基于空间太阳望远镜已有的光机热集成研究，结合其运载轨道修改、观测视场扩大等因素的调整，获取了深空太阳天文台磁场望远镜主反射镜温度分布的定量结果.采用光机热集成分析法，结合主反射镜前期的支承方案，获取了主反射镜在装夹状态下的热变形定量描述.采用抛物面多项式和Zernike多项式拟合，获取了主反射镜表面热变均方差值大于λ/40(λ=533 nm)的热控准确度，无法确保系统获取0.1″的高分辨率成像目标，验证了预研阶段热控方案的局限性.提出修改主反射镜正三角的机框式支撑为六点支撑的建议，为深空太阳天文台磁场望远镜热控准确度的提高、热控方案的优化提供技术参考.

Based on the thermal control system of Space solar telescope, the temperature of primary mirror in deep-space solar observatory was simulated under new orbit and larger view. Based on the theory of thermal-structural-optical integrated analysis, thermal deformation of the primary mirror under supported condition was calculated. And the deformed surface point of the primary mirror is fitted using parabolic polynomial and Zernike formula. The Root Mean Square(RMS) of deformed surface was greater than λ/40(λ=533 nm). It indicates the former thermal control system cannot meet its 0.1″ diffraction limit quality. Owing to the former thermal control system meets the demands of optical design difficultly, the supporting system of mirror is suggested to be adjusted in order to decrease thermal deformation. The integrated analysis of primary mirror is useful for optimizing the thermal control system and supporting system of Deep-space solar observatory.