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Higher production capacity thanks to automated manufacturing / Alexander Roth in JEC COMPOSITES MAGAZINE, N° 136 (09-10/2020)
[article]
Titre : Higher production capacity thanks to automated manufacturing Type de document : texte imprimé Auteurs : Alexander Roth, Auteur ; Denis Holleyn, Auteur Année de publication : 2020 Article en page(s) : p. 22-25 Langues : Anglais (eng) Catégories : Automatisation
Avions -- Matériaux
Bandes composites
Construction sandwich
Mousses plastiques
Placement automatisé de fibres
PréformesObjet constituant la majeur partie d’une pièce à fabriquer et qui nécessite un travail supplémentaire pour devenir une pièce finie. Ce terme s’utilise notamment pour le moulage, l’usinage, la taille d’outils en silex, la fabrication de fibre optique…
Productivité
Structure en nid d'abeillesIndex. décimale : 668.4 Plastiques, vinyles Résumé : Using Rohacell HERO polymethacrylimide (PMI) rigid, closed-cell structural foam core material, Evonik Resource EfficiencyGmbH successfully developed automatization production solutions for aircraft manufacturers that offer significantly higher productivity. Note de contenu : - Feasibilities studies
- Automatization investigations
- Robot lay-up preforming project
- EU CleanSky2 AFP project
- Eliminating in-service MRO problems
- Independent testing and AIMS approval
- Study conclusions
- Future application opportunities
- Fig. 1 : Comparison of honeycomb and foam in part production
- Fig. 2 : Comparison of manual and automated production
- Fig. 3a : Automated process steps for rapidly manufacturing a sandwich preform using a machined Rohacell HERO foamcore part, as carried out on the DLR Stade EVo automated production line
- Fig. 3b : Automated Fibre Placement (AFP) or Tape Laying (ATL) technology process steps for the rapid production of a sandwich composite aircraft part
- Table 1 : Technical data - Rohacell Hero PMI closed cell rigid foam core rangePermalink : https://e-campus.itech.fr/pmb/opac_css/index.php?lvl=notice_display&id=35453
in JEC COMPOSITES MAGAZINE > N° 136 (09-10/2020) . - p. 22-25[article]Réservation
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Code-barres Cote Support Localisation Section Disponibilité 22571 - Périodique Bibliothèque principale Documentaires Disponible Honeycomb fuselage panel certification by analysis / S. Leemans in SAMPE JOURNAL, Vol. 46, N° 4 (07-08/2010)
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Titre : Honeycomb fuselage panel certification by analysis Type de document : texte imprimé Auteurs : S. Leemans, Auteur ; P. J. Rohl, Auteur ; D. Huang, Auteur ; Frank Abdi, Auteur ; J. Surdenas, Auteur ; K. Raju, Auteur Année de publication : 2010 Article en page(s) : p. 30-47 Note générale : Bibliogr. Langues : Américain (ame) Catégories : Avions -- Fuselage
Avions -- Matériaux
Certification
Construction sandwich -- Rupture
Essais (technologie)
Qualité -- Contrôle
Structure en nid d'abeillesIndex. décimale : 624.18 Conception et construction avec des matériaux déterminés Résumé : The utilization of advanced composite material systems in general aviation and transport aircraft is rapidly growing. This is placing a growing demand on the certification process for composite components. parts and repairs to meet regulatory requirements and statutes. It is very desirable to establish and demonstrate the technical capability to perform "certification by analysis" to reduce test requirements, perform fatigue analysis, and predict residual strength and remaining life after damage is incurred. The objective for the present work was to demonstrate the ability to predict the failure behavior of composite structural airframe components by generating calibrated material allowables from existing ASTM coupon test data ; validating