航天器环境工程2023，Vol.40Issue(6)：581-586,6.DOI:10.12126/see.2023054
高精度光学载荷安装平台热控设计及试验验证
Thermal control design and test verification of high-precision optical payload assembly platform
摘要
Abstract
The three main optical payloads of a scientific satellite need to achieve parallel view with the sun,which requires the parallelism deviation of their optical axes to be less than 30".Considering the influence from thermal elastic deformation,the temperature of the optical payload assembly platform needs to be controlled at(22±5)℃.However,the payload assembly platform is large in size(1.6 m×1.6 m×0.8 m)and is located outside the cabin,resulting in great differences of heat fluxes in various directions and difficulties in temperature uniformity control.Therefore,combined thermal control measures of active PI closed-loop heating together with passive multi-layer insulation were implemented on the platform.Under the proposed thermal control scheme,software simulation shows that the temperature of the payload mounting plate and the support rod can be controlled at(22±3)℃.Satellite vacuum thermal test indicates that the temperature of the payload mounting plate and the support rod can be controlled at(22±2)℃ and(22±3)℃,respectively.All the above have verified that the proposed thermal control scheme is feasible and effective.关键词
光学载荷安装平台/光轴平行度/热控设计/试验验证/PI闭环加热Key words
optical payload assembly platform/parallelism of optical axis/thermal control design/test verification/PI closed-loop heating分类
能源科技引用本文复制引用
唐宗斌,王建平,廖星..高精度光学载荷安装平台热控设计及试验验证[J].航天器环境工程,2023,40(6):581-586,6.基金项目
中国科学院空间科学先导专项二期"先进天基太阳天文台卫星"项目(编号:XDA15320100) （编号:XDA15320100）
