新一代地球同步轨道气象卫星结构热变形分析  

Thermal Structure Distortion for Some New GEO Meteorological Satellite

作　　者：方宝东 李应典[1] 张建刚[1] 

机构地区：[1]上海卫星工程研究所,上海200240

出　　处：《上海航天》2006年第6期50-53,共4页Aerospace Shanghai

摘　　要：根据用MSC.PATRAN软件建立的整星有限元模型,对某地球同步轨道(GEO)气象卫星的结构热变形进行了计算。分析建模中铝蜂窝夹芯板线膨胀系数和未考虑板厚时热载荷场的影响。给出了高/低温、铝合金/碳纤维蒙皮四种不同工况的整星最大变形和有效载荷安装板对地变形角,并由此得到了整星和有效载荷板Y向的热变形图。分析结果表明,结合相关型号热真空试验数据,该法可有效地准确获得整星的热变形,对工程设计具有一定的参考价值。The structure thermal distortion for some GEO meteorological satellite was computed according to the finite element satellite model founded by MSC, PATRAN software in this paper. The effects of linear expansive coefficient for aluminum honeycomb structure plane and thermal load field when plate thickness not considered were analyzed. The maximum distortion and distortion angle between payload mounting plate and ground under 4 kinds of operational modes with high/low temperature and aluminum/carbon coat plane were acquired, and so were the thermal distortion pictures of the satellite and the Y-direction. The research results showed that this method could gain the thermal distortion of the satellite combined with the data of relative thermal vacuum test of other simillar satellite effectively and correctly, which was valuable in engineering design.

关 键 词：地球同步轨道气象卫星 热变形 蜂窝板 热膨胀系数 热载荷 有限元模型 

分 类 号：V414.5[航空宇航科学与技术—航空宇航推进理论与工程]