Avionic device operating modal measuring method for vibration finite element model correction

A technology for avionics equipment and working modes, which is applied in vibration testing, measuring devices, testing of machines/structural components, etc., can solve the problems of cumbersome testing steps and heavy workload, and achieve faster development process, accurate reflection, and saving The effect of testing time and cost

Active Publication Date: 2014-08-13
BEIHANG UNIV
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  • Application Information

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Problems solved by technology

This two-step test method requires a variety of equipment, the test steps are cumbersome, and the workload is large

Method used

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  • Avionic device operating modal measuring method for vibration finite element model correction
  • Avionic device operating modal measuring method for vibration finite element model correction
  • Avionic device operating modal measuring method for vibration finite element model correction

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Embodiment Construction

[0034] The present invention will be further described in detail below in conjunction with the accompanying drawings and examples.

[0035] The avionics equipment in the following example is an aviation parameter processing equipment. This equipment is mainly responsible for collecting information and performing signal processing. It is composed of a box, a circuit board, a motherboard, a relay box and an aviation plug. There are mainly 5 types of modules, respectively It is a power supply module, a digital signal module, an analog signal module, a CPU module and a power conversion module. Examples follow as figure 1 The flow shown is to identify the working mode of the whole aviation parameter processing equipment.

[0036] The present invention is a method for measuring the working mode of avionics equipment for vibration finite element model correction, such as figure 1 As shown, the specific steps are as follows:

[0037] Step 1: Arrange response test points on the avia...

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Abstract

The invention provides an avionic device operating modal measuring method for vibration finite element model correction. The method includes the following steps that firstly, response test points are arranged, and piezoelectric acceleration transducers are pasted, wherein the n response test points are arranged on a circuit board, and the piezoelectric acceleration transducers are pasted on the response test points respectively; secondly, an avionic device and a test device are installed, and an operating modal test platform is built; thirdly, time domain response data of the avionic device under the random vibration condition are acquired; fourthly, data processing is conducted through modal recognition software, and operating modal parameters of the avionic device are acquired. Through the steps, an avionic device operating modal measuring system for vibration finite element model correction is established, and the overall process from generation of random vibration signals to acquisition of the time domain response data and from generation of a time domain response data sample and a cross-spectrum function to recognition of the operating modal parameters of the avionic device is finished. According to the method, online modal recognition is achieved, and test time is saved and test cost is reduced.

Description

technical field [0001] The invention provides a method for measuring the working mode of avionics equipment used for vibration finite element model correction. The main research of the method is to solve and generate the time domain response data output by the vibration test only when the input excitation information is unknown. The cross-spectral function of modal information is used to identify the working mode of avionics equipment, which is used to correct the vibration finite element model in the reliability simulation test, and can also be used as the basis for improving the vibration design of avionics equipment, which belongs to the fault physics Reliability assessment technical field. Background technique [0002] Modal analysis is the process of obtaining modal parameters through calculation or experiment. It is a method to study the dynamic characteristics of structures, and it is the application of system identification methods in the field of engineering vibrati...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01M7/02
Inventor 陈颖高蕾袁增辉王自力
Owner BEIHANG UNIV
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