Although the performance of space cameras has largely improved, the micro vibration from flywheel disturbances still significantly affects the image quality of these cameras. This study adopted a passive isolation method to reduce the negative effect of flywheel disturbance on image quality. A metal-rubber shock absorber was designed and installed in a real satellite. A finite element model of an entire satellite was constructed, and a transient analysis was conducted afterward. The change in the modulate transfer function was detected using ray tracing and optical transfer function formulas. Experiments based on real products were performed to validate the influence of the metal-rubber shock absorber. The experimental results confirmed the simulation results by showing that the negative effects of flywheel disturbance on the image quality of space cameras can be diminished significantly using the vibration isolation method.

为了保证口径为Φ320 mm的反射镜粘胶前后面形精度变化较小，同时组件的动静态刚度满足使用要求，对空间相机反射镜的胶结技术进行了研究。首先，得出了六条均布粘胶和沿芯轴外环全粘胶两种粘胶方案的具体参数，并采用有限元的方法对两种方案进行了静刚度分析与光学性能分析；其次，在反射镜裸镜面形为0.030λ(λ=632.8)时，分别检测了采用这两种粘胶方案装配后反射镜的面形精度；最后，对反射镜组件进行了振动试验。分析与试验表明：采用六条均布粘胶方案装配后，进行振动试验组件完好无损，测得一阶频率为144.194 Hz，与有限元分析相对误差为1.23%，动静态刚度满足需求，同时对比外环全粘胶反射镜面形精度提高了13.5%。结果显示六条粘胶方案更适用于Φ320 mm反射镜组件的粘结。

随着光学遥感卫星在轨成像质量要求的提高，为了满足相机环境温度的要求，往往需要大量热控资源。由于微小卫星资源紧张，所以综合分析相机各组件的热敏感性，合理分配热控资源，改善成像质量，具有重要的实用意义。介绍了光机热集成分析的研究现状和方法。建立了空间视频相机的有限元模型，分析了各组件在各温度载荷下的热变形对光学系统成像质量的影响。最后对比分析不同工况下的分析结果，得到了各组件在各温度载荷下对光学系统成像质量影响的强弱关系。结果表明：对影响最大的6 种工况的温度载荷进行严格控制可使成像质量达到要求，从而为该视频相机的热控设计提供了参考。