Abstract
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.
| Original language | English |
|---|---|
| Number of pages | 23 |
| Journal | International Journal of Structural Stability and Dynamics |
| Volume | 12 |
| Issue number | 5 |
| DOIs | |
| Publication status | Published - Oct 2012 |
Bibliographical note
Submitted for 2014 REF Assessment, with following 100 words:This paper details a novel design methodology for buckling containment features on aerospace components. The design approach enables accurate and efficient analysis of advanced structural geometries, suitable for both preliminary and detailed design. The developed methodology has been rigorously validated experimentally and can yield significant airframe weight reductions in relation to traditional design practices. The research output has been distributed to Alcan CRV (Frederic Bron) for implementation in their design tool suite, and led to further collaborative funding with Bombardier Aerospace Belfast (Ken Poston, Head of Advanced Metallics: Strategic Technologies,), and Alcan CRV.