CAJ | 학술논문

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。
이대유대형배형가전개천선적항천기위연구대상，채용유한원법，대대형가전개천선진행료재궤진출음영구적순태온도구해；병기우위성－천선강유우합동역학모형，장시변온도장등효위시변열재하가재도천선상，대정성계통적열치우합동역학향응진행료수치모의。결과표명，천선진출음영기간，자신온도제도주요존재우영광측여배광측지간，병기우차가고산출천선적열향응특정시간；시변열재하회도치천선결구화위성자태발생명현적진동향응，천선결구진동향응주요집중재제일、이계고유모태상，위성칙회발생저빈자태진탕운동；해방법가이합리지예측대형가전개천선계통적열치우합동역학향응。
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'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.