4.6 Article

An estimate of the location of multiple delaminations on aeronautical CFRP plates using modal data inverse problem

Journal

Publisher

SPRINGER LONDON LTD
DOI: 10.1007/s00170-018-2502-z

Keywords

Damage identification; Structural health monitoring; Genetic algorithm; Aeronautics; CFRP plates

Funding

  1. Brazilian agency CNPq - Conselho Nacional de Desenvolvimento Cientifico e Tecnologico
  2. CAPES - Coordenacao de Aperfeicoamento de Pessoal de Nivel Superior

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With the increase in the use of composite materials, especially in the aeronautical industry, it is essential that a complete evaluation of the mechanical performance of such structures be undertaken, especially with regard to structural integrity. To assist in this task, structural health monitoring methodologies are employed in order to minimize time and maintenance costs, and errors arising principally from human factors, and which can occasionally result from the failure to properly inspect the aircrafts. This study addresses the use of an inverse method for delamination identification in carbon fiber reinforced polymers plates. First, the direct problem was modeled via a finite element method in order to obtain a faithful model that represented the real case studied. The inverse problem was solved by minimizing an objective function through genetic algorithms. Modal responses of delaminated plates are able to identify the possible location of multiple delaminations in laminated plates since the structural matrices are changed as a function of the induced damage. Numerical and experimental results showed excellent identification of small delaminations, reducing the initial search area by up to 96%, which can lead to savings in time and costs for the aeronautical industry.

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