those allowables against tailored, design-specific coupon test data ; and comparing the analytical results obtained from a blind study of full-scale "fuselage" panels with test results for equivalent full-scale test sub-components. The effort focused on fuselage panel test specimens built for the "full-scale damage tolerance of composite sandwich structures" tests performed at the "full-scale aircraft structural test evaluation & research" (FASTER) fixture at the FAA's Atlantic City test facility. A systematic "building-block" approach was followed to ensure high quality results. Basic material data for the material systems used were obtained through NIAR. Verification was accomplished by comparing test and predicteed cross-ply laminate and design-specific sandwich coupon test results. After the initial steps in the "building block" process were completed, progressive failure analyses (PFA) were performed for an undamaged panel ; ant then for panels with a circular hole and circumferential slots. PFA evaluations for damage initiation, damage propagation, fracture initiation, fracture propagation and final failure of the undamaged and the various damaged curved panels were obtained. The PFA results from the independent analysis verify GENOA's capability to accurately predict panel failure strength and modes, as well as highlight the capability of GENOA to be used as a test methodology verification. Permalink : https://e-campus.itech.fr/pmb/opac_css/index.php?lvl=notice_display&id=10039
in SAMPE JOURNAL > Vol. 46, N° 4 (07-08/2010) . - p. 30-47[article]Réservation
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Code-barres Cote Support Localisation Section Disponibilité 012327 - Périodique Bibliothèque principale Documentaires Disponible Hybrid seat structures - Efficient and suitable for large-scale production / Rudolf Emmerich in PLASTICS INSIGHTS, Vol. 114, N° 1 (2024)
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Titre : Hybrid seat structures - Efficient and suitable for large-scale production : A forward-looking approach to the sustainable manufacture of hybrid components Type de document : texte imprimé Auteurs : Rudolf Emmerich, Auteur ; Sergej Ilinzeer, Auteur ; Ronny Hanich-Spahn, Auteur Année de publication : 2024 Article en page(s) : p. 42-45 Langues : Anglais (eng) Catégories : Assemblages multimatériaux
Avions -- Matériaux
Durée de vie (Ingénierie)
Matériaux -- Allègement
Recyclabilité
SiègesIndex. décimale : 668.4 Plastiques, vinyles Résumé : Seats in commercial aircraft consist of multiple components, which are usually a mixture of plastics and metals. This makes recycling difficult and increases the cost of manufacturing and maintaining the seats. Fraunhofer Institute for Chemical Technology has consequently developed an aircraft seat that not only meets requirements for space- and weight-savings and fire resistance, but is also easy to recycle. The seat consists of only five components and is suitable for large-scale production. Note de contenu : - Design of the hybrid aircraft seat structure
- Surface treatment of the metal inserts
- Production of the outer seat shell
- Production of the inner seat shell
- Assembly and crash test
- Recycling and initial life cycle analysis
- Fig. 1 : Exploded view of the seat structure which, apart from the metal inserts, is made solely of PUR
- Fig. 2 : Lower half of the mold used to create the outer seat shell: Open mold, insertion of local reinforcement, insertion of SMC material into the mold
- Fig. 3 : The outer seat shell is produced using the SMC process
- Fig. 4 : Manufacturing steps for the inner seat shell: Carbon fiber fabric in the mold, resin poured onto the fabric, cured inner seat shell
- Fig. 5 : The inner seat shell is manufactured using the WCM process
