Searched for: subject:"damage%5C+tolerance"
(1 - 17 of 17)
document
Saleh, M.A.S.N. (author), El-Dessouky, Hassan M. (author), Saeedifar, M. (author), Teixeira De Freitas, S. (author), Scaife, Richard J. (author), Zarouchas, D. (author)
This paper investigates the effect of the fabric architecture and the z-binding yarns on the compression after multiple impacts behavior of composites. Four fiber architectures are investigated: non-crimp fabric (NCF), 2D plain weave (2D-PW), 3D orthogonal plain (ORT-PW) and twill (ORT-TW) weave. The specimens were subjected to single and...
journal article 2019
document
Davila, C.G. (author), Bisagni, C. (author)
The fatigue life and damage tolerance of composite stiffened panels with indentation damage are investigated experimentally using single-stringer compression specimens. The indentation damage was induced to one of the two flanges of the stringer of every panel. The advantages of indentation compared to impact are the simplicity of application...
journal article 2018
document
Bisagni, C. (author), Furfari, Domenico (author), Pacchione, Marco (author)
An experimental study has been carried out to investigate the behaviour of co-bonded carbon fibre reinforced plastics joints with a novel design incorporating a through the thickness local reinforcement. Different specimens were manufactured to investigate static and fatigue behaviour, as well as delamination size after impact and damage...
journal article 2018
document
Davila, CG (author), Bisagni, C. (author)
The fatigue life of composite stiffened panels with indentation damage was investigated experimentally using single stringer compression specimens. Indentation damage was induced on one of the two flanges of the stringer. The experiments were conducted using advanced instrumentation, including digital image correlation, passive thermography, and...
conference paper 2016
document
?en, I. (author)
The lower wing skin is one of the primary structures of an aircraft. To further improve the fatigue and damage tolerance (F&DT) performance of the lower wing, fibre metal laminates (FML) are proposed as a new material solution. FML consist of thin metal layers bonded with layers of fibre composites. This concept has potentially a large design...
doctoral thesis 2015
document
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
document
Nagelsmit, M.H. (author)
Composites are notorious for their poor impact behaviour. Delaminations seriously decrease the compressive strength of the material after impact. Laminates made from woven fabric show in general more beneficial impact behaviour than laminates with unidirectional layers, but their manufacturing process is harder to automate. The new fibre...
doctoral thesis 2013
document
Lemmen, H.J.K. (author)
Friction stir welding is a young welding process with high potential to replace riveted joints in aerospace structures like the fuselage. Friction stir welding is a robust process and capable of welding high strength aluminum alloys. Therefore it can lead to both costs and weight savings. To substitute riveted joints by friction stir welded...
doctoral thesis 2010
document
Lopes, C.S. (author)
For a long time, the application of composite materials was restricted to military aircraft and secondary structures of commercial aircraft. Furthermore, the design possibilities offered by composite laminates were narrowed to quasi-isotropic configurations due to their closer behaviour with monolithic materials, hence with a more predictable...
doctoral thesis 2009
document
Chen, D. (author)
doctoral thesis 1991
document
Chen, D. (author)
report 1990
document
Wanhill, R.J.H. (author), Schra, L. (author), 't Hart, W.G.J. (author)
New impetus to continued use of alximinium alloys in major structural areas of aircraft has been given by the development of aluminium-lithium alloys. However, qualification of these new materials for service requires extensive testing and evaluation, preferably in international cooperative programmes. The evaluation of aluminium-lithium alloys...
report 1989
document
Vlieger, H. (author)
This report presents results of residual strength calculations, carried out on cracked panel configurations of various designs and provided with bonded stiffeners. The calculations were carried out using the computer program BOND. The results of these calculations are compared with results of residual strength tests, performed on panels of...
report 1983
document
Wanhill, R.J.H. (author), Jongebreur, A.A. (author), Morgan, E. (author), Moolhuijsen, E.J. (author)
Flight simulation fatigue crack propagation tests on single and double element lugs made from 2024-T351 and TOT5-TT351 aluminium alloys and Ti-6AJ.-UV titanium alloy were carried out. Initial damage was a throughthickness notch at one side of each hole in one element. Results showed that crack propagation lives for double element lugs were much...
report 1981
document
Lof, C.J. (author)
An application of linear elastic fracture mechanics to 3-dimensional crack growth prediction was developed in two phases. In the first phase finite element techniques for accurate stress intensity (S.I.) calculation were evaluated and the Virtual Crack Extension (V.C.E.)-method was selected for further work. In the second phase the process of...
report 1981
document
't Hart, W.G.J. (author)
An experimental investigation was performed to examine the effect of low energy impact damage on tension-compression fatigue properties of sandwich panels. The specimens consisted of a 9 mm thick Nomex honeycomb and face sheets of (0,± 45) and (± 45,0) Carbon/epoxy. Drop weight impact was applied to create internal laminate damage. In order to...
report 1981
document
Vlieger, H. (author)
Past experience has shown that during the operational life of an aircraft structure cracks or failures may arise in different structural components. In future designs the designer must be able on the one hand to restrict the occurrence of cracks by a careful detail design and on the other hand to guarantee some specified life of the aircraft if...
report 1976
Searched for: subject:"damage%5C+tolerance"
(1 - 17 of 17)