摘要
以某卫星的碳纤维/铝蜂窝太阳翼基板为对象,研究了碳纤维层合板和铝蜂窝芯层弹性常数和热膨胀系数的等效计算。分别采用等效参数和I-deas软件中的Laminate铺层模型等方法,分析了高温和低温状态下太阳翼基板的热变形,并对计算结果进行了比较,初步说明热变形分析是可行的。面板铺层材料参数对基板的热变形影响很大,在建立分析模型时不能将其等效为各向同性的均匀材料。
Based on a satellite s solar array substrate with CFRP/aluminum honeycomb sandwich,an equivalent calculation method of elastic constants and CTE（the coefficient of thermal expansion） of CFRP lamination（carbon fiber reinforced plastics） and aluminum honeycomb is proposed.By using equivalent method and Laminate of I-deas software respectively,thermal-elastic deformations of solar array substrate in hot and cold states were simulated,and the results which were consistent with each other indicate that thermal deformation analysis in this paper is feasible. The parameters of CFRP lamination affect the deformation greatly, so it shouldn＇t be considered as homogeneous and isotropic in modeling.
出处
《航天器工程》
2009年第4期44-48,共5页
Spacecraft Engineering
基金
国家重大科技专项工程
关键词
碳纤维/铝蜂窝
弹性常数
线胀系数
等效
太阳翼
热变形
CFRP/aluminum honeycomb
elastic constant
CTE
simulation
solar array
thermal deformation
