A hybrid reduced-order modeling technique for nonlinear structural dynamic simulation

Yang, Chen; Liang, Ke; Rong, Yufei; Qin, Sun

doi:10.1016/j.ast.2018.11.008

Cited by 18 publications

(1 citation statement)

References 41 publications

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“…where M is the linear mass matrix and K is the linear stiffness matrix, f NL (u) indicates the nonlinear restoring force function, u and F are displacement vector and external force vector in physical space. The geometric nonlinear theory demonstrates that the quadratic and cubic polynomials of displacement are accurate enough to describe the nonlinear restoring force [40]. Introduced linear mode Φ and reduced system by: u=Φq…”

Section: Structure Equationsmentioning

confidence: 99%

A Substructure Synthesis Method with Nonlinear ROM Including Geometric Nonlinearities

Meng

Xie

et al. 2021

Aerospace

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

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Section: Structure Equationsmentioning

confidence: 99%