摘要
由于卫星表面热控涂层在空间恶劣环境下发生性能退化,导致实际参数与设计参数发生偏差,而重复计算卫星温度场和红外辐射耗时非常大。本文首先根据地面模拟实验数据建立了热控涂层性能退化模型,然后在卫星温度场和表面红外辐射计算模型的基础上,推导了卫星表面节点温度灵敏度和红外辐射灵敏度的计算公式。结合具体的卫星模型和轨道参数,求解了卫星表面节点温度灵敏度和红外辐射灵敏度。结果表明,热控涂层性能退化造成的卫星红外辐射特性变化,可直接利用卫星红外辐射灵敏度来分析,避免了卫星温度场和空间红外辐射的重复计算。
Because of the degradation of the thermal control coatings in harsh space environment,the error between the real parameters and the design parameter must happen.However,calculating the satellite＇s temperature and infrared radiation repeatedly was time-consuming.Firstly,based on the simulation experimental data,the degradation model of the thermal control coatings was established.Then,the temperature sensitivity and infrared radiation sensitivity formulae of the surface node of the satellite were derived,according to the calculation model of the temperature and infrared radiation.Combined with specific satellite＇s parameter,the temperature sensitivity and infrared radiation sensitivity were calculated.The result shows that the change of infrared radiation caused by the degradation of the thermal control can be analyzed by using the infrared radiation sensitivity directly to avoid the repeat calculation of the satellite＇s temperature and infrared radiation.
出处
《光电工程》
CAS
CSCD
北大核心
2010年第7期30-35,共6页
Opto-Electronic Engineering
基金
安徽省红外与低温等离子体重点实验室基金资助项目(2007A012012F)
关键词
卫星
热控涂层
温度灵敏度
红外辐射灵敏度
satellite
thermal control coatings
temperature sensitivity
infrared radiation sensitivity