- Fig. 6 : During the crash test of the hybrid seat row, the metal anchoring of the legs to the floor plate was the first element to failEn ligne : https://drive.google.com/file/d/1_fZL-skPecBb_hUHFleZMDiwl2-1WEVw/view?usp=drive [...] Format de la ressource électronique : Permalink : https://e-campus.itech.fr/pmb/opac_css/index.php?lvl=notice_display&id=40806
in PLASTICS INSIGHTS > Vol. 114, N° 1 (2024) . - p. 42-45[article]Réservation
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Code-barres Cote Support Localisation Section Disponibilité 24500 - Périodique Bibliothèque principale Documentaires Disponible Impact on composite aircraft fuselages / Christine Espinosa in REVUE DES COMPOSITES ET DES MATERIAUX AVANCES, Vol. 24, N° 3 (07-08-09/2014)
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Titre : Impact on composite aircraft fuselages : Modeling strategies for predicting the residual strength Type de document : texte imprimé Auteurs : Christine Espinosa, Auteur ; Frédéric Lachaud, Auteur ; Laurent Michel, Auteur ; Robert Piquet, Auteur Année de publication : 2014 Article en page(s) : p. 271-318 Note générale : Bibliogr. Langues : Anglais (eng) Catégories : Analyse numérique
Avions -- Fuselage
Avions -- Matériaux
Composites -- Délaminage
Endommagement (mécanique)
Essais (technologie)
Impact (mécanique)
Modèles mathématiques
Modélisation tridimensionnelle
PlasticitéIndex. décimale : 620.1 Mécanique de l'ingénieur (mécanique appliquée) et matériaux Résumé : Computer based design using damage mechanics is thought about as a new methodology to replace tests and help deriving realistic while simple new rules for Aeronautic Certification of composite structures. Numerical methods and models must then be robust and predictive. Three different computational strategies are developed and compared : a Cohesive Model (CM), a Continuous Damage Material model coupling failure modes and damage (CDM), a Mixed Methodology (MM) using the CDM for delamination initiation and the CM for 3D crack propagation and mesh openings. The CDM model is used to simulate the impact of a composite blade on a composite fuselage section and to predict the CAI behavior of samples up to fracture. Comparisons with experiments are discussed. Note de contenu : - INTRODUCTION : Purpose and limits of this chapter - Topics and issues addressed
- DELAMINATION ANALYSIS : Cohesive Model (CM) approach - Structural behaviors with the Cohesive Model approach - Data identification and discussion
- UNIDIRECTIONAL PLY BEHAVIOR : A CONTINUOUS DAMAGE MODEL
- COUPLINGPLY DAMAGE AND 3D OPEN CRACKS BRANCHING : A MIXED METHODOLOGY : Numerical method - Principe of the models coupling
- VIRTUAL VERSUS EXPERIMENTAL TEST OF IMPACT RESISTANCE : Impact tests and damage - Cohesive model : interface elements for plies delamination - Continuum Damage Mechanics model - 3D crack opening model : Mixed Methodology - Comparing Cohesive Model and Continuous Damage Model
- BOTTOM UP : TO THE VIRTUAL TESTING OF COMPOSITE FUSELAGE : Impact damage tolerance : CAI - Impact resistance of a fuselage : a numerical approachDOI : 10.3166/rcma.24.271-318 Permalink : https://e-campus.itech.fr/pmb/opac_css/index.php?lvl=notice_display&id=21972
in REVUE DES COMPOSITES ET DES MATERIAUX AVANCES > Vol. 24, N° 3 (07-08-09/2014) . - p. 271-318[article]Réservation
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Code-barres Cote Support Localisation Section Disponibilité 16510 - Périodique Bibliothèque principale Documentaires Disponible Improved and automated non-destructive inspection methods for composite structures / Paul van IJsselstein in JEC COMPOSITES MAGAZINE, N° 87 (03/2014)
[article]
Titre : Improved and automated non-destructive inspection methods for composite structures Type de document : texte imprimé Auteurs : Paul van IJsselstein, Auteur ; Franc Buijsen, Auteur ; Herman Neukermans, Auteur Année de publication : 2014 Article en page(s) : p. 45 Langues : Anglais (eng) Catégories : Avions -- Matériaux
