为保证航空相机光学系统的有效性和较高的成像质量，根据相机的热环境和结构特点进行了热控设计。采用热隔离等被动热控措施延长系统的热时间常数，降低光学系统对外部热环境变化的灵敏度。建立了镜头和窗口组件的传热模型和热阻网络模型，并对其在极端工况下的最大漏热率进行了分析计算，得到保持光学系统恒温所需的加热功率，根据计算结果设计了加热回路和分配加热功率。针对热控设计和航空相机的工况进行了稳态和瞬态仿真分析，对加热功率进行了优化。镜头和窗口的稳态温度分布均在 (20±1)℃范围内，表明漏热补偿效果较好；瞬态分析结果表明，在飞行拍摄的过程中，温控系统将光学系统的温度控制在 17.5℃~20.5℃范围内，满足热控指标要求，为提高光学系统的可靠性和热控设计优化提供了理论依据。

To assure the effectiveness of the optical system in an aerial camera and high image quality, thermal design was taken according to the thermal environment and the structure characteristic of the camera. Passive control methods such as thermal insulation were taken to overreach the thermal time constant and to reduce the sensitivity of the optical system to the external thermal environment. Heat transfer model and thermal resistant network model of the lens and the window unit were created, and the highest thermal leakages under extreme working conditions were analyzed and calculated. The heating power for maintaining the optical system temperature was obtained. According to the calculating results, the heating loops and heating power were designed. Steady-state and transient simulation was taken based on the thermal control methods and the work condition, and the heating powers were optimized. The steady-state temperature distributions of the lens and optical window were in the range of (20±1)℃, which indicated that the heat dissipation was well compensated. The transient results showed that the temperature of optical system was between 17.5℃~20.5℃, which met the thermal control index. Through the analysis, a theoretical warrant for reliability of optical system and optimization of thermal design was provided.