摘要
文章详细介绍了在真空高低温环境下一种伞状可展开天线的型面测量过程。首先依据天线在轨热分析结果定义典型温度工况,然后采用红外加热笼与天线自身主动热控相结合的方法实现天线各部件不同温度的控温要求,并采用摄影测量方法测量典型极端工况下的天线反射器型面热变形。结果表明,测量值与试验前热变形预示结果一致性较好,证明天线热变形分析模型有较高精度。依据在轨热分析温度场计算天线在轨热变形,得到天线在最大温度梯度工况下的型面变化(RMS)最大为0.19 mm。
This paper presents the thermal deformation testing of a deployable cable-mesh reflector by using the photogrammetry method with a thermal vacuum facility.The typical thermal conditions are adopted based on the on-orbit thermal analysis of antenna.The target temperatures on different parts of the antenna are reached by using an infrared heating device and the electric heater of the antenna itself at the same time.Testing results show that the RMS value of the reflector’s profile obtained by the thermal deformation modeling analysis agrees well with the measured data under typical thermal conditions,thus the model can be used for accurately predicting the on-orbit thermal deformation of the antenna.Based on that result and the on-orbit thermal environmental analysis results,the thermal deformation of the antenna is calculated for the on-orbit prediction.It is indicated that the maximum RMS value of the reflector is 0.19 mm under the maximum temperature difference condition during orbiting.
作者
王波
王朋朋
姚永田
师甜
李振伟
WANG Bo;WANG Pengpeng;YAO Yongtian;SHI Tian;LI Zhenwei(Xi’an Institute of Space Radio Technology,Xi’an 710100,China;Beijing Institute of Spacecraft Environment Engineering,Beijing 100094,China)
出处
《航天器环境工程》
2020年第3期269-274,共6页
Spacecraft Environment Engineering
基金
国家自然科学基金项目“大型天线高精度索网结构在轨稳定性关键影响因素和机理研究”(编号:U1537213)。
关键词
网状天线
天线反射面
热变形
摄影测量
热分析模型
在轨预示
cable-mesh antenna
antenna reflector
thermal deformation
photogrammetry
thermal analysis model
on-orbit prediction
