摘要
为满足卫星天线板的在轨热变形测量要求,需要建立精确有限元模型模拟天线板热变形过程。蜂窝夹层板作为天线板主体结构,在有限元建模过程中通常需要对其进行简化处理,导致有限元计算结果与实验测量值之间存在差异。针对上述问题,进行了高温环境下天线板结构的热变形实验,得到温度场分布与热变形位移矩阵。通过对温度场拟合得到有限元模型热载荷。在此基础上,提出了利用天线板有限元模型与实验模型面外位移测量矩阵的均方根误差作为修正目标,基于多岛遗传算法的有限元模型修正方法,对模型材料参数与边界条件进行修正。修正后有限元模型的预测精度得到了明显提高。
In order to meet the requirements for in-orbit thermal deformation measurements of satellite antenna panels,an accurate finite element model is required to simulate the thermal deformation process of the antenna panels.As the main structure of the antenna panel,the honeycomb sandwich panel usually needs to be simplified in the finite element modelling process,resulting in discrepancies between the finite element calculation results and the experimental measurement values.To address the above problem,thermal deformation experiments of the antenna plate structure under high temperature environment are carried out to obtain the temperature field distribution and thermal deformation displacement matrix.The finite element model thermal load is obtained by fitting the temperature field to it.On this basis,a method of finite element model updating based on the multi-island genetic algorithm is proposed to modify the model material parameters and boundary conditions using the root mean square error of the out-of-plane displacement measurement matrix of the antenna plate finite element model and the experimental model as the correction target.The prediction accuracy of the modified finite element model is significantly improved.
作者
杨何
王晨
沈星
黄天翔
操卫忠
黄欣婷
汪奕
袁慎芳
YANG He;WANG Chen;SHEN Xing;HUANG Tianxiang;CAO Weizhong;HUANG Xinting;WANG Yi;YUAN Shenfang(State Key Laboratory of Mechanics and Control for Aerospace Structures,Nanjing University of Aeronautics&Astronautics,Nanjing 210016,China;Nanjing Research Institute of Electronics Technology,Nanjing 210008,China)
出处
《南京航空航天大学学报》
CAS
CSCD
北大核心
2023年第6期1118-1125,共8页
Journal of Nanjing University of Aeronautics & Astronautics
基金
国家自然科学基金(51921003,52102475)。
关键词
蜂窝夹层板
热变形
有限元方法
模型修正
卫星天线
honeycomb sandwich plate
thermal deformation
finite element method
model updating
satellite antenna
