Experimental and Numerical Investigation of PZT Response in Composite Structures with Variable Degradation Levels

Memmolo, Vittorio; Elahi, Hassan; Eugeni, Marco; Monaco, Ernesto; Ricci, Fabrizio; Pasquali, Michele; Gaudenzi, Paolo

doi:10.1007/s11665-019-04011-4

Cited by 30 publications

(10 citation statements)

References 31 publications

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“…A fatigue crack, when initiated, grows slowly until the critical crack length is reached, after which the fatigue crack growth rate increases and leads to the failure of the component. Due to the lack of a thermal fatigue test standard, different experimental arrangements have been proposed by researchers for the thermal fatigue testing of materials [12] and [21]. Generally, researchers develop setups that are closer to actual conditions.…”

Section: • Ratcheting Behaviour Of Ss316l Results In Plastic Deformatmentioning

confidence: 99%

Studying the Effect of Thermal Fatigue on Multiple Cracks Propagating in an SS316L Thin Flange on a Shaft Specimen Using a Multi-Physics Numerical Simulation Model

Mukhtar

Qayyum

Elahi

et al. 2019

SV-JME

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After more than a decade of research on thermal fatigue cracking in nuclear reactor components, the science remains incomplete. It is essential to understand the crack propagation behaviour and the influence of multiple cracks on the fatigue life of a component due to thermal fatigue load. Accurate numerical simulation modelling can help in better understanding the influence of different factors on failure propagation. In this research, a finite element-based numerical simulation model has been developed using ABAQUS commercial software to obtain insight into crack propagation and crack arrest in an SS316L thin flange on shaft specimen; the assembly is cooled internally, and cyclic thermal loading is applied on the flange rim. The experiment was carried out on a specially designed rig using an induction coil for heating the outer rim. Thermocouples were attached radially on the rim to collect detailed temperature profiles. Real-time temperature-dependent elastic-plastic material data was used for modelling. The boundary conditions and thermal profile used for the numerical model were matched with experimental data. The stresses responsible for crack initiation, the effect of crack number and crack lengths on stresses, energy absorbed at the crack tip after every thermal cycle and the threshold values of cracks are evaluated in the current work. The obtained simulation results were validated by comparing experimental observations. The developed simulation model helps in better understanding the evolution of stresses and strains in uncracked and cracked SS316L discs mounted on a flange due to thermal cycling. It also helped in better understanding the crack propagation behaviour and the evolution of energy release at crack tips. Such a model can help future researchers in designing components undergoing thermal fatigue loading, for example, in nuclear power plants.

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Section: • Ratcheting Behaviour Of Ss316l Results In Plastic Deformatmentioning

confidence: 99%

Studying the Effect of Thermal Fatigue on Multiple Cracks Propagating in an SS316L Thin Flange on a Shaft Specimen Using a Multi-Physics Numerical Simulation Model

Mukhtar

Qayyum

Elahi

et al. 2019

SV-JME

Self Cite

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“…Indeed, further critical tasks are needed once diagnosis is achieved. In addition, different stages can be identified, and likewise different methodologies can be adopted to perform those tasks [ 47 , 48 , 49 ]. Generally, the underlying concept in SHM is to record and store the structural response after a diagnostic or ambient excitation, post-process current dataset looking for features sensitive to any defect and relate such parameters to damage characteristics [ 50 , 51 , 52 ].…”

Section: Methodsmentioning

confidence: 99%

Impact of Structural Health Monitoring on Aircraft Operating Costs by Multidisciplinary Analysis

Cusati

Corcione

Memmolo

2021

Sensors

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Structural health monitoring is recognized as a viable solution to increase aviation safety and decrease operating costs enabling a novel maintenance approach based on the actual condition of the airframe, mitigating operating costs induced by scheduled inspections. However, the net benefit is hardly demonstrated, and it is still unclear how the implementation of such an autonomic system can affect performance at aircraft level. To close this gap, this paper presents a systematic analysis where the impact of cost and weight of integrating permanently attached sensors—used for diagnostics- affect the main performance of the aircraft. Through a multidisciplinary aircraft analysis framework, the increment of aircraft operating empty weight is compared with the possible benefits in terms of direct operating costs to identify a breakeven point. Furthermore, the analysis allows to establish a design guideline for structural health monitoring systems returning a safer aircraft without any economic penalties. The results show that the operating costs are lower than those of the reference aircraft up to 4% increase in maximum take-off weight. Paper findings suggest to considering a condition monitoring strategy from the conceptual design stage, since it could maximize the impact of such innovative technology. However, it involves in a design of a brand-new aircraft instead of a modification of an existing one.

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“…4,5 Therefore, a correct prediction of the initiation and growth of fretting-initiated cracks is the key to improved fretting designs. Theoretically, the Smith–Watson–Topper method can be used to predict crack initiation, and fracture mechanics 6–9 and finite element approaches 10–15 are applied to predict crack propagation in a component.…”

Section: Introductionmentioning

confidence: 99%

Fretting fatigue crack initiation and propagation in Ti6Al4V sheets under tribocorrosive conditions of artificial seawater and physiological solutions

Anjum

Shah

Elahi

et al. 2020

Proceedings of the Institution of Mechanical Engineers, Part L:

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The interaction of mechanical components experiencing relative movements and cyclic loads in a corrosive environment is known as fretting corrosion or tribocorrosion. In the current work, the mechanism of crack initiation and propagation in dovetail slots of Ti6Al4V samples (in contact with carbide rods) under fretting corrosion conditions was investigated. A newly developed test rig installed on a universal testing machine was used to conduct tests at 20 Hz frequency under 5 and 7.5 kN fretting loads. Tests were conducted at room temperature in 3.5% NaCl and phosphate-buffered saline solutions. Crack propagation in all samples was examined by a metallurgical microscope, and the detailed analysis of fractured samples was carried out by a scanning electron microscope. In comparison to dry conditions, early crack initiation and faster crack propagation were observed in salt and physiological solution environments. Colored spots and large amounts of chlorine, sodium, and oxygen were found around cracks, and plastically deformed regions in the 3.5% NaCl environment provided the evidence of a corrosive attack. Large amounts of oxygen, phosphorous, chlorine, potassium, and sodium were detected in the phosphate-buffered saline environment.

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Experimental and Numerical Investigation of PZT Response in Composite Structures with Variable Degradation Levels

Cited by 30 publications

References 31 publications

Studying the Effect of Thermal Fatigue on Multiple Cracks Propagating in an SS316L Thin Flange on a Shaft Specimen Using a Multi-Physics Numerical Simulation Model

Studying the Effect of Thermal Fatigue on Multiple Cracks Propagating in an SS316L Thin Flange on a Shaft Specimen Using a Multi-Physics Numerical Simulation Model

Impact of Structural Health Monitoring on Aircraft Operating Costs by Multidisciplinary Analysis

Fretting fatigue crack initiation and propagation in Ti6Al4V sheets under tribocorrosive conditions of artificial seawater and physiological solutions

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