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Design and performance of novel aircraft structures with folded composite cores

Johnson, Alastair und Kilchert, Sebastian und Fischer, Sebastian und 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. Seiten 793-827. ISBN 978-0-08-100137-0.

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Kurzfassung

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.

elib-URL des Eintrags:https://elib.dlr.de/101333/
Dokumentart:Beitrag in einem Lehr- oder Fachbuch
Titel:Design and performance of novel aircraft structures with folded composite cores
Autoren:
AutorenInstitution oder E-Mail-AdresseAutoren-ORCID-iD
Johnson, Alastairalastair.johnson (at) dlr.de
Kilchert, Sebastiansebastian.kilchert (at) dlr.de
Fischer, SebastianUniversity of Stuttgart, Institute of Aircraft Design
Toso-Pentecôte, Nathalienathalie.toso (at) dlr.de
Datum:2015
Erschienen in:Structural Integrity and Durability of Advanced Composites - Innovative Modellíng Methods and Intelligent Design
Referierte Publikation:Ja
Open Access:Nein
Gold Open Access:Nein
In SCOPUS:Nein
In ISI Web of Science:Nein
Seitenbereich:Seiten 793-827
Herausgeber:
HerausgeberInstitution und/oder E-Mail-Adresse der HerausgeberHerausgeber-ORCID-iD
Beaumont, P.W.R.Cambridge University Engineering Department
Soutis, C.University of Manchester
Hodzic, A.
Verlag:Woodhead Publishing
Name der Reihe:Woodhead Publishing Series in Composites Science and Engineering
ISBN:978-0-08-100137-0
Status:veröffentlicht
Stichwörter:impact simulation, impact test, foldcore, damage tolerance
HGF - Forschungsbereich:Luftfahrt, Raumfahrt und Verkehr
HGF - Programm:Luftfahrt
HGF - Programmthema:Flugzeuge
DLR - Schwerpunkt:Luftfahrt
DLR - Forschungsgebiet:L AR - Aircraft Research
DLR - Teilgebiet (Projekt, Vorhaben):L - Strukturen und Werkstoffe (alt)
Standort: Stuttgart
Institute & Einrichtungen:Institut für Bauweisen und Strukturtechnologie > Strukturelle Integrität
Hinterlegt von: Toso, Dr.-Ing. Nathalie
Hinterlegt am:13 Jan 2016 16:12
Letzte Änderung:10 Mai 2016 23:39

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