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Damage monitoring method, device and system for composite structures

A damage monitoring and composite material technology, which is applied in the processing of detection response signals and the use of sonic/ultrasonic/infrasonic waves to analyze solids. Monitoring Efficiency, Quantity Reduction Effect

Active Publication Date: 2018-06-15
BEIJING AERONAUTIC SCI & TECH RES INST OF COMAC +1
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

In actual damage monitoring, it is generally required to scan the entire large-scale sensor network, and analyze and process a large number of Lamb wave sensing signals obtained from the scanning, which makes the task load of damage monitoring very large and the execution efficiency is low.

Method used

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  • Damage monitoring method, device and system for composite structures
  • Damage monitoring method, device and system for composite structures
  • Damage monitoring method, device and system for composite structures

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0031] see figure 1 , is a schematic flowchart of a damage monitoring method for a composite material structure provided in Embodiment 1 of the present invention. The method of the embodiment of the present invention can be executed by a damage monitoring device of a composite material structure configured with hardware and / or software. The implementation device is typically deployed in a damage monitoring system of a composite material structure, and the system includes: signal acquisition device, signal generator and collector, and the entire piezoelectric sensor network arranged in the composite material structure under test.

[0032] In this embodiment, damage monitoring of a large composite fuselage panel in an aircraft is taken as an example for illustration, but the large composite fuselage panel is not used to limit the composite structure to be tested in this embodiment.

[0033] For clarity, first combine figure 2 An introduction to composite fuselage panels.

[...

Embodiment 2

[0077] see Figure 9 , is a schematic structural diagram of a damage monitoring device with a composite material structure provided in Embodiment 2 of the present invention. The device includes: an impact monitoring configuration module 910 , an impact monitoring module 920 , a damage monitoring configuration module 930 and a damage monitoring module 940 .

[0078] Wherein, the impact monitoring configuration module 910 is used to select a piezoelectric sensor for impact monitoring of the tested composite material structure from the entire piezoelectric sensor network arranged in the tested composite material structure; the impact monitoring module 920 is used to When an impact event occurs on the composite material structure under test, the signal collector is used to synchronously collect impact response signals through the selected piezoelectric sensor for impact monitoring; impact monitoring is performed according to the impact response signals to obtain impact event param...

Embodiment 3

[0093] This embodiment provides a damage monitoring system for a composite material structure. The system includes: the entire piezoelectric sensor network arranged in the tested composite material structure, a signal collector, and a signal generator and collector, and also includes: a damage monitoring device for the composite material structure provided by any embodiment of the present invention.

[0094] Wherein, the signal collector may include an impact response signal conditioning unit and a multi-channel signal synchronous acquisition unit. For details, please refer to Embodiment 1, which will not be repeated here.

[0095] The signal generator and collector at least includes: a signal generator unit, a multiplexer unit, a signal conditioning unit and a signal acquisition unit. Preferably, the signal generator and collector may further include: a power amplification unit. For details, refer to Embodiment 1, which will not be repeated here.

[0096] The damage monitor...

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Abstract

The invention provides a damage monitoring method, device and system for a composite material structure. The method includes: selecting piezoelectric sensors for impact monitoring from the entire piezoelectric sensor network arranged in the tested composite material structure; using the selected piezoelectric sensors to collect impact response signals, performing impact monitoring, and obtaining impact event parameters ; Determine the damage monitoring area according to the parameters of the impact event; select the piezoelectric sensor for damage monitoring of the damage monitoring area from the entire piezoelectric sensor network, and determine the corresponding scanning strategy; according to the scanning strategy, use the damage monitoring The piezoelectric sensor excites the Lamb wave monitoring signal to the damage monitoring area, and collects the corresponding Lamb wave sensing signal for damage monitoring, obtains the damage monitoring result of the damage monitoring area, and updates the health of the entire tested composite structure according to the monitoring result state, which improves the efficiency of damage monitoring and ensures the accuracy of damage monitoring.

Description

technical field [0001] Embodiments of the present invention relate to the technical field of structural health monitoring, and in particular to a method, device and system for damage monitoring of composite material structures. Background technique [0002] Composite materials have the advantages of high specific strength and specific modulus, long fatigue life, high temperature and corrosion resistance, and material designability, so they are increasingly widely used in aerospace structures. The proportion of composite materials in the US military aircraft has increased from 2% of the F-15E to 35.2% of the F-35 / CV carrier-based type. The Eurofighter Typhoon uses 40% composites. For commercial aircraft, the composite material consumption of the Boeing B777 of the United States is 11%, while the composite material of the B787 reaches 50% of the weight of the entire aircraft structure. The amount of composite materials used by European Airbus A320 is only 10%, that of A380 h...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G01N29/44G01N29/04G01N29/06
Inventor 卿新林蔡建孙虎杨海楠赵琳
Owner BEIJING AERONAUTIC SCI & TECH RES INST OF COMAC
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