Modifikace I-nosníku a vliv na napěťový stav

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

článek ve sborníku ve WoS nebo Scopus

en

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.

Článek mapuje změnu obyčejného I nosníku v křídlo. Změna se týká geometrie (konstrukčního uspořádání) a okrajových podmínek. Je sledován podíl normálných a smykových napětí. Taktéž jsou srovnány numerické výsledky MKP s temi analytickými.

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.

nosník, normálné napětí, smykové napětí, klasická laminátová teorie, křídlo, kompozit

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

2014

22.12.2014

MAGNANIMITAS

Hradec Králové, Česká republika

978-80-87952-07-8

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

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1–5

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