Experimental Study and Simple Failure Analysis of Stitched J-Stiffened Composite Shear Panels

1996 ◽  
Vol 15 (11) ◽  
pp. 1070-1087 ◽  
Author(s):  
Hsien-Yang Yeh ◽  
Victor L. Chen
Keyword(s):  
Experimental Study ◽  
Failure Analysis ◽  
Failure Criterion ◽  
Resin Transfer Molding ◽  
Failure Criteria ◽  
Transfer Molding ◽  
Tension Tests ◽  
Failure Loads ◽  
Composite Shear ◽  
Tension Strength

Two fuselage type, stitched composite shear panels with J-shape stiffeners manufactured through the process of Resin Transfer Molding technique were tested. Through the diagonal tension tests, it was found that failure of each panel occurred at approximately 3.5 times its initial buckling load, indicating significant diagonal tension strength. Neither of the panels failed by stiffener “pop-off,” showing that the stitching helps to inhibit this failure mode. No other damage or delamination of the panel was visible as well. The newly developed generalized Yeh-Stratton (Y-S) failure criterion was used to evaluate the failure of these composite panels. Compared with several other failure criteria, the calculated failure loads are quite close to experimental results and all are conservative. The Y-S criterion is the most conservative for this case.

Progressive failure analysis of fiber-reinforced laminated composites containing a hole

2017 ◽  
Vol 27 (7) ◽  
pp. 963-978 ◽  
Author(s):  
Hadi Bakhshan ◽  
Ali Afrouzian ◽  
Hamed Ahmadi ◽  
Mehrnoosh Taghavimehr
Keyword(s):  
Failure Analysis ◽  
Failure Modes ◽  
Progressive Failure ◽  
Composite Plates ◽  
Failure Criteria ◽  
Element Analysis ◽  
Progressive Failure Analysis ◽  
Numerical Predictions ◽  
Open Hole ◽  
Failure Loads

The present work aims to obtain failure loads for open-hole unidirectional composite plates under tensile loading. For this purpose, a user-defined material model in the finite element analysis package, ABAQUS, was developed to predict the failure load of the open-hole composite laminates using progressive failure analysis. Hashin and modified Yamanda-Sun’s failure criteria with complete and Camanho’s material degradation model are studied. In order to achieve the most accurate predictions, the influence of failure criteria and property degradation rules are investigated and failure loads and failure modes of the composites are compared with the same experimental test results from literature. A good agreement between experimental results and numerical predictions was observed.

AN EXPERIMENTAL STUDY OF MICRO-VOID CREATION BY IMPURITY IN COMPOSITE MATERIALS DURING VARTM PROCESS

2011 ◽  
Vol 25 (31) ◽  
pp. 4204-4207 ◽  
Author(s):  
Yun-Hae Kim ◽  
Kyung-Man Moon ◽  
Byeong-Woo Lee ◽  
Joon-Young Kim ◽  
Dong-Hun Yang ◽  
...  
Keyword(s):  
Experimental Study ◽  
Composite Materials ◽  
Environmental Control ◽  
Resin Transfer Molding ◽  
Transfer Molding ◽  
Large Structures ◽  
Vartm Process

The effects of impurities on the generation of voids in composites fabricated by vacuum-assisted resin transfer molding was investigated to help reduce mechanical weakening in large structures. Impurities were intentionally inserted into laminates, which were then observed optically. Internal voids were generated in specimens with impurities of 2 – 3mm thickness. The voids grew as the impurities' thicknesses increased to 4 – 5 mm. The voids' diameters were proportional to the thickness of the impurity. Void generation was shown to depend on the thickness of impurities. Environmental control during vacuum-assisted resin transfer molding was shown to be important for ensuring the quality of the resulting composites.

Flexural failure analysis of angle-ply laminates of gfrp and cfrp

1980 ◽  
Vol 15 (1) ◽  
pp. 43-49 ◽  
Author(s):  
G J Turvey
Keyword(s):  
Exact Solution ◽  
Failure Analysis ◽  
Failure Criterion ◽  
Equilibrium Equations ◽  
Initial Failure ◽  
Flexural Failure ◽  
Failure Data ◽  
Centre Line ◽  
Failure Loads ◽  
Is Failure

An exact solution of the strip equilibrium equations is combined with the Tsai-Hill failure criterion to facilitate an initial flexural failure analysis of uniformly-loaded, antisymmetrically-laminated, GFRP and CFRP angle-ply strips. Dimensionless, initial-failure data (that is, failure loads and their associated strip centre-line deflections) are presented for the practical range of fibre orientations, 15° ≤|θ| ≤ 75°, in strips comprising up to ten laminae.

Progressive Failure Analysis of Unidirectional-Fabric Laminated Composite Joints under Pin-Loading

2007 ◽  
Vol 334-335 ◽  
pp. 1-4
Author(s):  
Jin Hwe Kweon ◽  
Hee Jin Son ◽  
Ji Young Choi ◽  
So Young Shin ◽  
Jin Ho Choi ◽  
...  
Keyword(s):  
Finite Element ◽  
Failure Analysis ◽  
Progressive Failure ◽  
Laminated Composite ◽  
Shell Element ◽  
Failure Criteria ◽  
Composite Joints ◽  
Element Analysis ◽  
Progressive Failure Analysis ◽  
Failure Loads

A two-dimensional progressive failure analysis is conducted to predict the failure loads and modes of carbon-epoxy composite joints under pin-loading. An eight-node laminated shell element is used for the finite element modeling. Post-failure stiffness is evaluated based on the complete unloading model combined with various failure criteria. The comparison of finite element and experimental results shows that the finite element analysis based on the combined maximum stress and Yamada-Sun criteria most accurately predicts the failure loads of the composite laminated joints.

scholarly journals Failure Analysis of Graphite Epoxy Composite Plate Under Transverse Sinusoidal Load

2018 ◽  
Vol 7 (3.11) ◽  
pp. 62
Author(s):  
Nor Fazli Adull Manan ◽  
Mohammad Firdaus Mohd Jam ◽  
Shishir Kumar Sahu ◽  
Jamaluddin Mahmud
Keyword(s):  
Composite Material ◽  
Failure Analysis ◽  
Failure Criteria ◽  
Element Analysis ◽  
Specific Strength ◽  
Aspect Ratios ◽  
Marine Industry ◽  
The Finite Element Analysis ◽  
Sinusoidal Load ◽  
Failure Loads

Composite material become interest on various applications in wide industry globally. The selection of composite material due to its versatile properties for instance high specific strength. Besides, the properties of composite material also tailorable for various application including automotive, aerospace and marine industry. The objective of this study is to perform the failure analysis of composite material under transverse sinusoidal load. Both failure criteria, Maximum Stress and Tsai-Wu Failure Criteria that provided in ANSYS used to carry out the analysis. Various aspect ratios will be used which are 5, 10, 20, 50 and 100 to perform the analysis with different thickness of laminate. Next, the boundary condition of the plate was set to simply and clamp supported. The finite element analysis of graphite/epoxy laminate with layup of (0/90/90/0) performed to determine the failure loads (First Ply Failure, FPF and Last Ply Failure, LPF loads). The un-normalized load obtained from the analysis is converted to normalized load using equation given. Finally, normalized load is plotted against aspect ratio for both failure criteria and boundary conditions.  

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