第9期1187-1194,共8页
Journal of Astronautics
基金
国家自然科学基金(11172078)
国防973子项(613133)
关键词
有限元
模型修正
基础激励
响应数据
卫星结构
Finite element
Model updating
Basic excitation
Response result
Satellite structure
