Abstract
This paper proposes a numerical approach to estimate the dynamic behavior of a typical aeronautical aluminum box-beam structure liable to buckling. The methodology is based on a nonlinear finite element model and an experimental modal analysis procedure. The finite element model deals with the coupled nonlinear static and dynamic problems in two steps: 1) determining the static equilibrium considering geometrical nonlinearities, and 2) solving for a linear small-amplitude free-vibration problem based on the tangential stiffness matrix from the current static equilibrium. To illustrate the proposed method, a finite element model is built for a simple supported box beam under a uniaxial compression load with different degrees of eccentricity. The numerical results are correlated with an experimental modal analysis procedure in pre- and postbuckling regimes. Based on this comparison, an updated model is proposed for adjusting the shape and magnitude of the initial imperfections based on linear buckling modes. The results are presented in order to illustrate the effect of the buckling phenomenon and initial imperfections on the dynamic behavior of the box-beam structure.
Original language | English |
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Pages (from-to) | 1987-2003 |
Number of pages | 17 |
Journal | AIAA Journal |
Volume | 54 |
Issue number | 6 |
DOIs | |
Publication status | Published - 2016 |
Externally published | Yes |