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Using ground vibration testing to correlate the hunter UVA structural model / J. B. Kosmatka in SAMPE JOURNAL, Vol. 41, N° 7 (11-12/2005)

[article]  inSAMPE JOURNAL > Vol. 41, N° 7 (11-12/2005) . - p. 5-13 Titre : Using ground vibration testing to correlate the hunter UVA structural model Type de document : texte imprimé Auteurs : J. B. Kosmatka, Auteur ; A. Valdes, Auteur Année de publication : 2006 Article en page(s) : p. 5-13 Note générale : Bibliogr. Langues : Américain (ame) Index. décimale : 668.4 Plastiques, vinyles Résumé : The Northrop Grumman Hunter unmanned air vehicle (UAV) is a workhorse of the U.S. Army for reconnaissance and surveillance missions. This all-composite aircraft is used for a wide variety of missions at extreme enviroment operating conditions. New payload opportunities and added mission demands require additional structural analysis to insure vehicle integrity. In the current effort, a detailed finite element model of the entire Hunter aircraft was developed to support these needed structural analyses. The finite element model was improved using measured mass properties and experimentally measured free-free modes of the actual Hunter aircraft. The resulting model accurately predicted the mass properties and all five primary structural modes below 40 Hz including the wing bending and torsion modes which are needed for aeroelastic (flutter) and aeroservoelastic studies. Moreover, this model can predict many realistic local modes (engine cowling, fuselage modes, etc). Thus, this model represents an outstanding tool for determining the internal loads and stresses, as well as identifying critical resonant conditios of the Hunter UAV under a wide variety of load, flight, and payload conditions. Note de contenu : - HUNTER AIRCRAFT DEFINITION : Geometry - Weight distribution - Materials-composite lay-ups and thicknesses - FINITE ELEMENT MODEL DEFINITION : Wing - Tail assembly - Fuselage and booms - Aircraft assembly - FINITE ELEMENT CORRELATION STUDIES Permalink : https://e-campus.itech.fr/pmb/opac_css/index.php?lvl=notice_display&id=23238 [article]

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Thermoplastics in aerospace, new products through innovative technology / A. Offringa in SAMPE JOURNAL, Vol. 41, N° 7 (11-12/2005)

[article]  inSAMPE JOURNAL > Vol. 41, N° 7 (11-12/2005) . - p. 19-27 Titre : Thermoplastics in aerospace, new products through innovative technology Type de document : texte imprimé Auteurs : A. Offringa, Auteur Année de publication : 2006 Article en page(s) : p. 19-27 Note générale : Bibliogr. Langues : Américain (ame) Index. décimale : 668.4 Plastiques, vinyles Résumé : Thermoplastic composites have long since matured into series production. Cost reduction has been the driver in this aerospace technology development and its applications. Fabric reinforced and unidirectional materials are currently available, both in sheet form and as single ply material. Thermo-folding and press-forming of single parts were the processing technologies initially developed. Welding of assemblies and co-consolidation have recently been added. With the co-consolidation technique, parts are built up from preforms and fused together in a single manufacturing step. Applications such as stiffened panels, beams and leading edges have emerged. Current development focuses on expanding co-consolidation and welding applications, such as welded control surfaces. The full range of thermoplastic processing technologies opens the road to an ever growing number of applications. Note de contenu : - MATERIAL DEVELOPMENT : Evolution of thermoplastic matrices - Thermoplastic composite material forms - PROCESSING TECHNOLOGY AND PRODUCT APPLICATIONS : Low-cost processing - The beginning: thermo-folding and press-forming - The advent of welding - Co-consolidation - Current development - Technology overview - FUTURE PROSPECTS Permalink : https://e-campus.itech.fr/pmb/opac_css/index.php?lvl=notice_display&id=23554 [article]

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Heated tooling for aerospace composite manufacture / S. M. Grove in SAMPE JOURNAL, Vol. 41, N° 7 (11-12/2005)

[article]  inSAMPE JOURNAL > Vol. 41, N° 7 (11-12/2005) . - p. 36-45 Titre : Heated tooling for aerospace composite manufacture Type de document : texte imprimé Auteurs : S. M. Grove, Auteur ; I. Progoulakis, Auteur ; T. Searle, Auteur ; J. Summerscales, Auteur ; P. Healey, Auteur Année de publication : 2006 Article en page(s) : p. 36-45 Note générale : Bibliogr. Langues : Américain (ame) Index. décimale : 668.4 Plastiques, vinyles Résumé : This paper reviews some currently available technologies for the direct application of heat to tooling for composites manufacture. The performance of experimental heated tooling has been evaluated fir the production of CFRP laminates up to 11 mm thick, manufactured by resin film infusion. The ability of numerical FEA to facilitate the design of heated tooling is exported. A preliminary (and approximate) cost analysis suggest that integrally-heated tooling could provide a significant cost advantage over autoclave or oven processing. Note de contenu : - INTEGRAL TOOL HEATING - TECHNOLOGY REVIEW : Heating fabrics - Heater mats - Resistive heaters - Heated fluid circulation - Other technologies - Manufacture - EXPERIMENTAL EVALUATION - EXPERIMENTAL RESULTS : Thermal performance of heated tool - Physical properties of cured laminates - THERMAL MODELS OF INTEGRALLY-HEATED TOOLING : Alternative thermal analyses - Numerical heat transfert analysis - COST IMPLICATIONS : Pre-production requirements - Production costs - Cost per part Permalink : https://e-campus.itech.fr/pmb/opac_css/index.php?lvl=notice_display&id=23555 [article]

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