Progressive Failure Analysis of Pipeline Repaired by Composite Wrapping

2016 ◽  
Vol 853 ◽  
pp. 483-487
Author(s):  
Yan Yv Wang ◽  
Zhi Qiang Cheng ◽  
Bao Sheng Liu
Keyword(s):  
Failure Analysis ◽  
Critical Pressure ◽  
Progressive Failure ◽  
Failure Criteria ◽  
Pressure Vessels ◽  
Progressive Failure Analysis ◽  
Failure Propagation ◽  
Hashin Failure Criteria ◽  
Two Stages ◽  
Good Agreement

Composite overwrap systems have been widely used to repair damaged pipelines. Its effectiveness has been proven by many researches and engineering applications. However, the research on progressive failure mode of the repaired structure has not been reported. In the present paper, finite element method with Hashin failure criteria is developed to realize the progressive failure analysis. The predicted burst pressure is in good agreement with the burst experiment. Different from widely-reported failure progress in Composite Overwrapped Pressure Vessels (COPV), the progressive failure analysis for the defected pipeline overwrapped by composite reveals very different failure stages: stable failure propagation and rapid failure propagation. The identification of critical pressure between these two stages is valuable in composite reparation design for the defected pipeline.

scholarly journals Open-Hole 3D Braided Composites Strength Prediction and Stress Analysis

2020 ◽  
Vol 38 (4) ◽  
pp. 889-896
Author(s):  
Shuangqiang Liang ◽  
Chenglong Zhang ◽  
Ge Chen ◽  
Qihong Zhou ◽  
Frank Ko
Keyword(s):  
Failure Analysis ◽  
Progressive Failure ◽  
Failure Criteria ◽  
Element Analysis ◽  
Braided Composite ◽  
Failure Initiation ◽  
Geometry Model ◽  
Progressive Failure Analysis ◽  
3D Braided Composites ◽  
Open Hole

The stress concentration caused by notches is a common engineering issue for composite structure application. 3D braided composite possess excellent damage tolerance compared to common laminates. The tensile properties of 3D braided composite with open-hole and un-notched were experimentally examined. The mechanic properties of 3D braided composite in other directions are predicted using FGM (Fabric Geometry Model) and finite element analysis. The stress distributions around the hole and perpendicular to the loading direction are analyzed based on Abaqus software. The simulation results were compared with Lekhnitskii's analytical study. The open-hole strength of 3D braided composite was predicted respectively using Average stress failure criteria, Point stress failure criteria (PSC), and also the progressive failure analysis based on different failure criteria. The predicted strength results were compared to the experimental values. The results show the PSC predicted strength matched the experiment, while the progressive failure analysis can predict the failure initiation, propagation and final failure mode.

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.

A particular criterion for progressive failure analysis of carbon/phenolic tape-wounded conic shells

2021 ◽  
pp. 105678952199591
Author(s):  
SA Hosseini Kordkheili ◽  
M Karimian ◽  
HR Jafari
Keyword(s):  
Failure Analysis ◽  
Composite Structures ◽  
Progressive Failure ◽  
Failure Criteria ◽  
Solution Algorithm ◽  
Shell Structures ◽  
Finite Element Software ◽  
Progressive Failure Analysis ◽  
Conic Shell ◽  
Margin Of Safety

Conic shell structures are widely used in aerospace industries. In the literature various models have been proposed to failure analysis of composite materials. Clearly, each model has a favorable range of applications. In this paper tensile, compressive, shear and thermal expansion properties of tape-wounded Carbon/Phenolic composites are firstly measured at various temperatures in range 23–200°C. The captured properties are then taken into account to progressive failure analysis of a conic Carbon/Phenolic structure under internal pressure and thermal loadings. For this end, a particular failure criterion is proposed to predict failure in the composite structures with a reasonable margin of safety. The enhanced model is then implemented into the commercial finite element software of ABAQUS via a developed user material (UMAT) subroutine utilizing a suitable solution algorithm. Advantages of the model are assessed and comparisons with other failure criteria as well as experiment are presented.

scholarly journals PROGRESSIVE FAILURE ANALYSIS OF HELICOPTER ROTOR BLADE UNDER AEROELASTIC LOADING

Aviation ◽  
2020 ◽  
Vol 24 (1) ◽  
pp. 33-41 ◽  
Author(s):  
Kamran Ahmad ◽  
Yasir Baig ◽  
Hammad Rahman ◽  
Hassan Junaid Hasham
Keyword(s):  
Failure Analysis ◽  
Composite Structures ◽  
Composite Laminate ◽  
Progressive Failure ◽  
Constitutive Relations ◽  
Metal Structure ◽  
Failure Criteria ◽  
Helicopter Rotor ◽  
Progressive Failure Analysis ◽  
Failure Location

