Data · dataset · 2026
Understanding buckling containment feature for aerospace panel design
Listed in ZivaHub and Deakin Research Online and DMU Figshare — shown once because both records carry DOI 10.17034/32637540.v1
To improve further aircraft structural performance requires practical design changes and better incorporation of advanced technologies.
Description
Instability failure modes typically constrain aerospace panel designs because buckling occurs at stresses less than that of material yield. Buckling containment features, small stiffeners located across the skin bay between the primary stiffeners/stringers, provide the ability to significantly improve panel-buckling stresses and thus exploit the full potential of available materials. <br><br>Inclusion of buckling containment features into industrial panel sizing procedures is constrained by the current inability to robustly predict and understand the complex buckling behaviour.
To aid inclusion requires a novel design approach that facilitates the extraction of understanding and selection of the optimum design.<br><br>The project developed a finite element modelling methodology that permits robust buckling behaviour prediction of plates with buckling containment features. A novel design chart presents compression and shear loading buckling behaviour predictions that are applicable to both high load intensity wing and low load intensity fuselage applications.
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Interrogation of the design charts enhances current understanding of how plates with buckling containment features buckle.<br><br>An experimental verification indicates the finite element modelling methodology to be accurate to within approximately 20 % and 7 % for initial and collapse buckling behaviour respectively. These deviations result from differences between the configuration of the finite element modelling methodology, the design of the test specimens, and the experimental setup.<br><br>The work develops the first theoretical compression buckling framework for predicting PBCF buckling behaviour subject to compression loading.
A verification process against predictions finite element analysis indicates a correlation error of less than 5 % when considering structure of aspect ratio greater than three. Furthermore, using regression analysis and finite element analysis, the work develops a computationally efficient closed-form means to predict PBCF buckling behaviour that is suitable for inclusion into early (conceptual/preliminary) aerospace panel sizing procedures.
Links
Where it is published
- DOI doi.org/10.17034/32637540.v1 ↗
DOI / persistent id · from zivahub uct ac za
Catalogue records · 1
- OAI-PMH record api.figshare.com/v2/oai?verb=GetRecord&metadataPrefix=oai_dc&identifier=oai%3Af… ↗
metadata API · from zivahub uct ac za
Topics
Provenance · 3 source records, 7 field assertions
| Source | Key | Last seen | Raw |
|---|---|---|---|
| ZivaHub | oai:figshare.com:article/32637540 | 10 d ago | JSON v1 |
| Deakin Research Online | oai:figshare.com:article/32637540 | 10 d ago | JSON v1 |
| DMU Figshare | oai:figshare.com:article/32637540 | 10 d ago | JSON v1 |
| Field | Assertion | Extractor | Evidence |
|---|---|---|---|
| concepts[field].local:field:earth-environmental | mapping · zivahub uct ac za | connector:zivahub_uct_ac_za@1.0.0 | |
| concepts[field].local:field:earth-environmental | mapping · figshare dmu ac uk | connector:figshare_dmu_ac_uk@1.0.0 | |
| concepts[field].local:field:earth-environmental | mapping · dro deakin edu au | connector:dro_deakin_edu_au@1.0.0 | |
| description | source · zivahub uct ac za | connector:zivahub_uct_ac_za@1.0.0 | /metadata/dc/description |
| license_text | source · zivahub uct ac za | connector:zivahub_uct_ac_za@1.0.0 | |
| publication_date | source · zivahub uct ac za | connector:zivahub_uct_ac_za@1.0.0 | |
| title | source · zivahub uct ac za | connector:zivahub_uct_ac_za@1.0.0 | /metadata/dc/title |