Searched for: faculty:"Aerospace%5C%2BEngineering"
(1 - 18 of 18)
document
Tandon, S. (author)
A parametric finite element model incorporating virtual crack closure technique was developed in order to determine the critical disbond size and location for disbond growth in an adhesively bonded skin stiffened structure, subjected to uniaxial compression loading. The model was validated using static experimental tests on both pristine and...
master thesis 2016
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Dikici, T. (author)
The carbon fiber industry is nowadays developing new grades of fibers that combine the high mechanical performance of carbon fibers in composites with more attractive cost structure. These developments are in the direction of heavy tow carbon fibers with tow values ranging from 50 to 60K. Using heavy tow carbon fibers reduces the cost structure...
master thesis 2016
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Subramanian, K. (author)
The high stiffness to weight ratio of fibre reinforced composites have been utilized in improving the performance of various structures conventionally designed using metals. One such application is the gangway of the Ampelmann system used to transfer personnel safely from and to the offshore platform in sea. In the current work, a preliminary...
master thesis 2016
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Yao, L. (author)
Advanced composite materials have been commonly used in aerospace engineering, because of their good mechanical properties and attractive potential for creating lightweight structures. Susceptibility to delamination is one of the most important issues in the applications of these materials. This disadvantage can prohibit the application of...
doctoral thesis 2015
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Bürger, D.B. (author)
Aerospace structures have been long dealing with the safety versus weight issue. Lighter airplanes are cheaper to operate, however, they may face a safety issue because of the reduced fatigue life. Consequently, a heavier/safer structure is designed. Adhesive bonding is a joining technique that offers potential for improvement in the fatigue...
doctoral thesis 2015
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Pascoe, J.A. (author), Alderliesten, R.C. (author), Benedictus, R. (author)
Current prediction methods for growth of disbonds under fatigue loading are generally based on a correlation with either the maximum strain energy release rate (SERR) or the SERR range. This paper highlights some issues with this approach. In particular, it is argued that the maximum SERR or the SERR range alone do not give sufficient...
journal article 2014
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Pascoe, J.A. (author), Alderliesten, R.C. (author), Benedictus, R. (author)
The concept of relating fatigue disbond growth to the strain energy release rate (SERR) is critically examined. It is highlighted that the common practise of using only the maximum SERR or only the SERR range is insufficient to correctly characterize a load cycle. As crack growth requires energy, it is argued that growth should be related to the...
journal article 2014
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Pascoe, J.A. (author), Alderliesten, R.C. (author), Benedictus, R. (author)
An overview is given of the development of methods for the prediction of fatigue driven delamination growth over the past 40 years. Four categories of methods are identified: stress/strain-based models, fracture mechanics based models, cohesive-zone models, and models using the extended finite element method. It is highlighted that most models...
journal article 2013
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Smit, J. (author)
master thesis 2013
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Spronk, S.W.F. (author)
The most highly loaded frames of the newly developed Airbus A400M transport aircraft have glass reinforced aluminium laminate (Glare) straps attached to them to increase their resistance to fatigue damage. These straps were designed using static strength requirements for the frame. Basic justification was done in two steps. Firstly, the frame...
master thesis 2013
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Pascoe, J.A. (author)
A model was developed for delamination growth in bonded repair patches under constant amplitude fatigue loading. The model used the finite element method, employing the virtual crack closure technique, to determine the strain energy release rate (SERR) as a function of delamination length. Interaction effects between multiple delaminations, and...
master thesis 2012
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Nijssen, R.P.L. (author)
Wind turbine rotor blades are subjected to a large number of highly variable loads, but life predictions are typically based on constant amplitude fatigue behaviour. Therefore, it is important to determine how service life under variable amplitude fatigue can be estimated from constant amplitude fatigue behaviour. A life prediction contains...
doctoral thesis 2006
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Malek, O.J.A. (author)
Thermoplastic blades offer a variety of advantages to the wind energy industry, but also a few major drawbacks. One of these is the weak fiber to matrix bond in traditional melt processed thermoplastic composites. Because fatigue is dependent on a strong interface, and it is a driving requirement for wind turbine blades, research has been...
master thesis 2006
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Randell, C.E. (author)
The investigation of the present thesis is concerned with the fatigue crack growth behaviour of part through the thickness cracks in Glare™ fibre metal laminate (FML) subjected to combined tension and bending. An experimental program was executed which required the development of a novel fatigue specimen, the Milled Open Hole Tension Bending ...
doctoral thesis 2005
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Plokker, H.M. (author)
The fatigue life of an aircraft is dependent on the loads of the aircraft service spectrum. Due to the variable nature of the load spectrum, fatigue crack growth is accelerated and decelerated by interaction effects. Interaction effects, like crack closure, make an accurate prediction of the fatigue life challenging. The material GLARE, a...
master thesis 2005
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De Rijck, J.J.M. (author)
The two historical fuselage failures, Comet in 1954 and Aloha in 1988, illustrate that similar accidents must be avoided which requires a profound understanding of the fatigue mechanisms involved, including analytical models to predict the fatigue behavior of riveted joints of a fuselage structure. The scope of the research project covers a...
doctoral thesis 2005
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Alderliesten, R.C. (author)
Fibre Metal Laminate Glare consists of thin aluminium layers bonded together with pre-impregnated glass fibre layers and shows an excellent fatigue crack growth behaviour compared to monolithic aluminium. The fibres are insensitive to the occurring fatigue loads and remain intact while the fatigue cracks occur in the aluminium layers. As a...
doctoral thesis 2005
document
Müller, R.P.G. (author)
doctoral thesis 1995
Searched for: faculty:"Aerospace%5C%2BEngineering"
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