Detail publikace

FEM Approach to Estimate Large Deformations of Stiffened Fuselage Structure

Originální název

FEM Approach to Estimate Large Deformations of Stiffened Fuselage Structure

Anglický název

FEM Approach to Estimate Large Deformations of Stiffened Fuselage Structure

Jazyk

en

Originální abstrakt

The article describes the evaluation of a progress of stiffness changes and stability failures of the fuselage structure. The two non-linear FE analyses were proved for a purpose of the stability and strength analysis of the L 410 NG aircraft. The results of the FE analyses and the additional analytical analysis were compared with the results of the static strength test. For the material non-linear characteristics, large deformations and the complex structure of the metal thin-walled fuselage the effect of used non-linear solvers, methods and input parameters were investigated.

Anglický abstrakt

The article describes the evaluation of a progress of stiffness changes and stability failures of the fuselage structure. The two non-linear FE analyses were proved for a purpose of the stability and strength analysis of the L 410 NG aircraft. The results of the FE analyses and the additional analytical analysis were compared with the results of the static strength test. For the material non-linear characteristics, large deformations and the complex structure of the metal thin-walled fuselage the effect of used non-linear solvers, methods and input parameters were investigated.

Dokumenty

BibTex


@inproceedings{BUT100420,
  author="Volodymyr {Symonov} and Tomáš {Katrňák}",
  title="FEM Approach to Estimate Large Deformations of Stiffened Fuselage Structure",
  annote="The article describes the evaluation of a progress of stiffness changes and stability failures of the fuselage structure. The two non-linear FE analyses were proved for a purpose of the stability and strength analysis of the L 410 NG aircraft. The results of the FE analyses and the additional analytical analysis were compared with the results of the static strength test. For the material non-linear characteristics, large deformations and the complex structure of the metal thin-walled fuselage the effect of used non-linear solvers, methods and input parameters were investigated.",
  address="Akademické nakladatelství CERM Brno",
  booktitle="New Trends in Civil Aviation 2013",
  chapter="100420",
  edition="1",
  howpublished="print",
  institution="Akademické nakladatelství CERM Brno",
  year="2013",
  month="june",
  pages="90--92",
  publisher="Akademické nakladatelství CERM Brno",
  type="conference paper"
}