星敏感器随机振动抑制方法设计与验证

To solve the problem of excessive random vibration response of commercial satellite star sensors under lightweight and miniaturization constraints, based on a certain type of satellite being developed, an isolator design method for restraining random vibration response is proposed. It first analyzes the vibration response using the finite element method according to the configuration, layout design, and local installation method for the star sensor of a type of satellite, concluding that the local random vibration response of a star sensor design without vibration isolation is too large. Then, a vibration suppression method based on a rubber isolator is proposed based on the amplitude-frequency characteristic of random vibration, actual space, and interface for star sensor installation. Its effectiveness is analyzed using the amplitude-frequency method. Finally, the result of the vibration test for the whole satellite shows that the isolator can suppress the root mean square of random vibration by 80%, and the amplitude of amplified sinusoidal vibration can still meet the mechanical requirement for a star sensor. The maximum pointing deviation before and after vibration is about 0. 021 67°. At present, the satellite has been successfully applied in orbit, the star sensor works properly, and the effectiveness of the vibration suppression method based on a rubber isolator is thereby verified, providing a technical reference for the engineering practice of other types of spacecraft.