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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
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
document
Folkerts, H.H. (author), Jorna, P.G.A.M. (author)
Two different design-philosophies with respect to the Man-Machine Interface of current auto thrust systems were compared in a flight simulator study. With the so-called moving thrust lever concept, the positions of the thrust levers are servo-controlled by the auto thrust system. Hence, the thrust levers provide the pilot with additional...
report 1994
document
'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
document
Gerharz, J.J. (author)
Fatigue life assessment of composite structures in fighter aircraft necessitates testing with both mechanical and environmental loading at both coupon and structural element size levels. Testing facilities to run such tests are now available but environmental fatigue testing is expensive and time consuming. An environmental fatigue loading...
report 1987
document
Erkelens, L.J.J. (author)
The present flight simulator study has been addressed to the evaluation of the approach path parameters for curved approach paths. A number of seven oblique approach paths has been investigated, varying in both straight final length and oblique angle. The investigation was carried out for various operating minima (decision height, runway visual...
report 1987
document
van Gool, M.F.C. (author)
The Working Group on All-Weather Operations of the European Civil Aviation Conference (ECAC) has initiated a study concerning the factors influencing the minium required visibility at take-off. In two special checkout sessions on the KLM Boeing 747 flight simulator, the experimental conditions have been defined for an investigation directed at...
report 1986
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't Hart, W.G.J. (author), Wanhill, R.J.H. (author)
Environmental conditions in Europe are conducive to corrosion attack of aircraft structures. In military aircraft corrosion problems occur especially at countersunk fastener holes. The corrosion is generally removed by grinding. A limited amount of material removal is specified by the aircraft manufacturers, but it is sometimes necessary to...
report 1986
document
Kolkman, H.J. (author)
The effect of penetrant on the fatigue life of single shear riveted lap joints was investigated by flight simulation fatigue tests using the MINITWIST gust spectrum. The penetrant/material combination investigated was ARDROX 985 P3T and aluminium alloy 202U-T3 sheet material (both bare and clad) respectively. The effect of penetrant on the...
report 1982
document
't Hart, W.G.J. (author), Schra, L. (author)
The engineering properties of PM alloy X7091-T7E69 forgings were compared with those of forgings of the IM alloys 7075-T73, 7175-T736, 7050-T736 and 7010-T736. The properties considered were: strength, fracture toughness, fatigue crack propagation under constant amplitude and flight simulation loading, stress corrosion crack initiation and...
report 1982
document
van Gool, M.F.C. (author)
report 1982
document
Nederveen, A. (author), de Jong, J.B. (author)
The influence of the approximation of the lower end of the load spectrum was investigated by comparative tests using the Basic F-27 test programme and an extended version, containing three times more cycles per flight. Crack growth was studied on notched sheet specimens made of Alclad 202U-T3 and Alclad TOT5-T6. Fatigue life tests were done on...
report 1981
document
de Koning, A.U. (author), van der Linden, H.H. (author)
A model for the prediction of growth rates of fatigue cracks in aluminium alloys subjected to service loading conditions is presented. The model is based on an approximate description of the crack opening behaviour and was applied successfully in an analysis of effects of crack growth acceleration and retardation observed experimentally under...
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
't Hart, W.G.J. (author), Schra, L. (author)
The Al-Zn-Mg-Cu alloy 7050 produced by Alcoa is a typical plate and forging alloy because of its low quench sensitivity. In order to compare this alloy with the earlier tested plate alloy 7010 an experimental programme was performed involving tensile, fracture toughness, and fatigue testing. In addition stress corrosion crack initiation and...
report 1980
document
't Hart, W.G.J. (author), Nederveen, A. (author)
Constant amplitude and flight simulation fatigue tests have been carried out on sulphuric acid, chromic acid and phosphoric acid anodized specimens. A comparison was made with the fatigue behaviour of bare sheet material. Before fatigue testing the fracture strain of the anodic layers was determined.
report 1980
document
de Wolf, W.B. (author), Munniksma, B. (author)
An experimental investigation was carried out concerning the effect of jet heating and external flow on the mean flow properties of a subsonic jet. A 60 mm diameter jet was tested in a wind tunnel at wind speeds of 0 and 60 m/s. Jet mach numbers varied between O.44 and 0.94 and jet total temperatures were 310 and 86O K. Velocity and temperature...
report 1980
document
Wewerinke, P.H. (author)
The visual scene is an important source of information for the manual approach and landing task. This study deals with the effect of this information in combination with basic display information on the manual approach performance. In this context, a pre-experimental theoretical analysis has been performed in terms of the optimal control model....
report 1980
document
Nederveen, A. (author), de Jonge, J.B. (author), Tromp, P.J. (author)
The effects of systematic variations in mean stress level and in spectrum and ground load severity of a flight simulation test programme have been investigated on riveted specimens (fatigue life) and sheet specimens with central saw cut (crack growth). The fatigue life and crack propagation life in Alclad 202U-T3 compared with Alclad TOT5-T6...
report 1980
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