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Research Papers: Materials Technology

Finite Element Analysis of the Ultimate Strength of Aluminum-Stiffened Panels With Fixed and Floating Transverse Frames

[+] Author and Article Information
Chenfeng Li

College of Shipbuilding Engineering,
Harbin Engineering University,
Harbin 150001, Heilongjiang, China;
Centre for Marine Technology and Ocean
Engineering (CENTEC),
Instituto Superior Técnico,
Universidade de Lisboa,
Avenue Rovisco Pais,
Lisboa 1049-001, Portugal
e-mail: lichenfeng@hrbeu.edu.cn

Zhiyao Zhu

College of Shipbuilding Engineering,
Harbin Engineering University,
Harbin 150001, Heilongjiang, China
e-mail: zhuzhiyao@hrbeu.edu.cn

Huilong Ren

College of Shipbuilding Engineering,
Harbin Engineering University,
Harbin 150001, Heilongjiang, China
e-mail: renhuilong@263.net

C. Guedes Soares

Fellow ASME
Centre for Marine Technology and Ocean
Engineering (CENTEC),
Instituto Superior Técnico,
Universidade de Lisboa,
Avenue Rovisco Pais,
Lisboa 1049-001, Portugal
e-mail: c.guedes.soares@centec.tecnico.ulisboa.pt

1Corresponding author.

Contributed by the Ocean, Offshore, and Arctic Engineering Division of ASME for publication in the JOURNAL OF OFFSHORE MECHANICS AND ARCTIC ENGINEERING. Manuscript received July 18, 2015; final manuscript received February 10, 2017; published online May 5, 2017. Assoc. Editor: Solomon Yim.

J. Offshore Mech. Arct. Eng 139(4), 041401 (May 05, 2017) (10 pages) Paper No: OMAE-15-1069; doi: 10.1115/1.4036111 History: Received July 18, 2015; Revised February 10, 2017

The aim of this study was to analyze the ultimate strength of stiffened aluminum panels by the nonlinear finite element method. A new type of stiffened aluminum alloy panel has been designed, which has fixed longitudinal and alternating floating transverse frames. Based on material tensile tests, the material properties of the aluminum alloy were obtained. Then, the simulation method of welding residual stresses and the effect of heat-affected zone (HAZ) are investigated. The finite element analysis (FEA) software abaqus V6.11 is used to estimate the ultimate strength of these stiffened panels under axial compression. The results show that: (1) the mechanical imperfections have significant effect on the ultimate strength of stiffened panels; (2) residual stresses may have positive effect on the ultimate strength; and (3) the new stiffened panels also have good performance on ultimate bearing capacities.

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Figures

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Fig. 1

Typical grillage structure of stiffened plates with fixed longitudinal and transverse frames

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Fig. 2

Typical stiffened panel with fixed longitudinal and alternating fixed/floating transverse frame

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Fig. 3

The axial load versus the axial displacement curves of models 1 and 3: (a) response curves of model 1 with difference mesh sizes and (b) response curves of model 3 with difference mesh sizes

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Fig. 4

Deflection modes and spreads of yielding of model 1 at the ultimate strength level

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Fig. 5

Deflection modes and spreads of yielding of model 3 at the ultimate strength level

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Fig. 6

Finite element models of stiffened aluminum plates with fixed and floating transverse frames

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Fig. 7

Engineering and true material curves of the aluminum 1561M in standard state and also in HAZ

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Fig. 8

Standard HAZ width

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Fig. 9

Calculation of residual stress fields

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Fig. 10

The three-span model used in the benchmark study of ISSC' 2003 Committee III.1

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Fig. 11

Deflection modes and spreads of yielding at ultimate strength level

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Fig. 12

The results of comparison in case A (four models without HAZ)

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Fig. 13

Collapse modes of the four models at the ultimate strength stage in case A (magnification 100)

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Fig. 14

The results of comparison in case B (four models with longitudinal direction HAZ softening)

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Fig. 15

Collapse modes of the four models at the ultimate strength stage in case B (magnification 100)

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Fig. 16

The results of comparison in case C (four models with longitudinal and transverse HAZ softening)

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Fig. 17

Collapse modes of the four models at the ultimate strength stage in case C (magnification 100)

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Fig. 18

The results of comparison in case D (four models with residual stress)

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Fig. 19

Collapse modes of the four models at the ultimate strength stage in case D (magnification 30)

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Fig. 20

The results of comparison in case E (four models with HAZ softening and residual stress)

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Fig. 21

Collapse modes of the four models at the ultimate strength stage in case E (magnification 100)

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