Johnson, Alastair and Toso-Pentecote, Nathalie (2007) Design and Performance of Novel Aircraft Sandwich Structures with Folded Composite Cores. In: Stretching the Endurance Boundary of Composite Materials: Pushing the Performance Limit of Composite Structures. International Scientific Meeting - Stretching the Endurance Boundary of Composite Materials: Pushing the Performance Limit of Composite Structures, 2007-09-23 - 2007-09-28, Island of Madeira (Portugal).
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Attention is focussed on novel composite sandwich structures with energy absorbing cores. These are non-standard sandwich structures, in which a main load-bearing composite laminate is protected from impact damage by an energy absorbing core and an outer cover laminate. The core materials consist of folded composite plate structures (foldcore). The DLR has been concerned with the damage tolerance of foldcore sandwich structures under more critical impact loads. A gas gun impact test programme was carried out on foldcore composite panels with projectiles such as steel cubes, ice balls and tyre rubber fragments at impact velocities in the range 50 – 220 m/s. A wide range of failure modes have been observed, ranging from rebound from the outer skin, outer skin damage, core penetration, inner skin damage and inner skin penetration. NDE methods were applied such as X-ray, lock-in thermography, ultrasonic C-scans and computer tomography (CT) to ascertain the presence and nature of the impact damage. Physical phenomena associated with impact damage and progressive collapse of such structures are complex, and predictive models and simulation tools for design and analysis are being investigated. Key issues are the development of constitutive laws for modelling composites in-ply and delamination failures, suitable models for folding and collapse in the composite cores, materials laws for soft body impactors, and the efficient implementation of the materials models into FE codes. The solution proposed here is to use meso-scale models for composites based on continuum damage mechanics (CDM) in explicit FE codes which provides a framework within which in-ply and delamination failures may be modelled.
|Document Type:||Conference or Workshop Item (Speech)|
|Title:||Design and Performance of Novel Aircraft Sandwich Structures with Folded Composite Cores|
|Journal or Publication Title:||Stretching the Endurance Boundary of Composite Materials: Pushing the Performance Limit of Composite Structures|
|Keywords:||sandwich structures, high velocity impact, folded core, gas gun tests, composite models, meso-scale models, delamination|
|Event Title:||International Scientific Meeting - Stretching the Endurance Boundary of Composite Materials: Pushing the Performance Limit of Composite Structures|
|Event Location:||Island of Madeira (Portugal)|
|Event Type:||international Conference|
|Event Dates:||2007-09-23 - 2007-09-28|
|HGF - Research field:||Aeronautics, Space and Transport (old)|
|HGF - Program:||Aeronautics|
|HGF - Program Themes:||Aircraft Research|
|DLR - Research area:||Aeronautics|
|DLR - Program:||L AR - Aircraft Research|
|DLR - Research theme (Project):||L - Structures & Materials|
|Institutes and Institutions:||Institute of Structures and Design > Structural Integrity|
|Deposited By:||Nathalie Toso|
|Deposited On:||27 Dec 2007|
|Last Modified:||27 Apr 2009 14:36|
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