Monitoring method and monitoring system for progressive damage of corrugated composite wing cover

Abstract

The invention discloses a monitoring method for a progressive damage of a corrugated composite wing cover, and particularly relates to a monitoring method and a monitoring system for the progressive damage of the corrugated composite wing cover based on a nonuniform fiber bragg grating (FBG) reflectance spectrum. The method comprises the steps that based on finite element analysis on the corrugated composite wing cover, a cover layer failure sequence is predicted; corresponding critical failure loads and distribution of strain fields at layer damage parts are extracted; and the FBG reflectance spectra corresponding to the critical failure loads are obtained by an FBG reflectance spectrum reconstruction principle. The monitoring system is constructed; spectra of cover layers during failure are monitored and recorded; trends of the spectra are the same as that of a predicted spectrum; and an error does not exceed 8.6%. The invention further discloses the monitoring system applying a monitoring technology. Therefore, the progressive damage of the corrugated composite cover can be monitored in real time by monitoring characteristic changes of the nonuniform FBG reflectance spectrum.

Description

technical field [0001] The invention discloses a progressive damage monitoring method and system for a corrugated composite material wing skin, specifically a progressive damage monitoring technology for a corrugated composite material wing skin based on FBG non-uniform reflection spectrum, which relates to industrial production, biological , aerospace and other fields. Background technique [0002] With its good chord flexibility, large span stiffness, and excellent deformation accumulation effect, the corrugated composite skin will become a breakthrough point in the development of future variant wings. When the skin is operated for a long time, under the conditions of alternating stress, chemical corrosion, mechanical vibration, etc., debonding damage will occur between the layers, and compression damage will occur at the peak. Therefore, the structural health monitoring and skin damage prediction of the corrugated composite skin are particularly important for the develop...

AI Technical Summary

Problems solved by technology

However, for some parts of the structure, such as the repaired area of ​​the metal repair structure, the internal area of ​​the joint of the composite bonded joint structure and the new composite wing skin, etc., the strain suffered during service is non-uniform, If the damage identification is carried out through the drift of the central wavelength of the FBG reflection spectrum, errors will inevitably occur, and even errors will occur

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