摘要
星载抛物面天线反射器在周期性的冷热辐射作用下,产生不均匀的温度分布,过大的热变形严重影响卫星通信质量;采用一种8节点超参数壳单元,通过每个节点3个温度自由度表示厚度方向上温度的非线性变化,建立了单元内温度插值函数,基于Galerkin法推导出受太空冷热辐射作用的壳体结构瞬态热分析的有限元公式;运用几何解析法分析了抛物面壳体的自遮挡.对某静止轨道卫星抛物面天线进行稳态分析,与FDM结果比较表明该方法具有良好的计算精度;在不考虑地球辐射热流作用的一个运行周期的瞬态分析中,该反射器上瞬间温差达200 K,在日照区内温度变化达250 K.
When parabolic antenna reflector on orbit is under the periodic outgoing and incoming radia- ting flux environment, non-homogeneous temperature distribution will be induced. Too large thermal de- formation of reflector will produce bad effect on the satellite communication. An 8-nodes shell element with 3 temperature DOFs is applied to analyze this thermal effect in the paper. The temperature function in one element is built and the finite element equations are derived based on Galerkin method,which are suit for transient thermal analysis of shell structures under space environment. Self-occlusion of parabolic shell is analyzed with analytic geometry. For a reflector on geosynchronous orbit,the steady-state results from this method are compared with these from FDM. it follows from the analysis that the precision of this method is high. For transient analysis,temperature difference of reflector reaches 200 K when the earth radiating flux is ignored,and even up to 250 K when it is in sunlight.
出处
《固体力学学报》
CAS
CSCD
北大核心
2008年第3期272-276,共5页
Chinese Journal of Solid Mechanics
基金
国家自然科学基金项目(69982009)资助
关键词
有限元
热分析
瞬态
天线
反射器
finite element, thermal analysis, transient, antenna, reflector
