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Prepreg non-autoclave manufacturing technology : program overview and co-cure enablers for disruptive, pervasive use / Gary G. Bond in SAMPE JOURNAL, Vol. 48, N° 5 (09-10/2012)  

[article]  inSAMPE JOURNAL > Vol. 48, N° 5 (09-10/2012) . - p. 8-15 Titre : Prepreg non-autoclave manufacturing technology : program overview and co-cure enablers for disruptive, pervasive use Type de document : texte imprimé Auteurs : Gary G. Bond, Auteur ; Gail L. Hahn, Auteur ; K. M. Jost, Auteur ; T. Storage, Auteur Année de publication : 2012 Article en page(s) : p. 8-15 Note générale : Bibliogr. Langues : Américain (ame) Catégories : Composites Hors autoclave (technologie) Matériaux -- Imprégnation Index. décimale : 668.4 Plastiques, vinyles Résumé : In 2007, non-autoclave manufacturing technology was initiated by a boeing-led team and the U.S. government (DARPA) under the guidance of the Air Force to enable disruptive, pervasive use of vacuum-bag-only prepreg for reduced recurring cost and cycle time for primary composite structures. This paper will provide a program overview as well as focusing specifically on composite co-curing technology out of the autoclave. Composite co-cures can be complicated and difficult to repeatedly produce with high quality. Factors that can contribute to these difficulties include autoclave pressure and the flow of the resin. By moving to out-of-autoclave systems, improvements in quality by reducing pressure and resin flow are achievable. Through the DARPA/Boeing co-funded, Air Force guided program non-autoclave manufacturing technology, two different co-cure designs were evaluated. The first was an existing production co-cure utilizing production tooling and engineering but substituting Cytec's toughened epoxy non-autoclave system 5320-1 for the baseline autoclave system. The second non-autoclave co-cure was a new design for a cooling outer aft duct (COAD) that utilized a novel large-scale tooling concept for the co-cured stiffeners. Non-destructive evaluation (ultrasonic inspection) and visual inspection were conducted on both co-cured structures and demonstrated that reduced resin flow and pressure during cure does improve some aspects of co-cure quality. Note de contenu : - EXPERIMENTATION : Program developmental approach - The path to very large structures - Fabrication of complex co-cure production structure (CCPS) - Cooling outer aft duct (COAD) - RESULTS : Complex co-cure production structure (CCPS) results - Cooling outer aft duct (COAD) results En ligne : http://vucoe.drbriansullivan.com/wp-content/uploads/Out-of-Autoclave-SAMPE-artic [...] Format de la ressource électronique : Pdf Permalink : https://e-campus.itech.fr/pmb/opac_css/index.php?lvl=notice_display&id=16078 [article]

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Approach to optimizing a combined out-of-autoclave (OOA) prepreg/liquid composite molding (LCM) process for integrated structures / Claudio di Fratta in SAMPE JOURNAL, Vol. 48, N° 5 (09-10/2012)

[article]  inSAMPE JOURNAL > Vol. 48, N° 5 (09-10/2012) . - p. 40-46 Titre : Approach to optimizing a combined out-of-autoclave (OOA) prepreg/liquid composite molding (LCM) process for integrated structures Type de document : texte imprimé Auteurs : Claudio di Fratta, Auteur ; Mario Danzi, Auteur ; Veit Gabathuler, Auteur ; Markus Zogg, Auteur ; Paulo Ermanni, Auteur Année de publication : 2012 Article en page(s) : p. 40-46 Note générale : Bibliogr. Langues : Américain (ame) Catégories : Composites thermoplastiques -- Moulage par infusion Composites thermoplastiques -- Moulage par injection Hors autoclave (technologie) Matériaux -- Imprégnation Moulage par transfert de résine sous vide Séchage Stratifiés Index. décimale : 620.1 Mécanique de l'ingénieur (mécanique appliquée) et matériaux Résumé : Hybrid processes combining characteristics of prepreg and resin infusion/injection techniques are interesting and advantageous solutions for manufacturing of highly integrated structures. The possibility, given by traditional prepreg technology, to manufacture with a good reproducibility parts having elevated mechanical performances and as well to introduce additives like flame retardants or tougheners, can be successfully combined with liquid composite molding (LCM) characteristics. This work aimed to investigate these combined processes. The present research involved furthermore out-of-autoclave (OOA) prepreg, which provide additional cost-savings and environmental advantages compared with standard autoclave techniques: OOA prepreg plies and dry fabrics are laid up together in a mold and then resin is injected (RTM-like) or infused (VARI-like) in the cavity. When the impregnation is completed the part can be cured in oven. Goal of the investigation is to analyze the performances of hybrid laminates, in respect to pure OOA prepreg- and LCM-parts and to optimize the manufacturing route, assessing the process robustness through several tests. Simple demonstrators have been also realized to prove the hybrid technique feasibility and effectiveness. Note de contenu : - MATERIALS AND PROCESS DESCRIPTION : Materials and process description - Hybrid OOA prepreg/LCM process description - TESTS RESULTS AND DISCUSSION : Feasibility analysis and comparison with pure procesing - Sensitivity study Permalink : https://e-campus.itech.fr/pmb/opac_css/index.php?lvl=notice_display&id=16079 [article]

