An ultra-low frequency and high-precision micro-vibration measurement system

Abstract

The invention discloses an ultra-low frequency high-accuracy micro-vibration measuring system which is composed of a base, four adapter blocks, four strain-type force sensors, a load disc, a dynamic strain indicator, 48 strain gages and a data collecting and processing system. The strain gages are pasted on the strain-type force sensors. The strain-type force sensors are located between the load disc and the adapter blocks and are connected between the load disc and the adapter blocks in a tightened mode through bolts. The adapter blocks are located on the side surface of the base and connected with the side surface of the base in a tightened mode through bolts. Three dynamic forces and three dynamic force moments of a disturbance source are measured through the fact that the strain gages pasted on the strain-type force sensors are reasonably combined and connected with the dynamic strain indicator to form 12 full bridge circuits. The disturbance source can be installed inside the measuring system and can also be installed outside the measuring system. The strain gages are connected with the dynamic strain indicator through wires. The dynamic strain indicator is connected with the data collecting and processing system through a wire. The ultra-low frequency high-accuracy micro-vibration measuring system can accurately measure the vibratory force and the vibratory force moment of a tiny disturbance source, the measured frequency range is accurate to 0Hz, and the measuring reliability is high.

Description

technical field [0001] The invention relates to an ultra-low frequency and high-precision micro-vibration measurement system, which can be used for dynamic measurement of vibration signals of micro-disturbance loads inside a spacecraft on six degrees of freedom. Background technique [0002] Most of the current spacecraft are large-scale flexible deployment mechanisms with a large number of optical elements, which have high requirements for pointing accuracy and stability. In addition, in the attitude control system of modern spacecraft, reaction wheels, single-frame moment gyroscopes and solar wing drive mechanisms are important components in the control system. While they provide the necessary control power, they will also cause some harmful vibrations ( For simplicity, the above three systems are collectively referred to as disturbance sources below). These disturbances are mainly caused by flywheel unbalance, bearing disturbance, motor disturbance, motor drive error, et...

AI Technical Summary

Problems solved by technology

In addition, the piezoelectric force sensor has low accuracy in the low frequency region and cannot meet the test requirements for the vibration of the solar wing drive mechanism

[0004] At present, there is no literature report on this kind of ultra-low frequency micro-vibration measurement system at home and abroad.

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