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Manufacturing overview of a 2.4 mater (7.9 foot) composite cryotank / D. A. McCarville in SAMPE JOURNAL, Vol. 49, N° 5 (09-10/2013)

[article]  inSAMPE JOURNAL > Vol. 49, N° 5 (09-10/2013) . - p. 7-13 Titre : Manufacturing overview of a 2.4 mater (7.9 foot) composite cryotank Type de document : texte imprimé Auteurs : D. A. McCarville, Auteur ; J. C. Guzman, Auteur ; J. L. Sweetin, Auteur ; J. R. Jackson, Auteur ; L. Pelham, Auteur ; J. Steenland, Auteur ; C. W. Petersen, Auteur Année de publication : 2013 Article en page(s) : p. 7-13 Note générale : Bibliogr. Langues : Américain (ame) Catégories : Avions -- Matériaux Composites à fibres Contrôle non destructif Hors autoclave (technologie) Industries aérospatiales -- Matériaux Procédés de fabrication Réservoirs (récipients) -- Conception et construction Stratifiés Index. décimale : 620.11 Matériaux (propriétés, résistance) Résumé : As part of the Space Technology Game Changing Development Program (GCDP) Composite Cryotank Technology Development (CCTD) contract, Boeing fabricated a 2.4 m diameter test article as a precursor to a 5.5 meter cryotank design, fabrication, and test. This component encompasses several challenging design features: (a) one-piece co-cured/co-bonded spherical geometry with integral skirts, (b) out-of-autoclave curing materials, (c) permeation resistant thin/hybrid ply laminate skins, and (d) thin and thick off-angle slit tape (tow) construction. The component was built on a 24 piece collapsible composite tool using robotic fiber placement. This paper details the tooling and manufacturing flow with an emphasis on process development building block activities. Cessons leamed are compiled that will be used to help guide the build of a 5.5 m diameter tank during the next phase of the CCTD contract. Note de contenu : - INTRODUCTION : CCTD program background - Cryotank design overview - Cryotank manufacturing overview - PRECURSOR TANK TOOLING : Tank tool design - Spindle and skirt tooling - Tank tool fabrication - PRECURSOR MANUFACTURING : Manufacturing summary - Facilities and equipment - Tank automated fiber placement - Fluted core manufacture - Cryotank nondestructive inspection Permalink : https://e-campus.itech.fr/pmb/opac_css/index.php?lvl=notice_display&id=19262 [article]

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Composites failure criteria - An important factor in composites design / Scott W. Beckwith in SAMPE JOURNAL, Vol. 49, N° 5 (09-10/2013)

[article]  inSAMPE JOURNAL > Vol. 49, N° 5 (09-10/2013) . - p. 30-31 Titre : Composites failure criteria - An important factor in composites design Type de document : texte imprimé Auteurs : Scott W. Beckwith, Auteur ; R. B. Heslehurst, Auteur Année de publication : 2013 Article en page(s) : p. 30-31 Langues : Américain (ame) Catégories : Matériaux -- Détérioration Matériaux -- Propriétés mécaniques Résistance des matériaux Rupture (mécanique) Index. décimale : 620.11 Matériaux (propriétés, résistance) Résumé : This short overview is part of a new tutorial being developed for SAMPE Tech 2013 (Wichita) on the topic of composites failure criteria. The upcoming tutorial will cover significantly more information and technology areas with respect to various aspects of different failure criteria and the use of safety factors and required testing. In general, composite structures and products are often designed and manufactured to various industry standards with their structural verification measured against a failure criteria and subsequent testing. At least that is often the intended plan or approach used within the composites industry by most reputable manufacturers. Permalink : https://e-campus.itech.fr/pmb/opac_css/index.php?lvl=notice_display&id=19269 [article]

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Thermoplastic composites technologies for manufacturing nose fuselage structures / P. Lefebure in SAMPE JOURNAL, Vol. 49, N° 5 (09-10/2013)

