Abstract
Prediction and tracking of aircraft structural life has long been a goal of the U.S. Air Force. Prediction for future high speed aircraft will require multi-scale modeling. One candidate method under investigation is presented in a companion paper. The method combines recent developments in nonlinear reduced-order models (ROMs) with the global-local approach of the Generalized Finite Element Method (GFEM). The ROMs are used to predict the dynamic response of an aircraft sub-component such as a panel. The GFEM provides a framework to model local effects such as stress risers and defects without geometric path dependency in the finite element (FE) mesh. Combined, the two methods provide an efficient method to track the dynamic stress conditions in order to predict life. This paper presents a numerical and experimental case study of the combined method on a bi-axial stress test specimen.
Published Version
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