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Loading device and loading method for measuring micro vibration characteristic of structure

A loading device and micro-vibration technology, which is used in measurement devices, machine/structural component testing, vibration testing, etc., can solve problems such as increasing loading instability and control difficulty, and inability to achieve vibration.

Active Publication Date: 2016-04-06
BEIJING INSTITUTE OF TECHNOLOGYGY
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The currently used vibrator is connected to the test piece through a connecting rod when a large excitation force is given, and can be connected to the test piece through a string wire when a small force is given. This direct loading method may be useful for The light-weight test piece has the influence of additional mass and stiffness, which increases the instability of loading and the difficulty of control, and cannot achieve vibration at a lower acceleration level

Method used

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  • Loading device and loading method for measuring micro vibration characteristic of structure
  • Loading device and loading method for measuring micro vibration characteristic of structure
  • Loading device and loading method for measuring micro vibration characteristic of structure

Examples

Experimental program
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Effect test

Embodiment 1

[0025] Example as figure 1 , 3 , 4, the loading device for measuring the amplitude-frequency characteristic curve of the test piece under low-acceleration vibration according to the present invention includes: computer 1, data acquisition system 3, piezoelectric ceramic controller 2, laser vibrometer 4, elastic rope 5 and piezoelectric ceramics 7, wherein the test piece 6 is suspended on the aluminum frame of the vibrating table through the elastic rope 5, and the piezoelectric ceramics 7 is pasted on the surface excitation input end of the test piece 6 and connected with the output end of the piezoelectric ceramic controller 2 Connected, the excitation control system includes: computer 1, data acquisition system 3, piezoelectric ceramic controller 2 and piezoelectric ceramics 7, wherein computer 1 is connected to data acquisition system 3, and the frequency sweep output terminal of data acquisition system 3 is connected to piezoelectric ceramics The input end of the ceramic ...

Embodiment 2

[0034] Example two such as figure 2 , 3 As shown, the difference between the second embodiment and the first embodiment is that two identical piezoelectric ceramics 7 are pasted on the test piece 6, and the piezoelectric ceramic controller applies an anti-phase control voltage to the two piezoelectric ceramics, thereby The amplitude-frequency characteristic curve under the condition that a moment load is applied to the test piece 6 can be obtained.

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Abstract

A loading device and a loading method for measuring the micro vibration characteristic of a structure are provided. The loading device comprises a computer, a data acquisition system, two laser vibration meters, a piezoelectric ceramic, and a piezoelectric ceramic controller. The device can apply a small incentive to a test piece, make up for the defect that a vibration exciter cannot provide a small vibration excitation force and reduce the influence of added mass on the test piece in the vibration excitation process. An effective method is provided for exploring the amplitude frequency characteristic curve test and the damping ratio of honeycomb plates, carbon fiber plates and other light test objects under low-acceleration vibration.

Description

technical field [0001] The invention relates to a loading device and method, in particular to a loading device and method for measuring the amplitude-frequency characteristic curve of a test piece under micro-acceleration vibration. Background technique [0002] The micro-vibration of the spacecraft refers to the micro-vibration of the spacecraft structure with an amplitude lower than 0.1g caused by factors such as the actuating mechanism during the normal operation of the spacecraft. During the orbital operation of aerospace, this micro-vibration environmental effect will seriously affect the pointing accuracy and attitude stability of the payload, so it is of great significance to study the frequency response characteristics of aerospace structures under micro-vibration conditions. In order to study the vibration at a lower acceleration level, it is necessary to give the structure a smaller excitation force, and to ignore the additional effects of the excitation, and to me...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01M7/02
CPCG01M7/02G01M7/022G01M7/025
Inventor 周春燕王超凡
Owner BEIJING INSTITUTE OF TECHNOLOGYGY
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