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Design and Performance of Novel Aircraft Sandwich Structures with Folded Composite Cores

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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Abstract

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
Authors:
AuthorsInstitution or Email of Authors
Johnson, AlastairUNSPECIFIED
Toso-Pentecote, NathalieUNSPECIFIED
Date:September 2007
Journal or Publication Title:Stretching the Endurance Boundary of Composite Materials: Pushing the Performance Limit of Composite Structures
Editors:
EditorsEmail
University of Cambridge, UNSPECIFIED
Engineering and Physical Sciences Research Council (UK), UNSPECIFIED
National Sciences Foundation (USA), UNSPECIFIED
Status:Published
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
Location: Stuttgart
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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