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Title: Advances in Computational Stability Analysis of Composite Aerospace Structures

European aircraft industry demands for reduced development and operating costs. Structural weight reduction by exploitation of structural reserves in composite aerospace structures contributes to this aim, however, it requires accurate and experimentally validated stability analysis of real structures under realistic loading conditions. This paper presents different advances from the area of computational stability analysis of composite aerospace structures which contribute to that field. For stringer stiffened panels main results of the finished EU project COCOMAT are given. It investigated the exploitation of reserves in primary fibre composite fuselage structures through an accurate and reliable simulation of postbuckling and collapse. For unstiffened cylindrical composite shells a proposal for a new design method is presented.
Authors:
 [1] ;  [2] ;  [3]
  1. DLR, Inst. Composite Structures and Adaptive Systems, Lilienthalplatz 7, 38108 Braunschweig (Germany)
  2. (Germany)
  3. Dept Civil Eng, UFOP, 35400-000 Ouro Preto, MG (Brazil)
Publication Date:
OSTI Identifier:
21428573
Resource Type:
Journal Article
Resource Relation:
Journal Name: AIP Conference Proceedings; Journal Volume: 1281; Journal Issue: 1; Conference: ICNAAM 2010: International conference of numerical analysis and applied mathematics 2010, Rhodes (Greece), 19-25 Sep 2009; Other Information: DOI: 10.1063/1.3498128; (c) 2010 American Institute of Physics
Country of Publication:
United States
Language:
English
Subject:
71 CLASSICAL AND QUANTUM MECHANICS, GENERAL PHYSICS; 36 MATERIALS SCIENCE; COMPOSITE MATERIALS; COMPUTER CALCULATIONS; COMPUTERIZED SIMULATION; CYLINDRICAL CONFIGURATION; DESIGN; FIBERS; LOADING; PANELS; STABILITY CONFIGURATION; MATERIALS; MATERIALS HANDLING; SIMULATION