Piezoelectric type decoupling micro-vibration measurement system

Abstract

The invention discloses a piezoelectric type decoupling micro-vibration measurement system. The piezoelectric type decoupling micro-vibration measurement system comprises a base plate, three side plates, eight independent shearing type piezoelectric type sensors, a wiring plate, a loading plate and a data collecting and processing system. The eight shearing type piezoelectric type sensors are coincident and simple in structure, are independently assembled, are located between the base plate and the loading plate and are vertically connected through bolts, each sensor can measure a transverse force and a longitudinal force, and three decoupling dynamic forces and three decoupling dynamic force moments of a disturbance vibration source in the center of the loading plate are measured by reasonably combining the eight sensors; a wire led out from the sensor combination is connected to a corresponding port in the wiring plate, and the port is connected with the data collecting and processing system through a wire. By means of the piezoelectric type decoupling micro-vibration measurement system, the vibration forces and the vibration force moments of the micro disturbance vibration source can be directly measured accurately, calibrating is simple, the measured frequency range is accurate, and the measurement reliability is high.

Description

technical field [0001] The invention relates to the technical field of micro-vibration measurement of moving parts of spacecraft, in particular to a piezoelectric decoupling micro-vibration measurement system, which can be used for dynamic measurement of vibration signals of micro-vibration loads inside 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 modern spacecraft attitude control system, the reaction wheel, the control moment gyroscope and the solar wing drive mechanism are important components in the control system. While they provide the necessary control power, they will also cause some harmful vibrations (for For simplicity, the above three systems are collectively referred to as disturbance sources below). These disturbances are mainly cause...

AI Technical Summary

Problems solved by technology

[0005] The technical problem to be solved by the present invention is: to overcome the deficiencies of the calibration process of the existing test technology and the complex post-processing of the test results, and to provide a piezoelectric decoupling micro-vibration measurement system, which can directly measure the six loads at the center of the vibration table The component is used to analyze the dynamic characteristics of the disturbance source in six degrees of freedom in space during the operation of the spacecraft, and provide reliable test data for improving the attitude control accuracy of the spacecraft and strengthening the safety design of the spacecraft

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