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Design and performance of novel aircraft structures with folded composite cores

Johnson, Alastair and Kilchert, Sebastian and Fischer, Sebastian and Toso-Pentecôte, Nathalie (2015) Design and performance of novel aircraft structures with folded composite cores. In: Structural Integrity and Durability of Advanced Composites - Innovative Modellíng Methods and Intelligent Design Woodhead Publishing Series in Composites Science and Engineering (57). Woodhead Publishing. pp. 793-827. ISBN 978-0-08-100137-0.

Full text not available from this repository.

Abstract

This chapter focuses on novel sandwich structures with open cellular composite cores manufactured by folding thin sheet base materials into a three-dimensional structure. Folded composite cores or ‘foldcore’ manufactured from resin impregnated aramid paper have similar densities and mechanical properties to Nomex honeycomb. Furthermore, they allow ventilation to prevent moisture build-up due to their open cell design and can be manufactured cost-efficiently in a continuous process. In aircraft fuselages, a sandwich design concept could yield significant weight savings compared to an aluminium reference fuselage, through increasing frame spacing and elimination of stringers. The foldcore concept is described with typical base sheet materials, core geometries, and fabrication technology suitable for continuous manufacturing processes. Folded core properties and design are discussed with test methods used for measuring thin base sheet properties and determining core through-thickness compression and shear failure modes and strength properties. Core design is based on micromechanics cell models used in FE methods for simulating progressive damage and collapse mechanisms to provide core properties for use in sandwich structural analysis and design of sandwich structures. Finally, the damage tolerance of sandwich panels with carbon fibre/ epoxy skins and aramid fibre/phenolic folded core is discussed, based on experimental investigations by drop tower and gas gun impact tests. Comparison between observed and computed failure behaviour for a range of impact load cases shows good agreement, indicating that the FE methods could provide the basis for design and certification of these advanced aircraft sandwich structures.

Item URL in elib:https://elib.dlr.de/101333/
Document Type:Book Section
Title:Design and performance of novel aircraft structures with folded composite cores
Authors:
AuthorsInstitution or Email of AuthorsAuthors ORCID iD
Johnson, Alastairalastair.johnson (at) dlr.deUNSPECIFIED
Kilchert, Sebastiansebastian.kilchert (at) dlr.deUNSPECIFIED
Fischer, SebastianUniversity of Stuttgart, Institute of Aircraft DesignUNSPECIFIED
Toso-Pentecôte, Nathalienathalie.toso (at) dlr.deUNSPECIFIED
Date:2015
Journal or Publication Title:Structural Integrity and Durability of Advanced Composites - Innovative Modellíng Methods and Intelligent Design
Refereed publication:Yes
Open Access:No
Gold Open Access:No
In SCOPUS:No
In ISI Web of Science:No
Page Range:pp. 793-827
Editors:
EditorsEmail
Beaumont, P.W.R.Cambridge University Engineering Department
Soutis, C.University of Manchester
Hodzic, A.UNSPECIFIED
Publisher:Woodhead Publishing
Series Name:Woodhead Publishing Series in Composites Science and Engineering
ISBN:978-0-08-100137-0
Status:Published
Keywords:impact simulation, impact test, foldcore, damage tolerance
HGF - Research field:Aeronautics, Space and Transport
HGF - Program:Aeronautics
HGF - Program Themes:fixed-wing aircraft
DLR - Research area:Aeronautics
DLR - Program:L AR - Aircraft Research
DLR - Research theme (Project):L - Structures and Materials
Location: Stuttgart
Institutes and Institutions:Institute of Structures and Design > Structural Integrity
Deposited By: Toso, Dr.-Ing. Nathalie
Deposited On:13 Jan 2016 16:12
Last Modified:10 May 2016 23:39

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