The formulation for riveted plates has been presented and several lap joints have been tested and compared with available results. The importance of the determination of rivet flexibility has been pointed out. Several empirical formulas are available, which give different values that can affect the results. As reported by Müller, defects in the joining between rivets and plates (i. e. gaps) and friction between plates, could be included in the rivet flexibility determination. Results found confirmed the validity of the formulation, although some discrepancies with FEM are acknowledged in trends along the same row for large joints. It has to be pointed out that contact between plate surfaces is also not modelled in FEM. For the boundary element method the contact algorithms are described in Man et al. and Aliabadi and Martin. The local effects around rivet holes are not investigated, as the aim is the application to large riveted structures. Then a skin-stiffener section has been modelled with different types of rivet distributions and compared with a perfect bonded joint. The general results have been found to be satisfactory; it has been found possible to model large structure connected with rivets. At the end a large wing-box section has been modelled; the results are found to be in accordance with expectations, it is possible to obtain the rivets by-pass loads and to locate highly stressed ones. The global solution for the entire section is found to be satisfactory. The BEM formulation can be extended to modelling riveted composite panels as reported by MacCarthy et al. using the finite element method.
Boundary element analysis of riveted aircraft panels
Rand-Element-Analyse von genieteten Flugzeug-Kastenprofilen
Journal of Strain Analysis for Engineering Design ; 47 , 3 ; 187-199
2012
13 Seiten, 20 Bilder, 6 Tabellen, 21 Quellen
Article (Journal)
English
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