Composites
Contrôle non destructifIndex. décimale : 668.4 Plastiques, vinyles Résumé : Non-destructive inspection (NDI) is an important issue for maintenance and safety in the aircraft industry. The development of new techniques, better instrumentation and accumulated experience have built a reputation of solid reliability for this methodology. Note de contenu : - Collaborative project
- NDI technologyPermalink : https://e-campus.itech.fr/pmb/opac_css/index.php?lvl=notice_display&id=22974
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Code-barres Cote Support Localisation Section Disponibilité 16109 - Périodique Bibliothèque principale Documentaires Disponible In-field non-destructive bonding verification for aircraft composites / André Lamarre in JEC COMPOSITES MAGAZINE, N° 52 (10/2009)
PermalinkInfluence de cycles de cuisson rapides sur le préimprégné aéronautique M21/T700 : suivi de polymérisation et propriétés mécaniques / Christophe Paris in MATERIAUX & TECHNIQUES, Vol. 100, N° 6/7 (2012)
PermalinkInfluence de la température sur le comportement mécanique de stratifiés tissés thermoplastique ou thermodurcissable / Jérémie Aucher in REVUE DES COMPOSITES ET DES MATERIAUX AVANCES, Vol. 21, N° 3 (09-10-11-12/2011)
PermalinkInnovative dispensing technology for two-component adhesives and sealants in ADHESION - ADHESIVES + SEALANTS, Vol. 17, N° 2/2020 (2020)
PermalinkIntégration de la simulation des procédés de fabrication / Sylvain Chatel in REVUE DES COMPOSITES ET DES MATERIAUX AVANCES, Vol. 15, N° 3 (2005)
PermalinkIntended and unitended consequences of REACH / Trevor Fielding in POLYMERS PAINT COLOUR JOURNAL - PPCJ, Vol. 206, N° 4626 (11/2016)
PermalinkIntroduction de composites à matrice thermoplastiques dans les nacelles d'avion / Mehdi Marin in REVUE DES COMPOSITES ET DES MATERIAUX AVANCES, Vol. 21, N° 3 (09-10-11-12/2011)
PermalinkJonctions hybrides boulonnées-collées / Jean-François Ramière in REVUE DES COMPOSITES ET DES MATERIAUX AVANCES, Vol. 20, N° 2 (05-06-07-08/2010)
PermalinkJournées techniques SAMPE des 18 et 19 novembre 2004 à Toulouse / Society for the Advancement of Material and Process Engineering (1973-) / Covina [Etats-Unis] : Societe for the Advancement of material and Process Engineering (2004)
PermalinkLaboratory infusion test unit / Patrick Noireaux in JEC COMPOSITES MAGAZINE, N° 48 (05/2009)
PermalinkLightweight aerospace solutions in JEC COMPOSITES MAGAZINE, N° 130 (09-10/2019)
PermalinkLow-cost composite structures : how to avoid pitfalls / G. Ghilai in JEC COMPOSITES MAGAZINE, N° 74 (07-2012)
PermalinkManaging EMI grounding & lightning strike protection in JEC COMPOSITES MAGAZINE, N° 68 (10/2011)
PermalinkManufacture of nominal-shape composite stiffeners using autoclave injection / Erik Kappel in JEC COMPOSITES MAGAZINE, N° 106 (07/2016)
PermalinkManufacturing large aerospace composite structures using liquid resin infusion / Will Harris in JEC COMPOSITES MAGAZINE, N° 128 (05-06/2019)
PermalinkManufacturing overview of a 2.4 mater (7.9 foot) composite cryotank / D. A. McCarville in SAMPE JOURNAL, Vol. 49, N° 5 (09-10/2013)
PermalinkMaterial & machine for complex composites manufacturing / Max Schultes in JEC COMPOSITES MAGAZINE, N° 141 (07-08/2021)
PermalinkMatériaux pour les aéronefs : de plus en plus de composites structuraux et thermostructuraux / Roger Naslain in L'ACTUALITE CHIMIQUE, N° 11 (11/1999)
PermalinkMechanical vs. adhesive bonds in assembly / Antoine Curet in ADHESIVES & SEALANTS INDUSTRY (ASI), Vol. 20, N° 10 (10/2013)
PermalinkNano-architectures in aerospace composites / Roberto Guzman de Villoria in JEC COMPOSITES MAGAZINE, N° 72 (04-05/2012)
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