Discrete support technology has been widely used in the mirror support of space optical remote sensor due to its high lightweight and good environmental adaptability. In this paper, a six point discrete structure is designed to meet the high force and thermal stability requirements of a lightweight mirror with a diameter of Φ550mm in a high-resolution space camera. Through the analysis of the mirror stiffness and the adaptability under various environmental effects such as gravity, temperature, shrinkage of glue spots and overload, the rationality of the structural design is verified, and the indicators meet the application requirements of space optical remote sensor.
With the increasing function density of space optical remote sensor, the integration of visible and infrared space camera has become an important development direction. As the main vibration, the micro-vibration of refrigerator is the key to affect the imaging quality of optical remote sensor. In this paper, three commonly used micro-vibration test methods are compared, and the fixed-support force test method is used to test and analyze the micro-vibration performance of a pulse tube refrigerator under different power and use state. It is pointed out that the strategy of using compressor vibration isolation to mount satellite is more suitable for the Visible and infrared integrated space camera.
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