【摘要】 静轨光学载荷对地凝视成像无法通过指向偏转规避太阳直射，导致遮光罩及光学系统受到照射后温度会剧烈波动，引发相关结构及光学系统产生热形变，这些形变引起视轴指向偏移，显著降低观测目标的定位精度。为了解决上述问题，更准确地获取在轨载荷内形变引起的视轴指向变化，文章在卫星布局和载荷设计中实施了视轴热变形控制策略，并构建了载荷结构-光学热力形变仿真模型。通过地面真空环境模拟在轨极限温度工况，开展了视轴指向测量试验，获取了视轴热变形与温度分布的关联曲线。试验结果表明：在高温工况持续期间，相对于起始时刻，视轴最大漂移量≤0.16像元；在低温工况持续期间，视轴最大漂移量≤0.09像元；将对应的温度分布代入热变形仿真模型分析，测量结果与仿真分析结果相差0.08像元，吻合度较高。地面测量试验直观量化了热变形对视轴指向的影响，验证了热变形仿真模型的有效性与精度。后续将在轨遥测温度数据输入该仿真模型计算视轴指向偏转值，可为观测目标定位提供数据支持。更多还原

【Abstract】 Since optical payloads cannot avoid direct solar irradiation by deflecting their pointing directions,the thermal radiation from sunlight induces intense temperature fluctuations in the sunshields and optical systems,subsequently triggering thermal deformation for associated structures and even whole optical systems. These deformations cause deviations in the line of sight, significantly reducing the accuracy of target positioning. To address these problems and more accurately capture the line-of-sight pointing changes caused by in-orbit internal deformations, a thermal deformation control strategy is implemented in this study for the line of sight in satellite layout and payload design. Additionally, a structural-optical-thermal deformation simulation model is developed.By simulating extreme in-orbit temperature conditions in ground vacuum environment, line-of-sight pointing measurement tests are conducted to obtain the correlation curve between thermal deformation and temperature distribution. The test results show that during high-temperature conditions, the maximum line-of-sight drift is ≤0.16 pixels relative to the initial state; during low-temperature conditions, the maximum drift is ≤0.09 pixels.When the corresponding temperature distribution is applied into the simulation model, the difference between the simulation and measured results is only 0.08 pixels, showing high consistency. The ground measurement tests quantitatively reveal the impact of thermal deformation on the line of sight, validating the effectiveness and accuracy of the thermal deformation simulation model. Subsequent steps involve inputting in-orbit telemetry temperature data into this model to calculate line-of-sight deflection values, which can provide data support for target positioning.更多还原