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This paper presents the results from a study of the in-plane (interlamina) shear characteristics of specific CFRP with a particular balanced lay-up of 12 ply cured laminates. This study involved a detailed experimental program to determine the material properties. The material properties were used for the failure analysis of a new type of fastener joint for composite laminates, which has a potential use in the aerospace industry. Twenty shear tests were carried out using a minimum of 6 specimens for every lay-up. Although some thickness tolerances issues were caused by using different laminate lay-ups, all other geometric parameters were kept similar. Ply failures were observed for 45°/90°, 45°, 90° specimens. An FE model was also developed for each particular lay-up and compared against the test data. It was also used to determine why each coupon failed in a certain way. The FE model uses 2D unsymmetrical material properties with shell elements representing the thickness. In terms of boundary conditions the model was constrained at one end of the specimen and in two directions with a compressive load applied at the other end.

Describes preliminary structural design work on a notional uninhabited tactical aircraft (UTA), carried out at Cranfield University. UTAs are seen as an important future element of military fleets. A notional baseline requirement was derived, leading to the evolution of a design solution. The basic requirements for such a UTA are naturally highly classified but, although industry has been hesitant to comment, the baseline requirements and design solution developed herein are believed to be reasonable.