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Research Papers

Nonintrusive Structural Dynamic Reduced Order Modeling for Large Deformations: Enhancements for Complex Structures

[+] Author and Article Information
Ricardo Perez

Mem. ASME
SEMTE, Faculties of Mechanical
and Aerospace Engineering,
Arizona State University,
Tempe, AZ 85287-6106
e-mail: raperez1@asu.edu

X. Q. Wang

Mem. ASME
SEMTE, Faculties of Mechanical
and Aerospace Engineering,
Arizona State University,
Tempe, AZ 85287-6106
e-mail: xwang138@asu.edu

Marc P. Mignolet

Fellow ASME
SEMTE, Faculties of Mechanical
and Aerospace Engineering,
Arizona State University,
Tempe, AZ 85287-6106
e-mail: marc.mignolet@asu.edu

Contributed by the Design Engineering Division of ASME for publication in the JOURNAL OF COMPUTATIONAL AND NONLINEAR DYNAMICS. Manuscript received July 14, 2013; final manuscript received November 29, 2013; published online February 13, 2014. Assoc. Editor: Arend L. Schwab.

J. Comput. Nonlinear Dynam 9(3), 031008 (Feb 13, 2014) (12 pages) Paper No: CND-13-1181; doi: 10.1115/1.4026155 History: Received July 14, 2013; Revised November 29, 2013

This paper focuses on the development of nonlinear reduced order modeling techniques for the prediction of the response of complex structures exhibiting “large” deformations, i.e., a geometrically nonlinear behavior, which are nonintrusive, i.e., the structure is originally modeled within a commercial finite element code. The present investigation builds on a general methodology successfully validated in recent years on simpler beam and plate structures by: (i) developing a novel identification strategy of the reduced order model parameters that enables the consideration of the large number of modes (>50 say) that would be needed for complex structures, and (ii) extending a step-by-step strategy for the selection of the basis functions used to represent accurately the displacement field. The above novel developments are successfully validated on the nonlinear static response of a nine-bay panel structure modeled with 96,000 degrees of freedom within Nastran.

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References

Figures

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Fig. 1

Displacements from Nastran at two points of a clamped–clamped beam under various loadings, transverse displacement at middle point versus transverse and in-plane displacements at quarter point

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Fig. 2

Sidewall fuselage panel taken from [28]. Nine-bay panel is a section of this structure.

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Fig. 3

Finite element model of the nine-bay fuselage sidewall panel: (a) isometric view and (b) top view

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Fig. 14

Location of selected frame node for output of results

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Fig. 15

Power spectral density of the transverse (T3) and in-plane (T1 and T2) deflections at the middle point of bay 1. Reduced order model and finite element (“SOL 400”), SPL = 144 dB.

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Fig. 16

Power spectral density of the transverse (T3) and in-plane (T1 and T2) deflections at the middle point of bay 2. Reduced order model and finite element (“SOL 400”), SPL = 144 dB.

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Fig. 17

Power spectral density of the transverse (T3) and in-plane (T1) deflections at the middle point of bay 5. Reduced order model and finite element (“SOL 400”), SPL = 144 dB.

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Fig. 18

Power spectral density of the transverse (T3) and in-plane (T1) deflections at point A of the frame. Reduced order model and finite element (“SOL 400”), SPL = 144 dB.

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Fig. 6

Translation magnitude (in in.) induced by a uniform pressure of 0.6 psi, 85-mode ROM

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Fig. 7

Magnitude (in in.) of the in-plane displacement induced by a uniform pressure of 0.6 psi, skin panel only, NX/Nastran

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Fig. 8

Magnitude (in in.) of the in-plane displacement induced by a uniform pressure of 0.6 psi, skin panel only, 85-mode ROM

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Fig. 9

In-plane displacement (in in.) along T2 induced by a uniform pressure of 0.6 psi, skin panel only, NX/Nastran

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Fig. 10

In-plane displacement (in in.) along T2 induced by a uniform pressure of 0.6 psi, skin panel only, 85-mode ROM

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Fig. 11

In-plane displacement (in in.) along T1 induced by a uniform pressure of 0.6 psi, skin panel only, NX/Nastran

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Fig. 4

Displacements from Nastran at two points of the nine-bay panel under various loadings, transverse displacement at the middle point of the center panel and transverse and in-plane (T2) displacement at the middle point of (a) panel 1 and (b) panel 2

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Fig. 5

Translation magnitude (in in.) induced by a uniform pressure of 0.6 psi, NX/Nastran

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Fig. 12

In-plane displacement (in in.) along T1 induced by a uniform pressure of 0.6 psi, skin panel only, 85-mode ROM

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Fig. 13

Nastran linear response (in in.) induced by a uniform pressure of 0.6 psi, (a) transverse component (T3), (b) in-plane component along T2, and (c) in-plane component along T1

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