Improving composite damage modelling through automatic placement of cohesive elements

Numerous experimental studies of damage in composite laminates have shown that intralaminar (in-plane) matrix cracks lead to interlaminar delamination (out-of-plane) at ply interfaces. The smearing of in-plane cracks over a volume, as a consequence of the use of continuum damage mechanics, does not always effectively capture the full extent of the interaction between the two failure mechanisms. A more accurate representation is obtained by adopting a discrete crack approach via the use of cohesive elements, for both in-plane and out-of-plane damage. The difficulty with cohesive elements is that their location must be determined a priori in order to generate the model; while ideally the position of the crack migration, and more generally the propagation path, should be obtained as part of the problem’s solution. With the aim of enhancing current modelling capabilities with truly predictive capabilities, a concept of automatic insertion of interface elements is utilized. The consideration of a simple traction criterion in relation to material strength, evaluated at each node of the model (or of the regions of the model where it is estimated cracks might form), allows for the determination of initial crack location and subsequent propagation by the insertion of cohesive elements during the course of the analysis. Several experimental results are modelled using the commercial package ABAQUS/Standard with an automatic insertion subroutine developed in this work, and the results are presented to demonstrate the capabilities of this technique.

Aerospace Stiffened Panel Initial Sizing With Novel Skin Sub-Stiffening Features

The introduction of skin sub-stiffening features has the potential to modify the local stability and fatigue crack growth performance of stiffened panels. Proposed herein is a method to enable initial static strength sizing of panels with such skin sub-stiffening features. The method uses bespoke skin buckling coefficients, automatically generated by Finite Element analysis and thus limits the modification to the conventional aerospace panel initial sizing process. The approach is demonstrated herein and validated for prismatic sub-stiffening features. Moreover, examination of the generated buckling coefficient data illustrates the influence of skin sub-stiffening on buckling behavior, with static strength increases typically corresponding to a reduction in the number of initial skin longitudinal buckle half-waves.

The Financial Accountability of Irish Credit Unions: an initial empirical study

Credit unions are member-owned, voluntary, self-help, democratic, not-for-profit institutions that provide financial services to their members. They have both economic and social goals. Over this last decade they have achieved remarkable growth levels and currently there are 600 such organisations in Ireland, with approximately 50 per cent of the adult population of Ireland belonging to a credit union. Accounting for credit unions is a much-neglected area and relatively little is known about the sector's accountability. This paper presents the results of an initial empirical study of the financial accountability of Irish credit unions. A series of interviews and a basic content analysis of 178 recent financial statements were used to identify the views of key stakeholders with respect to the discharge of financial accountability by credit unions and the current quality of financial reporting. Overall, the research points to a sector where financial accountability through the medium of the annual report is weak and possible adverse consequences of this are explored. On the basis of the interviews it is suggested that if changes in financial accountability are to be achieved then some more proactive engagement of parties external to the management of individual credit unions is needed.