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

Johnson, Alastair und 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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Kurzfassung

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.

Dokumentart:Konferenzbeitrag (Vortrag)
Titel:Design and Performance of Novel Aircraft Sandwich Structures with Folded Composite Cores
Autoren:
AutorenInstitution oder E-Mail-Adresse der Autoren
Johnson, AlastairNICHT SPEZIFIZIERT
Toso-Pentecote, NathalieNICHT SPEZIFIZIERT
Datum:September 2007
Erschienen in:Stretching the Endurance Boundary of Composite Materials: Pushing the Performance Limit of Composite Structures
Herausgeber:
HerausgeberInstitution und/oder E-Mail-Adresse der Herausgeber
University of Cambridge, NICHT SPEZIFIZIERT
Engineering and Physical Sciences Research Council (UK), NICHT SPEZIFIZIERT
National Sciences Foundation (USA), NICHT SPEZIFIZIERT
Status:veröffentlicht
Stichwörter:sandwich structures, high velocity impact, folded core, gas gun tests, composite models, meso-scale models, delamination
Veranstaltungstitel:International Scientific Meeting - Stretching the Endurance Boundary of Composite Materials: Pushing the Performance Limit of Composite Structures
Veranstaltungsort:Island of Madeira (Portugal)
Veranstaltungsart:internationale Konferenz
Veranstaltungsdatum:2007-09-23 - 2007-09-28
HGF - Forschungsbereich:Verkehr und Weltraum (alt)
HGF - Programm:Luftfahrt
HGF - Programmthema:Starrflügler
DLR - Schwerpunkt:Luftfahrt
DLR - Forschungsgebiet:L AR - Starrflüglerforschung
DLR - Teilgebiet (Projekt, Vorhaben):L - Strukturen & Werkstoffe
Standort: Stuttgart
Institute & Einrichtungen:Institut für Bauweisen- und Konstruktionsforschung > Strukturelle Integrität
Hinterlegt von: Nathalie Toso
Hinterlegt am:27 Dez 2007
Letzte Änderung:27 Apr 2009 14:36

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