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van der Hoeven, W. (author)
Fatigue and residual strength tests were done on doubler specimens consisting of an ARALL3 (3/2) laminate with a bonded-on fingertip doubler. The primary objective was to determine the effect of fatigue crack length on the residual strenght and delamination onset stress for this type of specimen. The specimens were precracked to variable crack...
report 1994
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van Rijn, J.F.C.N. (author)
A number of experiments were done to investigate the influence of plasticity on the strain distribution in the vicinity of a notch and the occurrence of local failure for ARALL3 plate specimens. Analysis of the results led to the development of a model for the blunt notch behaviour of fibre metal laminates. A preliminary implementation was...
report 1994
document
Laméris, J. (author)
The effect of the environment on the fatigue behaviour and residual strength of ARALL-3 has been studied using three types of specimens, varying in structural complexity. In addition to the reference ambient air condition, specimens were aged and/or fatigue loaded in hot/humid air or in sump tank fluid. Environmental fatigue loading of door...
report 1994
document
van der Hoeven, W. (author)
Fatigue crack growth and residual strength tests were done on ARALL2 (2/1) laminates with bonded-on doublers. The main test variables were the shape of the doubler (square and fingertip) and the thickness of the doubler (0.5 and 0.8 mm). All coupons had a starter notch in the outer aluminium face sheet of the ARALL2 laminate at the edge of the...
report 1994
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van Rijn, J.C.N. (author)
The stress distribution in the vicinity of a notch is investigated as a first step towards a more fundamental understanding of the blunt notch behaviour of fibre metal laminates. The applicability of several analytical methodologies for determination of the stress distribution in the vicinity of a notch in a finite width plate is assessed in...
report 1994
document
van der Hoeven, W. (author)
The effect of cooling rate on some mechanical properties of APC-2/AS4 composite was investigated over the range between 1 and 70° C/min. Preconsolidated unidirectional laminates were reprocessed in a hot platen press at controlled cooling rates. Double Cantilever Beam specimens and End Notch Flexure specimens were used to determine the mode I...
report 1993
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Labonté, S. (author), Wiggenraad, J.F.M. (author)
A preliminary investigation is reported of the development of a Structure Relevant (SR-) specimen, which maintains the essential features of a stiffened panel configuration, in order to study damage growth behavior at limited cost. Several SR-specimens were fabricated, damage was applied, either through impacts or by the insertion of artificial...
report 1993
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van der Hoeven, W. (author)
Residual strength tests were performed on ARALL panels consisting of ARALL3 (3/2) laminates with bonded-on doublers. In particular, the effect of the doubler geometry (shape and thickness) on the residual strength was investigated. Prior to residual strength testing all panels were fatigue loaded to create a realistic type of damage, i.e. cracks...
report 1992
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van Rijn, J.C.F.N. (author)
The blunt notch behaviour of metal laminates has mostly been described using concepts which were developed to describe the blunt notch behaviour of metals. In the current work the applicability of fracture models which were developed for composites to describe the blunt notch behaviour of metal laminates is assessed. It is shown that three...
report 1992
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Oldersma, A. (author)
Composite materials with more than one type of fiber in one matrix are known as hybrid composites. In this work the fatigue behaviour of composite materials is discussed and the behaviour of hybrid composites is related to simple (single-fiber) composites. The properties and the behaviour of hybrid composites can mostly be explained...
report 1991
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Poon, C. (author)
This report describes the determination of empirical parameters for a fracture model which can be used to predict the uniaxial tensile strength of composite laminates containing notches of various sizes. The parameters required are the characteristic dimension and the unnotched tensile strength of the subject laminate. A data base including...
report 1991
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Olthoff, J. (author)
This report provides an inventory of computer programs for composite materials which are owned by or known to the members of the NFK-TVK action group. The programs are divided in four groups: general laminate theory; specific laminate problems; general (F.E.) analysis programs; miscellaneous problems. The programs are not discussed in the report...
report 1990
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Laméris, J. (author), Minderhoud, P. (author)
The mechanical behaviour of mechanically fastened double lap carbon-epoxy joints has been investigated both by experiments (static tests) and by analysis. Several fastener types and joint geometries has been investigated. In the experimental programme the Fibredux 6376/T400H material was used. Two methods to analyze mechanically fastened...
report 1989
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't Hart, W.G.J. (author)
The damage development In notched (± 45, 0„, 90, 0-) carbon-epoxy coupon specimens tested under different loading conditions was determined. Constant amplitude tests at R = -1 and R = 0.1 as well as flight simulation tests were performed to establish those stress values for which no damage growth occurs.
report 1988
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't Hart, W.G.J. (author)
In this report the results of an impact damage and fatigue investigation are discussed. Comparative impact tests have been carried out on a solid (± 45₂,O ₄)s carbon/epoxy base laminate and the same type of laminate covered with outer layers of glass, aramid or carbon fabric. In addition an Aramid Reinforced Aluminium Laminate (ARALL) was...
report 1985
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Wanhill, R.J.H. (author)
Flight simulation fatigue crack propagation tests with gust spectrum loading were carried out on laminates of (i) aluminium alloy 2024-T3/carbon-epoxy, (ii) aluminium alloy 7475-T761/carbon-epoxy and (iii) titanium alloy Ti-6Al-4V/carbon-epoxy with nominal weight savings of 30% and 40% as compared to equivalent 2024-T3 Alclad and 7475-T761...
report 1982
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de Jonge, J.B. (author)
The report starts with a general review of the loading of transport aircraft fuselages and the consequent fuselage skin stresses Taking the F-28 fuselage as an example, the potential weight savings that can be obtained by using ARALL as skin material are assessed. The report ends with conclusions and recommendations
report 1982
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'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
van der Hoeven, W. (author), Schra, L. (author)
The influence of sheet thickness (2 mm and 10 mm) and the influence of laminating (5x2 ram) on the fatigue crack growth properties of the aluminium alloy AL 7010-T 73651 were investigated. Both constant amplitude loading and flight simulation loading were applied. All 2 mm and 10 mm thick sheets were machined from a 150 mm thick plate, i.e....
report 1981
document
Wanhill, R.J.H. (author)
Flight simulation fatigue crack propagation tests on 202U-T3 and 7475-T761 aluminum alloy sheet were carried out using a gust spectrum representative of the load history of an under wing skin in a transport aircraft. The investigation included tests at several design stress levels and in environments of laboratory air and air plus water spray....
report 1980
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