摘要
卫星的太阳电池翼在轨的温度状况对其性能和可靠性有着重要的影响。相比于刚性太阳翼,柔性太阳翼有着质量轻,综合性能好,结构也较简单等优点。在考虑了地球红外辐射,地球的太阳反照,太阳辐射加热的前提下,以柔性太阳翼为研究对象,利用I-DEAS TMG建立2种太阳电池有限元模型,分析了柔性太阳翼厚度方向的温差,以及不同太阳高度和工作状态对其在轨温度场的影响。分析结果表明,当飞行器绕轨道飞行进入第2个周期后,太阳电池温度场呈现周期变化特性;柔性太阳翼正反两面温度几乎一致,不会因为厚度方向的温差引起热应力;0°太阳高度角分流状态太阳电池温度最高,温度变化最为剧烈;66°太阳高度角工作状态,太阳电池的温度最低,温度变化最为缓慢;电池板面内温差极小。
The temperature of the satellite solar array has a big impact on its performance and reliability. Compared with the rigid solar arrays, the flexible solar arrays have an advantage of light structure and better overall performance. To investigate the temperature of the flexible solar array in orbit under different solar altitudes and operating conditions, thermal models were established by FEM analysis software I-DEAS TMG. The analysis takes into account of all the heat sources： the terrestrial infrared radiation, the earth＇s sun reflection, and solar radiation. The results indicate that from the second period, the temperature changes periodically, difference between the two sides of the flexible solar arrays is small enough to ignore and when the solar attitude is 0 degree, the solar array gets the highest temperature during light district in non-operating state. When the solar attitude is 66 degree, the solar array has the lowest temperature during the light district in full operating state. In both conditions, the temperature difference within the solar plane is very small.
出处
《飞机设计》
2014年第4期22-26,共5页
Aircraft Design
关键词
柔性太阳翼
太阳高度
工作状态
温度
flexible solar array
solar altitude
operating conditions
temperature
