The results of using early damage diagnostics technique (developed in the Mechanical Engineering Research Institute of the Russian Academy of Sciences (IMASH RAN) for detecting the latent damage of an aviation panel made of composite material upon bench tensile tests are presented. We have assessed the capabilities of the developed technique and software regarding damage detection at the early stage of panel loading in conditions of elastic strain of the material using brittle strain-sensitive coating and simultaneous crack detection in the coating with a high-speed video camera “Video-print” and acoustic emission system “A-Line 32D.” When revealing a subsurface defect (a notch of the middle stringer) of the aviation panel, the general concept of damage detection at the early stage of loading in conditions of elastic behavior of the material was also tested in the course of the experiment, as well as the software specially developed for cluster analysis and classification of detected location pulses along with the equipment and software for simultaneous recording of video data flows and arrays of acoustic emission (AE) data. Synchronous recording of video images and AE pulses ensured precise control of the cracking process in the brittle strain-sensitive coating (tensocoating)at all stages of the experiment, whereas the use of structural-phenomenological approach kept track of the main trends in damage accumulation at different structural levels and identify the sources of their origin when classifying recorded AE data arrays. The combined use of oxide tensocoatings and high-speed video recording synchronized with the AE control system, provide the possibility of definite determination of the subsurface defect, reveal the maximum principal strains in the area of crack formation, quantify them and identify the main sources of AE signals upon monitoring the state of the aviation panel under loading P = 90 kN, which is about 12% of the critical load.

A methodical approach to the estimation of the localization zone and geometric parameters of a delamination defect in layered composite materials is presented on the basis of mathematical processing of the experimental results of deformation measurements obtained with a grid of fiber-optic sensors. The results of methodological developments related to the determination of the optimal topology of the grid of sensors to ensure the detection of defects of a given size with the necessary accuracy and determination of their parameters are presented. We present methods for computational analysis and simulation of the strain-stress state in the defect zone, based on the algorithm used for modeling the problems of strain-stress analysis in the defect zone using 2D finite elements, instead of 3D ones, thus allowing the use a model of lower dimensionality and retain all the features of the stress-strain state. The results of methodological developments related to the determination of the defect parameters from the results of strain measurements using the methodology of solving the inverse problem, based on solving the problem of minimizing the discrepancy between the vector of deformation response and the vector of initial parameters are presented. The technique is implemented as a software consisting of a series of macros for ANSYS and programs for MATLAB. The results of cyclic testing of a sample from a multilayer CM with a delamination type of defect are presented. Estimation of the increment in the defect size upon loading is performed by mathematical processing of data recorded by fiber-optic strain sensors glued on one of the sample surfaces, based on the solution of the inverse problem. Comparison of the results of calculations of geometric parameters of the defects with the measurement data obtained by the method of ultrasonic flaw detection showed good agreement between them.

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