变工况空间太阳电池翼在轨热变形分析

摘要/Abstract

摘要：

以空间飞行器太阳电池翼在轨运行期间热变形和热应力变化规律为对象，采用有限元软件I-DEAS建立电池翼热变形分析模型，针对电池翼满负荷和半负荷（变工况）工作状态进行在轨热结构耦合分析.计算中采用三明治夹心板理论将电池翼基板进行合理简化，得出电池翼等效力学参数.数值结果对比分析发现，电池翼厚度方向瞬态温差是导致电池翼发生热变形的主要原因，太阳电池翼在从阳光区转入阴影区时，电池翼温度变化最剧烈，厚度方向温差达到最大值，此时基板热变形量最大，半负荷（变工况）基板变形最大值明显大于满负荷基板变形最大值.

关键词: 太阳电池翼, 变工况, 等效力学参数, 热变形, 热应力

Abstract:

To investigate the thermal deformation and thermal stress of solar panels in orbit under two operating conditions (full-load and half-load), an analysis model of thermal deformation was developed using I-DEAS. The substrate of the solar panels, which was composed of several composite materials, could be reasonably simplified, and the sandwich plate theory was employed to derive the equivalent mechanical parameters of solar panels. The simulation results show that the thermal deformations of solar panels are mainly caused by the transient temperature difference along the thickness direction. Additionally, the temperature difference along the thickness direction of solar panels reaches the max value when solar panels enter the eclipse. The thermal deformation of the solar panels under halfload operating condition is higher than that under fullload operating condition.

Key words：

Key words: solar panels, variable operating conditions, equivalent mechanical parameters, thermal deformation, thermal stress

中图分类号:

TK 124

刘振宇，陈娅琪，吴慧英. 变工况空间太阳电池翼在轨热变形分析[J]. 上海交通大学学报（自然版）, 2013, 47(11): 1762-1766.

LIU Zhenyu,CHEN Yaqi,WU Huiying. Analysis of Thermal Deformation of Solar Panels in Orbit under Variable Working Conditions[J]. Journal of Shanghai Jiaotong University, 2013, 47(11): 1762-1766.

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