[article]  inSAMPE JOURNAL > Vol. 49, N° 5 (09-10/2013) . - p. 32-41 Titre : Thermoplastic composites technologies for manufacturing nose fuselage structures Type de document : texte imprimé Auteurs : P. Lefebure, Auteur ; J.-M. Guimard, Auteur Année de publication : 2013 Article en page(s) : p. 32-41 Note générale : Bibliogr. Langues : Américain (ame) Catégories : Avions -- Fuselage Avions -- Matériaux Chauffage laser Composites thermoplastiques Composites thermoplastiques -- Propriétés mécaniques Métallisation Résistance au chocs Soudage Index. décimale : 668.4 Plastiques, vinyles Résumé : In the framework of the French national DPAC COMP TP (Thermoplastic) Program, EADS IW has continued its long term efforts on the development of thermoplastic composites technologies for aeronautics structural applications. Most of the research and development activities were focused on the manufacture of "nase" fuselage parts, such as skin panels and stringers and (or) frames, and on the development of TP welding processes. Aircraft windshield front fairings were estimated as good candidates for thermoplastics technologies among all the aeronautic nase fuselage parts. Therefore this paper will discuss the recent developments led by EADS IW, for manufacturing a technological demonstrator, whose main specifications are: - Thick part (compared to fuselage skins thicknesses) for potential impact resistance properties - Geometry with severe double curvatures - Use of cost-effective manufacturing processes These specifications led to a development program that encompassed the following activities: - Determination and validation of process limits for TP parts consolidation in aven. - Automated lay down technique for TP multi-tows deposition with a laser heating system. - Panel metallization, for LSP application, with a laser TP tape deposition machine. - Press-forming process for manufacture of thick and double curvature stiffeners. - Specific welding process and understanding the mixing of different high performance thermoplastic materials. A specific design of a representative Thermoplastic CFRC Panel has been created and the associated technological demonstrator is manufactured for validation of the different related development works. Mechanical performance, detailed structural sizing and actual impact resistance of such a component will be addressed at a later date in another development program. Note de contenu : - AUTOMATED TP FIBRE PLACEMENT PROCESS WITH LASER HEATING SYSTEM - HARMFUL IMPACT OF THE POROSITY IN THERMOPLASTIC COMPOSITE PARTS - CONSOLIDATION OF PROUS LAMINATES - MECHANICAL TESTS : FHC (Filled Hole Compression) tests - After impact compression tests - METALLIZATION OF LARGE CURVED TP CFRC PANELS - INFLUENCE OF AN AUTOMATED DEPOSITION PROCESS ON LIGHTNING STRIKE BEHAVIOUR - TECHNOLOGY ADAPTATION TO A MULTI-TOW PLACEMENT MACHINE WITH LASER HEATING SYSTEM - EADS IW TECHNOLOGICAL DEMONSTRATOR :Part design - Skin manufacture - Frames manufacture - Skin-frames welding feasibility Permalink : https://e-campus.itech.fr/pmb/opac_css/index.php?lvl=notice_display&id=19270 [article]

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High temperature RTM370 polyimide composites fabricated by RTM : characterization and impact testing / K. C. Chuang in SAMPE JOURNAL, Vol. 49, N° 5 (09-10/2013)

[article]  inSAMPE JOURNAL > Vol. 49, N° 5 (09-10/2013) . - p. 48-57 Titre : High temperature RTM370 polyimide composites fabricated by RTM : characterization and impact testing Type de document : texte imprimé Auteurs : K. C. Chuang, Auteur ; D. M. Revilock, Auteur ; J. M. Pereira, Auteur ; J. M. Criss, Auteur ; E. A. Mintz, Auteur Année de publication : 2013 Article en page(s) : p. 48-57 Note générale : Bibliogr. Langues : Américain (ame) Catégories : Avions -- Matériaux Caractérisation Composites à fibres de carbone -- Propriétés mécaniques Composites thermoplastiques -- Propriétés mécaniques Essais de résilience Matériaux -- Imprégnation Moulage par transfert de résine sous vide Polyimides Résistance au chocs Résistance des matériaux Index. décimale : 668.4 Plastiques, vinyles Résumé : RTM370 imide resin based on 2,3,3',4'-biphenyl dianhydride (a-BPDA), 3,4'-oxydianiline (3,4'-ODA) and terminated with the 4-phenylethynylphthalic (PEPA) endcap has been shown to exhibit a low melt viscosity (10-30 poise) et 280°C with a pot-life of 1-2 h and a high cured Tg of 370°C. RTM370 resin has been successfully fabricated into composites reinforced with T650-35 car-bon fabrics by resin transfer molding (RTM). RTM370 composites displays excellent mechanical properties up to 327°C (620°F), and outstanding property retention after aging at 288°C (550°F) for 1000 h, and under hot-wet conditions. RTM370 triaxial braided composites were subjected to impact test with projectiles, and exhibited enhanced energy absorption at 288°C (550°F) compared to ambient temperature. Note de contenu : - EXPERIMENTAL : Resin preparation and characterization - Composite fabrication - RESULTS AND DISCUSSION : Physical properties and viscosity profile of RTM370 imide oligomers and cured resin - RTM370 composite fabrication, characterization - RTM370/T650-35/8HS/polyimide sizing - Triaxial braided RTM370/650-35 composites - Impact study of RTM370/triaxial braided T650-35 composites - Table 1 : Physical properties of RTM370 imide resin - Table 2 : Mechanical properties of RTM370/8HS fabric compare to BMI-5270-1 - Table 3 : Durability of RTM370 composites/T650-35-/8HS/HTG sizing) at 288°C - Table 4 : Hot-wet property of RTM370/T650-35 composites with polyimide sizing Permalink : https://e-campus.itech.fr/pmb/opac_css/index.php?lvl=notice_display&id=19271 [article]

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