Frequency regulation implementing method for deployable flexible appendages of satellites

Abstract

The invention provides a frequency regulation implementing method for deployable flexible appendages of satellites. An onboard computer controls a controller of a frequency regulation module, the controller of the frequency regulation module supplies power for a drive assembly and performs drive control, torque and rotation speed generated by the drive assembly are transmitted through a self-locking assembly and the drive assembly drives a reel to rotate to tension or release a rope, so that the purpose of frequency regulation is achieved. The controller of the frequency regulation module monitors location of the reel through a position sensor, force on the rope is transmitted to a force sensor through an elastic tensioning assembly and is fed back to the controller of the frequency regulation module, limiting position is protected by a limit switch, and accordingly, controllability and reliability of the system are improved. By the frequency regulation implementing method, the problem that fundamental frequency of the flexible appendages of some satellites is low or frequency regulation is needed for coupling of frequency and an onboard disturbance source is solved, and system controllability and reliability are realized by monitoring locations, force values and the like.

Description

technical field [0001] The invention relates to a mechanism design method of a satellite, in particular to a method for realizing frequency adjustment of a satellite expandable and flexible accessory. Background technique [0002] With the development of aerospace technology, modern satellites are developing in the direction of large size, low rigidity and flexibility. The fundamental frequency of the flexible accessories of the satellite, such as solar arrays, is relatively low, and the low-frequency dense phenomenon is also obvious. On-orbit satellites are prone to coupling resonance with flexible accessories due to disturbance sources such as flywheels, servo mechanisms, and gyroscopes, which will have a negative impact on the attitude of the entire satellite, and may affect the reliability and stability of some key loads. Conventional solutions mainly include: [0003] 1) Optimize the design of the flexible attachment to reduce the weight so that its natural frequency ...

AI Technical Summary

Problems solved by technology

[0003] 1) Optimize the design of the flexible attachment to reduce the weight so that its natural frequency misses the coupling frequency, but this method has a limited design margin and a small range of frequency changes;

[0004] 2) Add auxiliary struts to the flexible attachment, so that the original flexible attachment configuration of the cantilever beam configuration becomes a triangular truss support structure. This method has an obvious effect on increasing the frequency, but increases the weight, and the strut The design is also more complicated, which increases the complexity of the system;

This method is also limited by the working mode and task requirements of the rotating parts, and cannot effectively solve the problem

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