Flexible support micro-vibration testing device for simulating whole satellite

Abstract

Provided is a flexible support micro-vibration testing device for simulating a whole satellite. The flexible support micro-vibration testing device comprises a brace supporting structure, a six-component force sensor, an acceleration sensor, a data acquiring and processing system, a rigid platform, and an adaptive support. A whole satellite simulated member is a test object. The top of the brace supporting structure is fixed to the six-component force sensor through an interface. The six-component force sensor is fixed to the whole satellite simulated member through the adaptive support. The acceleration sensor is pasted onto the brace supporting structure. The data acquiring and processing system is connected with the six-component force sensor and the acceleration sensor. The rigid platform is equipped with a plurality of ground racks. The brace supporting structure is fixed to the ground racks on the rigid platform through screws. The flexible support micro-vibration testing device may control and change the rigidity of a whole test system, simulates a transverse fundamental frequency satellite from 5 to 15Hz, has level support structures each of which forms the function of a measuring subsystem in order to simulate the flexible support of a single machine and components to a brace, a single cabin, and a whole satellite.

Description

technical field [0001] The invention belongs to the technical field of vibration testing, and in particular relates to a flexible support micro-vibration testing device for simulating the whole satellite. Background technique [0002] High-performance satellites play an irreplaceable role in today's military struggles. On-orbit micro-vibrations are usually caused by the work of moving parts. With the improvement of the accuracy of payloads carried by spacecraft, the micro-vibrations generated by moving equipment such as flywheels, control moment gyroscopes, and solar panel drive mechanisms commonly used in satellites have entered the effective stage. In the sensitive area of ​​the payload, if no corresponding restraint measures are taken, it is enough to affect the normal operation of the spacecraft. It is not only related to the micro-mechanisms such as friction and collision of moving parts, but also closely related to the coupling of factors such as internal structure, r...

AI Technical Summary

Problems solved by technology

The above research uses a single-stage flexible support structure, which is complicated to load and unload, and does not have multiple flexible support states for simulating brackets, cabins, and entire satellites to test the disturbance characteristics of micro-vibration sources and simulate the flexible supports and micro-vibration sources of satellites with natural frequencies within a certain range ability to couple

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