Vibration isolation device of satellite control moment gyro

Abstract

The invention provides a vibration isolation device of a satellite control moment gyro, which is used for vibration isolation of the control moment gyro and comprises vibration isolator assemblies and a cellular plate, wherein the vibration isolator assemblies are disposed on the cellular plate; the vibration isolator assembly comprises a sealing cover, a connecting rod, a vibration isolator, a damping layer, a switch-over part and a base, the connecting rod, the vibration isolator, the damping layer, the switch-over part and the base are connected in sequence; the sealing cover is disposed on the outer side of the connecting rod, the vibration isolator and the damping layer; the base is connected to the cellular plate; and the connecting rod is used to connect the control moment gyro. Quantity of the vibration isolator assemblies is four; the four vibration isolator assemblies are distributed in a rectangular manner; and the two adjacent vibration isolator assemblies are distributed symmetrically. The vibration isolation device of the satellite control moment gyro provided by the invention is rational in structural design, can significantly reduce interference of micro-vibration responses caused by the control moment gyro during in-track running to a sensitive load, and ensures stability, reliability and safety of the high-precision sensitive load on a satellite during the in-track running.

Description

technical field [0001] The invention relates to a vibration isolation device, in particular to a vibration isolation device for a satellite control moment gyroscope. Background technique [0002] In order to achieve the purpose of on-orbit operation and fast maneuvering of satellites, the control moment gyroscope (CMG) has been applied to the development of satellite models as an actuator. Similar to the flywheel, due to the static and dynamic imbalance of the CMG rotor, the difficulty of the bearing process, and other processing errors, the CMG becomes the main factor affecting the performance index of the satellite's sensitive load. Therefore, it is necessary to suppress the vibration generated by CMG to provide an ultra-quiet environment for satellite sensitive loads. [0003] At present, there is no vibration isolation device for controlling the vibration of a control moment gyroscope (CMG). For the above defects, if a vibration isolation device for a satellite control ...

AI Technical Summary

Problems solved by technology

According to the literature search of the prior art, it is found that there is no vibration isolation device for satellite control moment gyroscope at present. The design constraints of the vibration isolation device mainly include four aspects: one is to reduce the vibration transmitted to the honeycomb panel when the satellite is in orbit. The second is to realize the lightweight design of the structure and the optimal design of the envelope size to save the entire star resources; the third is that the vibration isolation device cannot affect the control pointing accuracy of the CMG; the fourth is that the vibration isolation device does not affect the output of the CMG. Useful torque for orbit changes and quick maneuvers

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