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Damage Tolerance of Pre-stressed Composite Panels Under Impact Loads

Johnson, A.F. and Toso-Pentecôte, Nathalie and Schueler, Dominik (2014) Damage Tolerance of Pre-stressed Composite Panels Under Impact Loads. CEAS Aeronautical Journal. Springer. DOI: 10.1007/s10443-013-9383-y ISSN 1869-5590

Full text not available from this repository.

Abstract

An experimental test campaign studied the structural integrity of carbon fibre/epoxy panels preloaded in tension or compression then subjected to gas gun impact tests causing significant damage. The test programme used representative composite aircraft fuselage panels composed of aerospace carbon fibre toughened epoxy prepreg laminates. Pre-load levels in tension were representative of design limit loads for fuselage panels of this size, and maximum compression preloads were in the post-buckle region. Two main impact scenarios were considered: notch damage from a 12 mm steel cube projectile, at velocities in the range 93 – 136 m/s; blunt impact damage from 25 mm diameter glass balls, at velocities 64 – 86 m/s. The combined influence of preload and impact damage on panel residual strengths was measured and results analysed in the context of damage tolerance requirements for composite aircraft panels. The tests showed structural integrity well above design limit loads for composite panels preloaded in tension and compression with visible notch impact damage from hard body impact tests. However, blunt impact tests on buckled compression loaded panels caused large delamination damage regions which lowered plate bending stiffness and reduced significantly compression strengths in buckling.

Item URL in elib:https://elib.dlr.de/87960/
Document Type:Article
Title:Damage Tolerance of Pre-stressed Composite Panels Under Impact Loads
Authors:
AuthorsInstitution or Email of AuthorsAuthors ORCID iD
Johnson, A.F.BK-SINUNSPECIFIED
Toso-Pentecôte, Nathalienathalie.toso (at) dlr.deUNSPECIFIED
Schueler, Dominikdominik.schueler (at) dlr.deUNSPECIFIED
Date:January 2014
Journal or Publication Title:CEAS Aeronautical Journal
Refereed publication:Yes
Open Access:No
Gold Open Access:No
In SCOPUS:Yes
In ISI Web of Science:No
DOI :10.1007/s10443-013-9383-y
Publisher:Springer
Series Name:CEAS Aeronautical Journal
ISSN:1869-5590
Status:Published
Keywords:carbon fibre/epoxy laminates, high velocity impact tests, impact damage in pre-stressed plates, damage tolerance of composites
HGF - Research field:Aeronautics, Space and Transport
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: Stuttgart
Institutes and Institutions:Institute of Structures and Design > Structural Integrity
Deposited By: Toso, Dr.-Ing. Nathalie
Deposited On:30 Jan 2014 11:28
Last Modified:08 Mar 2018 19:01

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