This paper aims to give an introduction of the design of composite bolted joints at British Aerospace. Basic failure modes and the effects of geometric and lay-up variations are discussed. Codes of design practice to ensure optimum joint design are presented. The most common joint occurring in aircraft structures is a countersunk fastener in single shear. Results from programmes investigating the static and fatigue response of such joints as a function of laminate thickness and fastener type are presented. Finally the two methods of stressing bolted joints under combined loading are discussed. The first method is applied to relatively lightly loaded joints using small fasteners e.g. wink skin/spar bolting. The second is applied to highly loaded joints using large fasteners e.g. wing/fuselage attachment.
Carbon fibre composite bolted joints
Bolzenverbindungen in Carbonfaser-Verbundwerkstoffen
Design in Composite Materials, Proc. of the I Mech E Conf. ; 2 , Mar ; 61-67
1989
7 Seiten, 7 Bilder, 3 Quellen
Aufsatz (Konferenz)
Englisch
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