[article]
| 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 |
in SAMPE JOURNAL > Vol. 46, N° 4 (07-08/2010) . - p. 30-47
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Honeycomb fuselage panel certification by analysis in SAMPE JOURNAL, Vol. 46, N° 4 (07-08/2010)
