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de Jonge, J.B. (author), Hol, P.A. (author)Fatigue meter data obtained during operational flights of Fokker F27 and Fokker F28 aircraft were re-processed and analyzed to study the variation in load experience between different aircraft of the same type. The Data covered about 470000 flights, made by 101 aircraft of 51 different operators. A simple algorithm was developed to quantify the...report 1996
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de Koning, A.U. (author), Henriksen, T.K. (author)Probably one of the most challenging problems in fracture mechanics is related to its application to fastener and joints. By nature, not only the quality such as material, manufacturing and mounting processes, of the fasteners are playing a role, but also the stiffness, surface conditions and geometry of the parts are to be considered. Moreover,...report 1996
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Wanhill, R.J.H. (author)This paper reviews currently available information on corrosion and fatigue in aircraft as a background to discussing the assessment of corrosion and fatigue damage. The main topics are: - aircraft operating environments and loads - corrosion - fatigue - corrosion and fatigue - corrosion and fatigue damage assessment. Aircraft structures are...report 1995
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Wanhill, R.J.H. (author), Schra, L. (author)An investigation was made of the effect of starter notch geometry on flight simulation fatigue crack growth in three damage tolerant aluminium sheet alloys, 2024-T3, 2091-T84 and 8090-T81. Changing the starter notch geometry resulted in significant differences in initial nonstabilized fatigue crack growth behaviour. However, there was only a...report 1995
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- de Jonge, J.B. (author), Hol, P.A. (author), van Gelder, P.A. (author) report 1995
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Wanhill, R.J.H. (author)This report reviews currently available information on corrosion and fatigue in aircraft as a background to discussing the assessment of corrosion and fatigue damage. The main topics are: * aircraft operating environments and loads * corrosion * fatigue * corrosion and fatigue * corrosion and fatigue damage assessment. Aircraft structures are...report 1994
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Wanhill, R.J.H. (author)The NLR examined by fractography nine ruptured creep specimens supplied by EGT. Three specimens had been tested at 600° C and six specimens had been tested at 650° C. Internal (creep) cracking occured by transgranular microvoid coalescence, which is likely to be characteristic for standard heat treatment Inconel 718. One specimen tested at 600°...report 1994
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Richmond, M.J. (author), de Koning, A.U. (author)Utilising the NLR Stripyield cycle-by-cycle fatigue crack growth model a basic description of the time dependent effects associated with periods of constant load level has been added to model Fatigue-Creep interactions. An outline of the basic Creep model is given along with flow diagrams of the sub programs added to the Stripyield model. Other...report 1993
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de Jonge, J.B. (author)Many military aircraft are used more severely and over a longer periodthan originally intended. Consequently, a careful life management, including service load monitoring has become indispensable. This paper describes the development of a simple method to quantify the severity in terms of "potential crack growth" of recorded load spectra. This...report 1992
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de Jonge, J.B. (author), Bartelds, G. (author)The problems of Ageing Aircraft are worldwide. Hence, actions to overcome or prevent these problems should be taken in international collaboration. The Federal Aviation Administration FAA and the Netherlands Civil Aviation Department RLD have signed a Memorandum of Cooperation in the area of structural integrity, with specific reference to...report 1991
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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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ten Have, A.A. (author)The RNLN Fleet Air Arm (Marine Luchtvaartdienst) has recently implemented a series of usage monitoring procedures for optimisation of Orion and Lynx operation. Goal is an enhancement of efficiency, economy and safety of the usage of both aircraft systems. Compared to the benefits, the efforts for achieving useful usage monitoring are relatively...report 1991
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Schra, L. (author), 't Hart, W.G.J. (author), Boogers, J.A.M. (author)Outdoor corrosion and stress corrosion tests were conducted on Al-Li plate and sheet materials for 3 and almost 5 years respectively. The results can be summarized as follows: Corrosion: Peak aged XXXA-T651 (8090-T651) exhibited greater exfoliation corrosion resistance than 2024-T351 and 2324-T39 plate. 2091-T3 and 2024-T3 sheet were found to be...report 1990
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de Jonge, J.B. (author)Paper presented at the 17th ICAS Congress, Stockholm, September 1990. The actual service load experience of aircraft may differ appreciably from design assumptions. The necessity to monitor service loads is generally recognized now for military aircraft. This paper starts with a general review of the overall life management procedure commonly...report 1990
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Lameris, J. (author)In the full scale durability and damage tolerance tests of composite aircraft structures, the US and European certification requirements demand among other things that the number of cycles applied are statistically significant and that the influence of the environment has been taken into account. Several certification methods are described which...report 1990
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Wanhill, R.J.H. (author)The opportunities for sustained load fracture control in spacecraft are indicated. Emphasis is given to verification by small-scale laboratory testing.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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Schra, L. (author), 't Hart, W.G.J. (author)Long-term outdoor stress corrosion tests were executed on overaged 7000 series aluminium alloy plate and forgings. Plate material of the alloys 7010-T7651, 7010-T7451 and 7075-T7351 exhibited an excellent resistance to SCC. PM alloy X7091-T7E69 forgings combined a higher strength with superior SCC resistance as compared to IM alloy forgings. The...report 1988
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de Koning, A.U. (author)As an introduction the practical significance of fatigue crack growth life prediction is related to the service life, the inspection period and the fracture control requirements. Then different aspects of fatigue crack growth in metallic materials are discussed in more detail. Important effects such as chemical environment, short cracks, crack...report 1987
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Wanhill, R.J.H. (author), Schra, L. (author)Constant amplitude low stress Intensity fatigue crack growth for 2024-T3 and 7475-T761 aluminium alloys In laboratory air, sump tank water and synthetic seawater was Investigated. Corrosion fatigue crack grouwt retardation and arrest occurred In both sump tank water and synthetic seawater, resulting In higher AKth values than In air. Crack...report 1987