航天器在轨全周期热变形分析方法

摘要

提出一种适应于在轨全周期热变形的分析方法,采用基于热传导算法进行“热分析模型-结构分析模型”全周期温度场映射,利用数学拟合算法开展对各类结果数据的分析,通过相关程序实现全周期多工况温度场映射、计算、数据分析的自动化.对某遥感卫星进行全周期热变形分析,结果表明:全周期温度场映射时间由天缩短至小时量级,温度场映射精度可控制在1％以内,相对于以往基于极端工况的热变形分析方法,可显著地提升分析精度与验证覆盖性,获得在轨热变形量级、全周期变化规律.文章的研究结果可为航天器热稳定设计提供参考.%Thermal deformation analysis method of in orbit whole cycle is presented.Mapping of thermal model to mechanical model during the whole cycle is executed based on method of heat conduction.Through mathematic fitting algorithm,analysis data are processed and analyzed,and process is automated by procedure.Thermal deformation analysis of whole cycle is analyzed for a remote sensing satellite.According to the analysis results,time cost of mapping is reduced from several days in the past to several hours nowadays.Besides,simulating precision is improved significantly,mapping error is less than 1 ％,and results can coverage cases of the whole cycle compared with the thermal deformation analysis method based on extreme load case.Dimension of thermal deformation and change rule of deformation are obtained from the calculating results meanwhile.All of the achievements are of great importance to the design of thermal stability for spacecraft.