大型可展开天线与卫星的热致耦合动力学分析

Thermal induced coupling-dynamic analysis of a deployable satellite antenna system

以带有大型环形可展开天线的航天器为研究对象,采用有限元法,对大型可展开天线进行了在轨进出阴影区的瞬态温度求解;并基于卫星-天线刚柔耦合动力学模型,将时变温度场等效为时变热载荷加载到天线上,对整星系统的热致耦合动力学响应进行了数值模拟。结果表明,天线进出阴影期间,自身温度梯度主要存在于迎光侧与背光侧之间,并基于此可估算出天线的热响应特征时间;时变热载荷会导致天线结构和卫星姿态发生明显的振动响应,天线结构振动响应主要集中在第一、二阶固有模态上,卫星则会发生低频姿态振荡运动;该方法可以合理地预测大型可展开天线系统的热致耦合动力学响应。

The coupling-vibration of a spacecraft with a large ring-shaped deployable antenna induced by temperature variations during the spacecraft entering and leaving the Earth＆#39;s shadow was numercially analyzed.The transient temperature field of the large deployable antenna was solved using the finite element method,and a rigid-flexible coupling dynamic model was established for the coupling-vibration analysis of a deployable satellite antenna system.The results showed that temperature gradient of the antenna itself exists mainly between the light side and the backlight side, and with it the thermal response characteristic time of antenna was estimated.The obvious thermal induced coupling-vibration of the antenna structure and the satellite attitude could be observed.The method presented here could be used to reasonably predict the thermal induced coupling-dynamic responses of a deployable satellite antenna system.