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Degradation investigation in a postbuckling composite stiffened fuselage panel

Orifici, Adrian and Thomson, R.S. and Degenhardt, Richard and Kling, Alexander and Rohwer, Klaus and Bayandor, J. (2005) Degradation investigation in a postbuckling composite stiffened fuselage panel. 13. International Conference of Composite Structures, 2005-11-14 - 2005-11-16, Melbourne, Australien.

Full text not available from this repository.

Abstract

The European Commission Project COCOMAT (Improved MATerial Exploitation at Safe Design of COmposite Airframe Structures by Accurate Simulation of COllapse) is a currently running four-year project that aims to exploit the large strength reserves of composite structures through a more accurate prediction of collapse. Accordingly, one of the COCOMAT work packages involves the design of test panels with a focus on investigating the progression of composite damage mechanisms. This paper presents the collaborative results of some of the partners for this task. Different design alternatives were investigated for fuselage-representative test panels. Non-linear structural analyses were performed using MSC.Nastran (Nastran) and ABAQUS/Standard (Abaqus). Numerical predictions were also made applying a stress-based adhesive degradation model, previously implemented into a material user subroutine for Abaqus. Following this, a fracture mechanics analysis using Nastran was performed along all interfaces between the skin and stiffeners, to examine the stiffener disbonding behaviour of each design. On the basis of the structural and fracture mechanics analyses, a design was selected as being the most suitable for the experimental investigation within COCOMAT. Though the COCOMAT panels have yet to be manufactured and tested, experimental data on the structural performance and damage mechanisms were available from a separate project for a panel identical to the selected design. This data was compared to the structural, degradation and fracture mechanics predictions made using non-linear finite element solutions, and the application of the design within the COCOMAT project was discussed.

Item URL in elib:https://elib.dlr.de/50769/
Document Type:Conference or Workshop Item (Speech)
Title:Degradation investigation in a postbuckling composite stiffened fuselage panel
Authors:
AuthorsInstitution or Email of AuthorsAuthors ORCID iD
Orifici, AdrianSchool of Aerospace, Mechanical & Manufacturing Engineering, Royal Melbourne Institute of Technology,UNSPECIFIED
Thomson, R.S.Cooperative Research Centre for Advanced Composite Structures LimitedUNSPECIFIED
Degenhardt, RichardUNSPECIFIEDUNSPECIFIED
Kling, AlexanderUNSPECIFIEDUNSPECIFIED
Rohwer, KlausUNSPECIFIEDUNSPECIFIED
Bayandor, J.Sir Lawrence Wackett Centre for Aerospace Design Technology, Royal MelbourneUNSPECIFIED
Date:November 2005
Open Access:No
Gold Open Access:No
In SCOPUS:No
In ISI Web of Science:No
Keywords: Composite, postbuckling stiffened panels, skin-stiffener disbonding, COCOMAT
Event Title:13. International Conference of Composite Structures
Event Location:Melbourne, Australien
Event Type:international Conference
Event Dates:2005-11-14 - 2005-11-16
HGF - Research field:Aeronautics, Space and Transport (old)
HGF - Program:Aeronautics
HGF - Program Themes:Aircraft Research (old)
DLR - Research area:Aeronautics
DLR - Program:L AR - Aircraft Research
DLR - Research theme (Project):L - Structures & Materials (old)
Location: Braunschweig
Institutes and Institutions:Institute of Composite Structures and Adaptive Systems > Structural Mechanics
Deposited By: Ries, Doris
Deposited On:08 Aug 2007
Last Modified:27 Apr 2009 14:13

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