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Design Methodology for Damage tolerant Composite Wing Panels

Gädke, M. (2000) Design Methodology for Damage tolerant Composite Wing Panels. Garteur MS AG 22 8th Progress Meeting, Hamburg-Finkenwerder, 15.-16.11.2000.

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Abstract

In co-operation with the partners in the GARTEur SM AG 22 an analytical approach for modelling and calculation of the impact behaviour of composites was developed during the past years in the Institute of Structural Mechanics. The main features of the approach are · an independent damage characterisation method; · a new failure criterion for delamination damage; · a simple model for the prediction of impact damage, based on the bending strain energy density and · an algorithm for the residual strength analysis of single and/or multiple delaminations, either introduced by impact or pre-implanted. The approach led to the development of the Windows and NT compatible computer program COmposite Damage Tolerance Analysis Code (CODAC), which enables the calculation of the impact transient response, the impact damage and consequently the residual compressive strength of composite laminates and stringer stiffened panels..

Document Type:Conference or Workshop Item (Speech)
Additional Information: LIDO-Berichtsjahr=2001,
Title:Design Methodology for Damage tolerant Composite Wing Panels
Authors:
AuthorsInstitution or Email of Authors
Gädke, M.UNSPECIFIED
Date:2000
Status:Published
Event Title:Garteur MS AG 22 8th Progress Meeting, Hamburg-Finkenwerder, 15.-16.11.2000
Organizer:EADS
HGF - Research field:Aeronautics, Space and Transport (old)
HGF - Program:Aeronautics
HGF - Program Themes:other
DLR - Research area:Aeronautics
DLR - Program:L ST - Starrflüglertechnologien
DLR - Research theme (Project):UNSPECIFIED
Location: Braunschweig
Institutes and Institutions:Institute of Composite Structures and Adaptive Systems > Institut für Strukturmechanik
Deposited By: Sibylle Wolff
Deposited On:16 Sep 2005
Last Modified:14 Jan 2010 16:00

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