Finite element model updating using modal flexibility for damage detection on an aircraft wing

Authors

  • Leon V. Lobo Universidade de São Paulo, SP, Brazil.
  • Edilson M. L. Silva Universidade Federal do Pará, PA, Brazil.
  • Thiago A. M. Souza Universidade Federal do Espírito Santo, ES, Brazil.
  • Giedre A. Sirilo Universidade Federal do Espírito Santo, ES, Brazil.
  • João V. F. Dias Universidade Federal do Espírito Santo, ES, Brazil.
  • Reyolando. M. L. R. F. Brasil Universidade de São Paulo, SP, Brazil.

Abstract

SHM is a fundamental area for aerospace engineering. Within this broad area, there are non-destructive ways to assess integrity. This paper presents an approach to damage detection using optimization of a finite element model, where the design variables are the bending inertia of the rectangular box sections forming the components of the structural system, and the objective function is the relative difference between the modal flexibility of the damaged model and the adjusted one. This allows for the detection of damages that caused changes in the modal parameters of the structure using an optimal combination of design variables that generate responses obtained in the modal analysis of the damaged structure once the model is calibrated. The practical application used is the detection of damages in a simplified aircraft wing model.

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Published

05/31/2025

Issue

Vol. 16 No. 2 (2025): Mathematics in Engineering, Science and Aerospace (MESA)

Section

Articles