大型可展开天线与卫星的热致耦合动力学分析

杨癸庚;朱敏波;连培园;高峰;宗亚雳

振动与冲击 ›› 2014, Vol. 33 ›› Issue (24) : 173-178.

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PDF(1775 KB)
振动与冲击 ›› 2014, Vol. 33 ›› Issue (24) : 173-178.
论文

大型可展开天线与卫星的热致耦合动力学分析

  • 杨癸庚,朱敏波,连培园,高峰,宗亚雳
作者信息 +

Thermally Induced Coupling-dynamic Analysis of a Deployable Satellite Antenna System

  • Yang Guigeng, Zhu Minbo,Lian Peiyuan,Gao Feng,Zong Yali
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摘要

本文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;本文的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。

Abstract

The coupling-vibration of spacecraft with large ring-shaped deployable antenna induced by temperature variations during the spacecraft entering and leaving the Earth’s shadow was numercially analysized. The transient temperature field of large deployable antenna was solved using the finite element method, and a rigid-flexible coupling dynamic model was established for the coupling-vibration analysis. The results show that temperature gradient of the antenna itself is mainly between the light side and the backlight side, and with which the thermal response characteristic time of antenna can be estimated. Obvious thermally induced coupling-vibration of antenna structure and the satellite attitude can be observed. The method present in this paper can reasonably be used to predict the thermally induced coupling-dynamic of deployable satellite antenna system.

关键词

可展开天线 / 热响应特征时间 / 卫星-天线刚柔耦合 / 热致耦合动力学

Key words

deployable antenna / thermal response characteristic time / satellite-antenna rigid-flexible coupling / thermally induced coupling-dynamic

引用本文

导出引用
杨癸庚;朱敏波;连培园;高峰;宗亚雳. 大型可展开天线与卫星的热致耦合动力学分析[J]. 振动与冲击, 2014, 33(24): 173-178
Yang Guigeng;Zhu Minbo;Lian Peiyuan;Gao Feng;Zong Yali. Thermally Induced Coupling-dynamic Analysis of a Deployable Satellite Antenna System[J]. Journal of Vibration and Shock, 2014, 33(24): 173-178

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