Detail publikace

Detailed topometry FEM optimization of wing structural panel

Originální název

Detailed topometry FEM optimization of wing structural panel

Anglický název

Detailed topometry FEM optimization of wing structural panel

Jazyk

en

Originální abstrakt

The detailed topometry optimization of the critical part of an aircraft wing is presented in this article. The integral lower wing structural panel of aircraft in the Commuter category of the CS-23 regulation standard is selected for optimization. The first case demonstrates significant weight savings using modern Finite Element (FE) optimization methods for determined structural constraints. A practical aircraft operation and additional regulation requirements affect optimization constraints in the second case. This detailed optimization also consists of FE model validation, stress analyses and complex load capacity analyses, which are necessary for designed structural modifications with an optimal stress distribution.

Anglický abstrakt

The detailed topometry optimization of the critical part of an aircraft wing is presented in this article. The integral lower wing structural panel of aircraft in the Commuter category of the CS-23 regulation standard is selected for optimization. The first case demonstrates significant weight savings using modern Finite Element (FE) optimization methods for determined structural constraints. A practical aircraft operation and additional regulation requirements affect optimization constraints in the second case. This detailed optimization also consists of FE model validation, stress analyses and complex load capacity analyses, which are necessary for designed structural modifications with an optimal stress distribution.

Dokumenty

BibTex


@misc{BUT123883,
  author="Tomáš {Katrňák} and Jaroslav {Juračka}",
  title="Detailed topometry FEM optimization of wing structural panel",
  annote="The detailed topometry optimization of the critical part of an aircraft wing is presented in this article. The integral lower wing structural panel of aircraft in the Commuter category of the CS-23 regulation standard is selected for optimization. The first case demonstrates significant weight savings using modern Finite Element (FE) optimization methods for determined structural constraints. A practical aircraft operation and additional regulation requirements affect optimization constraints in the second case. This detailed optimization also consists of FE model validation, stress analyses and complex load capacity analyses, which are necessary for designed structural modifications with an optimal stress distribution.",
  chapter="123883",
  howpublished="online",
  year="2015",
  month="may",
  type="lecture"
}