In general, a finite width correction to stress intensity factor (SIF) is required in the fatigue crack growth. The finite width correction factor can be explained physically from the energy point of view. It is assumed that the finite width correction factor primarily constitutes an energy correction factor, i.e. it corrects the applied load for the work applied. To evaluate the finite width correction for FMLs, constant amplitude load fatigue crack growth tests were performed on monolithic aluminium 2024-T3 and the Fibre Metal Laminate GLARE containing 2024-T3 aluminium layers. The loads and displacements were recorded to quantify the total amount of work applied throughout each fatigue test. The crack length and delamination size were mo...
Inconsistent experimental results of fatigue crack closure studies over the past 15 years have cause...
Conventional theories to describe and predict FCG are based on a SIF parameter, ΔK. If ΔK is used as...
Whilst crack growth retardation following the application of an overload during variable amplitude l...
In general, a finite width correction to stress intensity factor (SIF) is required in the fatigue cr...
Finite-width-correction factors (FWCF) are required for GLARE to accurately predict fatigue crack gr...
A mechanistic approach for fatigue crack growth prediction in GLARE laminates is presented. Three-di...
The fatigue life of an aircraft is dependent on the loads of the aircraft service spectrum. Due to t...
Fibre Metal Laminate Glare consists of thin aluminium layers bonded together with pre-impregnated gl...
The investigation of the present thesis is concerned with the fatigue crack growth behaviour of part...
This thesis presents the investigation into the fatigue propagation and delamination growth of Fibre...
The most highly loaded frames of the newly developed Airbus A400M transport aircraft have glass rein...
The excellent durability performance of Glare, a thin fiber metal laminate (FML) material system, is...
This project studies the strength and stiffness degradation of different grades of GLARE with respec...
The aim of the paper is to present the results of a study on the damage of fiber metal laminate (GLA...
Fiber metal laminates (FMLs), composed of alternating layers of metal sheets and fiber-reinforced co...
Inconsistent experimental results of fatigue crack closure studies over the past 15 years have cause...
Conventional theories to describe and predict FCG are based on a SIF parameter, ΔK. If ΔK is used as...
Whilst crack growth retardation following the application of an overload during variable amplitude l...
In general, a finite width correction to stress intensity factor (SIF) is required in the fatigue cr...
Finite-width-correction factors (FWCF) are required for GLARE to accurately predict fatigue crack gr...
A mechanistic approach for fatigue crack growth prediction in GLARE laminates is presented. Three-di...
The fatigue life of an aircraft is dependent on the loads of the aircraft service spectrum. Due to t...
Fibre Metal Laminate Glare consists of thin aluminium layers bonded together with pre-impregnated gl...
The investigation of the present thesis is concerned with the fatigue crack growth behaviour of part...
This thesis presents the investigation into the fatigue propagation and delamination growth of Fibre...
The most highly loaded frames of the newly developed Airbus A400M transport aircraft have glass rein...
The excellent durability performance of Glare, a thin fiber metal laminate (FML) material system, is...
This project studies the strength and stiffness degradation of different grades of GLARE with respec...
The aim of the paper is to present the results of a study on the damage of fiber metal laminate (GLA...
Fiber metal laminates (FMLs), composed of alternating layers of metal sheets and fiber-reinforced co...
Inconsistent experimental results of fatigue crack closure studies over the past 15 years have cause...
Conventional theories to describe and predict FCG are based on a SIF parameter, ΔK. If ΔK is used as...
Whilst crack growth retardation following the application of an overload during variable amplitude l...