Virtual Crack Closure Technique and Finite Element Method for Predicting the Delamination Growth Initiation in Composite Structures

Pietropaoli, Elisa

doi:10.5772/17337

Cited by 14 publications

(7 citation statements)

References 40 publications

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“…Previous work in this area which formed the foundation for the topic of this dissertation has focused on the single fastener response to quasi-static loading. Additionally, work has been conducted using other reinforcement mechanisms which also show promising results [25] [26].…”

Section: Previous Work In This Areamentioning

confidence: 99%

Delamination Arrest by Fasteners in Aircraft Structures Under Static and Fatigue Loading

Richard

2018

2018 AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference

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Laminated composite structures convey tremendous benefits of specific strength and fatigue properties in plane, but are highly susceptible to interlaminar failures such as delaminations and disbonds. The initiation of this failure mode further complicates the design as delaminations initiate along termination points of bonded interfaces, such as a skin-stringer, or are often driven by discrete damage events. As a result, the service life cannot be predicted in the same manner as for metallic aircraft where fatigue analysis is used to substantiate the damage tolerance of the aircraft. In order to provide a substantiation for the FAA damage tolerance requirement of composite bonded structures (FAR23.573), fasteners are subsequently installed. The delamination arrest by fasteners was studied in depth to create a detailed understanding of the process such that it could be accurately predicted under varying load conditions. The fastener itself provides crack arrest capability initially through mode I suppression, and subsequently through fastener joint shear stiffness and frictional load transfer. However, there is also v 7.

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Section: Previous Work In This Areamentioning

confidence: 99%

Delamination Arrest by Fasteners in Aircraft Structures Under Static and Fatigue Loading

Richard

2018

2018 AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference

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“…[5] [12] In this method, the nodal displacements and forces necessary to determine the energy that is required to close the crack can be established by a single step finite element analysis inspite of two as in virtual crack closure technique [11].…”

Section: Literature Reviewmentioning

confidence: 99%

Damage Tolerance Evaluation of an Aircraft Skin Structure by Mvcci Technique (2d Analysis) Using MSC – Nastran / Patran

.¹

2016

IJRET

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An Aircraft is a light weight airbreathing semi-monococque complex aerostructure comprising of longerons, bulkheads, stiffeners, stringers, lugs, bolts and joints, ribs and other special forms of structures. In its service, it has to sustain aerodynamic, structural, propulsive, fatigue and impact loads. Even though the load carrying agents are the stiffening materials, the loads are firstly faced by the aircraft skin in the form of shear loads and later on transferred to the stiffening structures inside. In the present study, A small portion of the aircraft skin is considered and is analyzed by Damage Tolerance technique, ie, by assuming a minute flaw to be present at the time of manufacturing itself or by other processing efforts. While in operation, due to the crack initiation, the accumulated crack propagates to critical sizes leading to catastrophic failure. The main objective of this paper is to determine the normalized stress intensity factor in the opening mode K I for a finite width plate in uniform tension with a central crack. The report will start with a brief review of fracture proceeding further with the concept of Stress Intensity Factor in opening mode, i.e., K I, and common design strategies (Assumptions) to assure the structural integrity of components and of the role that stress intensity factor plays through different modes of failures. And it also covers an overview of energy approach and stress intensity approach to a problem. Using MSC NASTRAN/PATRAN, Stress Intensity Factor in opening mode, K I is found by MVCCI technique and is validated with the theoretical results obtained by Feddersen empirical modeling.

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“…Among seven types of wind blade damage, delamination and adhesive joint failure are most frequent. Delaminations are the most critical and commonly studied failure mode in laminated composite materials (Abdussalam, 2000;Bolotin, 1996;Davidson et al, 2000;Elisa, 2011;Pagano and Schoeppner, 2000;Tay, 2003). There are many reasons for blade damage starting from the manufacturing floor to field operation.…”

Section: Introductionmentioning

confidence: 99%

Damage mitigation techniques in wind turbine blades: A review

et al. 2017

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Wind blades are major structural elements of wind turbines, but they are prone to damage like any other composite component. Blade damage can cause sudden structural failure and the associated costs to repair them are high. Therefore, it is important to identify the causation of damage to prevent defects during the manufacturing phase, transportation, and in operation. Generally, damage in wind blades can arise due to manufacturing defects, precipitation and debris, water ingress, variable loading due to wind, operational errors, lightning strikes, and fire. Early detection and mitigation techniques are required to avoid or reduce damage in costly wind turbine blades. This article provides an extensive review of viable solutions and approaches for damage mitigation in wind turbine blades.

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Virtual Crack Closure Technique and Finite Element Method for Predicting the Delamination Growth Initiation in Composite Structures

Cited by 14 publications

References 40 publications

Delamination Arrest by Fasteners in Aircraft Structures Under Static and Fatigue Loading

Delamination Arrest by Fasteners in Aircraft Structures Under Static and Fatigue Loading

Damage Tolerance Evaluation of an Aircraft Skin Structure by Mvcci Technique (2d Analysis) Using MSC – Nastran / Patran

Damage mitigation techniques in wind turbine blades: A review

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