Three-level feature fusion diagnosis method and terminal for aircraft structure damage

Abstract

The invention discloses a three-level feature fusion diagnosis method for aircraft structure damage and a terminal, and belongs to the field of aerospace structure health monitoring. Comprising the following steps: calculating a plurality of damage factors of each guided wave channel in a monitoring range, and sequentially carrying out weighted fusion on a single-channel multi-damage factor and damage factors of all channels in a monitoring sub-region to obtain a primary damage feature of each sub-region; feature fusion imaging is carried out based on the damage factor of each channel, and the maximum pixel value of the imaging result of each sub-region is searched as the secondary imaging feature of the sub-region; and finally, carrying out weighted fusion on the damage feature and the imaging feature of each sub-region to obtain a third-level diagnosis feature capable of reliably representing the health state of the sub-region, and judging the sub-region with the damage in combination with an adaptive threshold. According to the method, the problem of large monitoring error of a conventional diagnosis method in an engineering environment is solved, the structural damage occurrence sub-region can be reliably judged, and the method has a good application prospect in the aspect of reliable monitoring of the health state of the aircraft structure.

Description

technical field [0001] The invention belongs to the technical field of aerospace structure health monitoring, and in particular relates to a three-level feature fusion diagnosis method and terminal for aircraft structure damage. Background technique [0002] Compared with conventional metal materials, advanced composite materials such as carbon fiber have the advantages of high specific stiffness, high specific strength, corrosion resistance and strong designability, and have been more and more widely used in the aerospace field. In the actual service process, the composite material structure is prone to internal delamination, fiber breakage and other damage under the action of external impact, fatigue load, etc., which reduces the strength and integrity of the structural parts and seriously threatens the flight safety of the aircraft. Therefore, it is urgent to carry out reliable damage diagnosis of aerospace composite structures to ensure the safe service of aircraft struc...

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Problems solved by technology

[0005] Aiming at the deficiencies of the above-mentioned prior art, the purpose of the present invention is to provide a three-level feature fusion diagnosis method and terminal for aircraft structural damage, so as to solve the problem that the accuracy of the existing single damage feature identification damage is affected by the engineering environment. Problem: The diagnostic method of the present invention combines damage factors and feature fusion imaging results to calculate the three-level eigenvalue of structural damage diagnosis, and compares the magnitude of this eigenvalue with the adaptive damage threshold to comprehensively judge the health status of the structure

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