Unlike metal structure, composite structures don’t give any clue till the fatal final collapse. The problem is more complicated when applied load on the structure is aeroelastic in nature. Under such loading, composite laminate experiences stresses. The first layer failure happens when stresses in the weakest ply exceed the allowable strength of the laminate. This initial layer-based failure changes overall material characteristics. It is important now to degrade the composite laminate characteristics for the subsequent failure prediction. The constitutive relations are required to be updated by the reduction in stiffness. The rest of the undamaged laminates continue to take the load till the updated strength is reached. In the present work, layer wise progressive failure analysis under aeroelastic loading has been performed by the inclusion of different failure criteria which allow for the identification of the location of the failure. ANSYS APDL environment has been used to model geometry of helicopter rotor. Under the loading conditions, stresses are calculated in the blade. Using stress tensor and failure criteria, failure location and modes have been predicted. It has been found that failure starts at higher speeds and failure starts from the root chord and tend towards the tip chord.

scholarly journals Investigation of mechanical performances of composite bolted joints with local reinforcements

2018 ◽  
Vol 25 (1) ◽  
pp. 75-83 ◽  
Author(s):  
Jifeng Zhang ◽  
Qiang Xie ◽  
Yonggang Xie ◽  
Limin Zhou ◽  
Zhenqing Wang
Keyword(s):  
Finite Element ◽  
Tensile Strength ◽  
Failure Analysis ◽  
Failure Modes ◽  
Numerical Study ◽  
Progressive Failure ◽  
Failure Criteria ◽  
Bolted Joints ◽  
Progressive Failure Analysis ◽  
Mechanical Performances

AbstractFour different local reinforcement schemes used in composite bolted joints were studied. In numerical study, a set of 3-D failure criteria was used and the progressive failure analysis was implemented via user-defined subroutine vectorized user-material (VUMAT), which was programmed by the commercial finite element (FE) software ABAQUS. In the experiment, test specimens were manufactured with different local reinforcement schemes, and the mechanical performances of these specimens were tested under tensile loads. Failure modes of these specimens were observed and mechanical performances of test specimens with local reinforcement were studied. It was found that the numerical results agreed well with the experiment. It was also found that local reinforcement schemes influenced the mechanical performances of bolted joints obviously and that the tensile strength of composite bolted joints could be improved significantly by burying laminate slices.

MULTISCALE PROGRESSIVE FAILURE ANALYSIS OF PLAIN-WOVEN COMPOSITE MATERIALS

2009 ◽  
Vol 01 (02) ◽  
pp. 263-301 ◽  
Author(s):  
L. RAIMONDO ◽  
M. H. ALIABADI
Keyword(s):  
Composite Materials ◽  
Failure Analysis ◽  
Damage Mechanics ◽  
Progressive Failure ◽  
Fibrous Composite ◽  
Closed Form Solution ◽  
Failure Criteria ◽  
Woven Composite ◽  
Progressive Failure Analysis ◽  
Proposed Model

The paper presents an overview of multiscale modeling of advanced fibrous composite materials. Following the review, a nonlinear, fully three-dimensional, numerical model is proposed which is suitable for multiscale elastic and progressive failure analysis of plain-woven composite materials. The proposed model is developed for implementation into the Finite Element code ABAQUS/Explicit as a user-defined subroutine for constant stress (one integration point) solid elements. The multiscale strategy applied in this paper uses a closed-form solution approach for homogenization of the mesoscale properties of a woven composite. A mosaic model of the woven composite's Representative Volume Element (RVE) is used for deriving the micromechanical relations used for homogenization. The composite RVE model used herein is composed of UD interlacing yarns (fill and warp yarns) and matrix-rich regions. For failure and damage analysis, the following features are implemented in this work: material nonlinearity for pure in-plane shear deformation; physically-based failure criteria for matrix failure in the UD yarns; maximum stress failure criteria for failure of fibers in the UD yarns and of the pure matrix in the resin-rich regions and energy-based damage mechanics. The proposed strategy, which has been implemented and tested for a special case of an in-plane damage, has some evident advantages compared to the other approaches, especially for application to full-scale simulations, i.e., component and structural scales. A comparison of the proposed model with experimental data shows a good correlation can be achieved.

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