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Manufacturing defects in composite structures / Scott W. Beckwith in SAMPE JOURNAL, Vol. 48, N° 5 (09-10/2012)

[article]  inSAMPE JOURNAL > Vol. 48, N° 5 (09-10/2012) . - p. 52-53 Titre : Manufacturing defects in composite structures Type de document : texte imprimé Auteurs : Scott W. Beckwith, Auteur Année de publication : 2012 Article en page(s) : p. 52-53 Note générale : Bibliogr. Langues : Américain (ame) Index. décimale : 620.1 Mécanique de l'ingénieur (mécanique appliquée) et matériaux Résumé : The design and analysis of functioning, high performance, safe composite structures depends upon numerous decisions that the structural design engineer, the materials engineer and the manufacturing engineer must make over the course of getting a composite product into the market place. Theoretical design processes rely upon a firm understanding fo the physics and material aspects generally of three important materials in a composite : the reinforcement fiber the resin matrix (for polymer composites), and, that region defined as the "interface" between the fiber-resin. The latter often contributes a lot - but often is ignored in the generation of theoretical structural models. Permalink : https://e-campus.itech.fr/pmb/opac_css/index.php?lvl=notice_display&id=16080 [article]

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Face-sheet analysis ant thermo-physical property characterization of OOA and autoclave panels / S. G. Miller in SAMPE JOURNAL, Vol. 48, N° 5 (09-10/2012)

[article]  inSAMPE JOURNAL > Vol. 48, N° 5 (09-10/2012) . - p. 56-61 Titre : Face-sheet analysis ant thermo-physical property characterization of OOA and autoclave panels Type de document : texte imprimé Auteurs : S. G. Miller, Auteur ; R. D. Lort, Auteur ; James K. Sutter, Auteur ; L. I. Pelham, Auteur ; L. S. McCorkle, Auteur ; D. A. Scheiman, Auteur Année de publication : 2012 Article en page(s) : p. 56-61 Note générale : Bibliogr. Langues : Américain (ame) Catégories : Autoclave (technologie) Caractérisation Composites à fibres de carbone Construction sandwich Epoxydes Hors autoclave (technologie) Matériaux -- Imprégnation Polyimides Structure en nid d'abeilles Index. décimale : 620.1 Mécanique de l'ingénieur (mécanique appliquée) et matériaux Résumé : Increased application of polymer matrix composite (PMC) materials in large vehicle structures requires consideration of non-autoclave manufacturing. The NASA Composites for Exploration project, and its predecessor, Lightweight Spacecraft Structures and Materials project, were tasked with the development of materials and manufacturing processes for structures that will perform in a heavy-lift-launch vehicle environment. Both autoclave and out-of-clave processable materials were considered. Large PMC structures envisioned for such a vehicle included the payload shroud and the interstage connector. In this study, composite sandwich panels representing 1/16th segments of the barrel section of the Ares V rocket fairing were prepared as 1.8m x2.4m sections of the 10m diameter arc segment. IM7/977-3 was used as the face-sheet prepreg of the autoclave processed panels and T40-800B/5320-1 for the out-of -autoclave panels. The core was 49.7 kg/p2 (3.1 lb/ft3) aluminum honeycomb. Face-sheets were fabricated by automated tape laying 153 mm wide unidirectional tape. This work details analysis of the manufactured panels where face-sheet quality was characterized by optical microscopy, cured ply thickness measurements, acid digestion, and thermal analysis. Note de contenu : - EXPERIMENTAL : Panel fabrication - Face-sheet characterization core and adhesive removal - Optical microscopy - Void analysis - Dynamic mechanical analysis - RESULTS AND DISCUSSION : IM7/977-3 - Cured Ply Thickness (CPT) - DMA - 3.2T40-800B/5320-1 - Void analysis - Cured Ply Thickness Permalink : https://e-campus.itech.fr/pmb/opac_css/index.php?lvl=notice_display&id=16081 [article]

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