Publication detail

MODIFICATIONS OF A SIMPLE I-BEAM AND ITS EFFECTS ON THE STRESS STATE

CEJPEK, J. JURAČKA, J.

Original Title

MODIFICATIONS OF A SIMPLE I-BEAM AND ITS EFFECTS ON THE STRESS STATE

English Title

MODIFICATIONS OF A SIMPLE I-BEAM AND ITS EFFECTS ON THE STRESS STATE

Type

conference paper

Language

en

Original Abstract

The motivation for this work is a desire for deep understanding of the structural failures in a composite glider wing, which has been tested in the laboratories of the Institute of Aerospace Engineering, Faculty of Mechanical Engineering, University of Technology in Brno. To understand the causes of the encountered failures, one has to consider the effects of all the stages in design, manufacturing and testing of the wing. This paper focuses on the design stage only. Presented facts are obtained from finite element analysis. The geometry used for the analysis is that of tested specimens. This allows validating the results by comparison of deformation and strains measured during the laboratory tests. Analysis starts with simple I-beam loaded by three-point-bending. In the next step a cantilever is added. Several more modifications follow, changing the I-beam to the wing. Case evaluation considers the interaction between normal (material direction 1) and inter-laminar shear stresses in the upper flange. The goal of this paper is quantifying the effect of each design change in the wing structure and loading on the stress plane S1-T31.

English abstract

The motivation for this work is a desire for deep understanding of the structural failures in a composite glider wing, which has been tested in the laboratories of the Institute of Aerospace Engineering, Faculty of Mechanical Engineering, University of Technology in Brno. To understand the causes of the encountered failures, one has to consider the effects of all the stages in design, manufacturing and testing of the wing. This paper focuses on the design stage only. Presented facts are obtained from finite element analysis. The geometry used for the analysis is that of tested specimens. This allows validating the results by comparison of deformation and strains measured during the laboratory tests. Analysis starts with simple I-beam loaded by three-point-bending. In the next step a cantilever is added. Several more modifications follow, changing the I-beam to the wing. Case evaluation considers the interaction between normal (material direction 1) and inter-laminar shear stresses in the upper flange. The goal of this paper is quantifying the effect of each design change in the wing structure and loading on the stress plane S1-T31.

Keywords

beam, normal stress, shear stress, classical laminate theory, wing, composite

RIV year

2014

Released

22.12.2014

Publisher

MAGNANIMITAS

Location

Hradec Králové, Česká republika

ISBN

978-80-87952-07-8

Book

Sborník příspěvků Mezinárodní Masarykovy konference pro doktorandy a mladé vědecké pracovníky 2014

Edition

2014

Edition number

5

Pages from

1

Pages to

5

Pages count

5

Documents

BibTex


@inproceedings{BUT110745,
  author="Jakub {Cejpek} and Jaroslav {Juračka}",
  title="MODIFICATIONS OF A SIMPLE I-BEAM AND ITS EFFECTS ON THE STRESS STATE",
  annote="The motivation for this work is a desire for deep understanding of the structural failures in a composite glider wing, which has been tested in the laboratories of the Institute of Aerospace Engineering, Faculty of Mechanical Engineering, University of Technology in Brno.
To understand the causes of the encountered failures, one has to consider the effects of all the stages in design, manufacturing and testing of the wing.
This paper focuses on the design stage only. Presented facts are obtained from finite element analysis.
The geometry used for the analysis is that of tested specimens. This allows validating the results by comparison of deformation and strains measured during the laboratory tests.
Analysis starts with simple I-beam loaded by three-point-bending. In the next step a cantilever is added. Several more modifications follow, changing the I-beam to the wing.
Case evaluation considers the interaction between normal (material direction 1) and inter-laminar shear stresses in the upper flange.
The goal of this paper is quantifying the effect of each design change in the wing structure and loading on the stress plane S1-T31.",
  address="MAGNANIMITAS",
  booktitle="Sborník příspěvků Mezinárodní Masarykovy konference pro doktorandy a mladé vědecké pracovníky 2014",
  chapter="110745",
  edition="2014",
  howpublished="online",
  institution="MAGNANIMITAS",
  year="2014",
  month="december",
  pages="1--5",
  publisher="MAGNANIMITAS",
  type="conference paper"
}