Influence of modelling and solution methods on the FE-simulation of the post-buckling behaviour of stiffened aircraft fuselage panels

Composite Structures

Volumn 73, Issue 2, 2006, Pages 229-236

  Linde, P ^a   Schulz, A ^b   Rust, W ^b,c  

^a AIRBUS OPERATIONS GMBH   (Germany)

^b CADFEM GMBH   (Germany)

^c UNIVERSITY OF APPLIED SCIENCES   (Germany)

Author keywords

FE limit load analysis; Metal fibre laminate; Quasi static dynamic solution; Stiffened shell structure; Virtual testing

Indexed keywords

BUCKLING; COMPUTER SIMULATION; FAILURE (MECHANICAL); FIBER REINFORCED METALS; LAMINATED COMPOSITES; MATHEMATICAL MODELS; MECHANICAL TESTING; SHELLS (STRUCTURES); STIFFNESS;

METAL FIBER LAMINATE; QUASI-STATIC DYNAMIC SOLUTION; STIFFENED AIRCRAFT FUSELAGE PANELS; STIFFENED SHELL STRUCTURES; VIRTUAL TESING;

STRUCTURAL PANELS;

AIRCRAFT;

EID: 32044449182     PISSN: 02638223     EISSN: None     Source Type: Journal    
DOI: 10.1016/j.compstruct.2005.11.048     Document Type: Article

References (4)

1. Linde P. Feasibility study, Virtual structural test analysis system, internal report, Airbus Deutschland GmbH, 2002.
2. Linde P, Pleitner J, Frank C, Gotthold S, Rust W, Schulz A. Development of a virtual test rig for stiffenened fuselage panels. In: Proceedings of the 21st CAD-FEM Users' Meeting, International Congress on FEM Technology, Potsdam, 12-14 November 2003. Grafing: CAD-FEM GmbH.
3. Linde P, Pleitner J, Rust W. Virtual testing of aircraft fuselage stiffened panels, ICAS 2004. In: Proc 24th International Congress of the Aeronautical Sciences, Yokohama, 29 August 4 September 2004.
4. W. Rust K. Schweizerhof Finite element limit-load analysis of thin-walled structures by ANSYS (implicit) and LS-DYNA (explicit) and in combination Thin-Walled Struct 41 2003 227-244