A Substructure Synthesis Method with Nonlinear ROM Including Geometric Nonlinearities

نویسندگان

چکیده

Large flexible aircraft are often accompanied by large deformations during flight leading to obvious geometric nonlinearities in response. Geometric nonlinear dynamic response simulations based on full-order models carry unbearable computing burden. Meanwhile, caused wings most cases and the deformation of fuselages is small. Analyzing whole as a structure will greatly increase analysis complexity cost. The complicated structures can be more efficient simplified if subcomponents divided treated. This paper aims develop hybrid interface substructure synthesis method expanding reduced-order model (ROM) with implicit condensation expansion (ICE) approach, estimate transient for including nonlinearities. A small number linear modes used construct ROM substructures deformation, also assembled comprehensively. proposed compatible finite element (FEM), allowing realistic engineering analysis. Numerical examples calculated validate accuracy efficiency this contrasted FEM.

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ژورنال

عنوان ژورنال: Aerospace

سال: 2021

ISSN: ['2226-4310']

DOI: https://doi.org/10.3390/aerospace8110344