Computational approach for composite material allowables using sealed envelope predictions for reduced testing / Galib Abumeri in SAMPE JOURNAL, Vol. 45, N° 5 (09-10/2009)

[article]  inSAMPE JOURNAL > Vol. 45, N° 5 (09-10/2009) . - p. 26-35 Titre : Computational approach for composite material allowables using sealed envelope predictions for reduced testing Type de document : texte imprimé Auteurs : Galib Abumeri, Auteur ; M. Garg, Auteur ; Frank Abdi, Auteur ; A. McCloskey, Auteur ; R. Bohner, Auteur Année de publication : 2009 Article en page(s) : p. 26-35 Note générale : Bibliogr. Langues : Américain (ame) Tags : 'Composites  polymères'  'Simulation  par  ordinateur'  'Tests  réduits'  'Résistance  des  matériaux' Index. décimale : 668.4 Plastiques, vinyles Résumé : Accurate prediction of 1- and B-basis material allowables is essential for statistical characterization and risk reduction of structural aerospace materials. Current practices for determining allowables for polymer composites follow recommended procedures set forth by CMH-17 (formerly military handbook MIL-HKBK-17-1E) and FAA. The process is costly and time consuming as accurate determination of allowables requires physical testing of a large number of coupons for various layup configurations and test environments. Further, new composite materials are introduced to the market at a rapid rate amplyfying the need for timely cost effective approach. To mitigate time and cost associated with material allowable generation, Alpha STAR Corporation (ASC) and Northrop Grumman (NG) are cooperating in an effort to explore a novel computational method for predicting B-basis strength valeus of polymer matrix composites. The approach combines composites mechanics based progressive failure analysis (PFA), finite element analysis, probabilistic methods, and reduced testing to virtually generate coupon tests. To examine the validity of this approach the ASC-NG team used a "sealed envelope" process. Here, ASC made its predictions independent of test results and then handed them to NG for comparison against a "sealed envelope" of real test data. B-basis tensile strength values for un-notched and notched IM7/MTM45-1 coupons were predicted (using a reduced number of test replicates) and provided to the NG team. Predicted results were compared to those obtained using standard military specification practices and the standard number of test replicates. This computational approach has potential for simulation of all types of ASTM tests under various environmental conditions, potentially reducing the required number of test replicates by more than 67 %. The difference in the B-basis results obtained from prediction and those from current practices ranged from -5,8 % and -7,95 %. The average difference between th two results was less than -0,2 %. The difference between the two solutions was less than 1 % for 30 % of the test cases simulated. Permalink : https://e-campus.itech.fr/pmb/opac_css/index.php?lvl=notice_display&id=7194 [article]

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Durability and reliability of large composite wind turbine blades / Galib Abumeri in SAMPE JOURNAL, Vol. 48, N° 6 (11-12/2012)  

[article]  inSAMPE JOURNAL > Vol. 48, N° 6 (11-12/2012) . - p. 7-14 Titre : Durability and reliability of large composite wind turbine blades Type de document : texte imprimé Auteurs : Galib Abumeri, Auteur ; Frank Abdi, Auteur Année de publication : 2012 Article en page(s) : p. 7-14 Note générale : Bibliogr. Langues : Américain (ame) Catégories : Analyse multiéchelle Composites à fibres de verre -- Propriétés mécaniques Durée de vie (Ingénierie) Eoliennes -- Matériaux Fiabilité Matériaux -- Fatigue Pales d'éoliennes Résistance des matériaux Rupture (mécanique) Index. décimale : 620.11 Matériaux (propriétés, résistance) Résumé : Because of its advantageous weight-to-stiffness and weight-to-strength ratios, the E-glass composite has become more attractive in the design of large wind turbine blade. In this paper, material characterization of E-glass composites was performed to determine the composite's static and fatigue properties. Also, durability and damage tolerance (D&DT) and fatigue life analyses based on a multi-scale progressive failure analysis (PFA) were performed to determine a large wind turbine blade made of E-glass composites : a) structural integrity, under 140 mph wind pressure, b) improved structural performance, under 140 mph wind pressure and c) fatigue life and the associated damage under 30-60 mph wind pressures. Note de contenu : - METHODOLOGY : Durability and damage tolerance (D&DT) analysis - Composite material calibration - static strength and stiffness calibration - RESULTS AND DISCUSSION : Large wind blade design configuration - Material static and fatigue calibration and qualification - Static property calibration of E-glass composite - Fatigue life of E-glass composite En ligne : http://enu.kz/repository/2011/AIAA-2011-1819.pdf Format de la ressource électronique : Pdf Permalink : https://e-campus.itech.fr/pmb/opac_css/index.php?lvl=notice_display&id=16498 [article]

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Honeycomb fuselage panel certification by analysis / S. Leemans in SAMPE JOURNAL, Vol. 46, N° 4 (07-08/2010)

[article]  inSAMPE JOURNAL > Vol. 46, N° 4 (07-08/2010) . - p. 30-47 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'abeilles Index. 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 [article]

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Impact damage propagation in composite structures / Frank Abdi in JEC COMPOSITES MAGAZINE, N° 24 (04/2006)  

[article]  inJEC COMPOSITES MAGAZINE > N° 24 (04/2006) . - p. 35-36 Titre : Impact damage propagation in composite structures Type de document : texte imprimé Auteurs : Frank Abdi, Auteur Année de publication : 2006 Article en page(s) : p. 35-36 Langues : Anglais (eng) Tags : 'Propriété  mécanique'  'Etude  théorique'  'Simulation  numérique'  Modélisation  traction'  'Résistance  choc'  Stratifié  'Matériau  renforcé  fibre'  Polymère  'Tissu  textile'  Durabilité  composite'  Endommagement Index. décimale : 668.4 Plastiques, vinyles Résumé : Durability of a woven fabric panel subject to low-velocity impact and post-impact tension was investigated using the GENOA code. The results were in good agreement with the experiments. The building block approach and advanced damage tracking are the key factors in the success of the analysis. En ligne : http://www.jeccomposites.com/news/composites-news/impact-damage-propagation-comp [...] Format de la ressource électronique : Web Permalink : https://e-campus.itech.fr/pmb/opac_css/index.php?lvl=notice_display&id=13990 [article]

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