. . "2014-12-15+01:00"^^ . . "2"^^ . "[B79F1D747339]" . . "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."@en . "MODIFICATIONS OF A SIMPLE I-BEAM AND ITS EFFECTS ON THE STRESS STATE" . "2"^^ . . "Cejpek, Jakub" . . . "P(ED0002/01/01)" . . . "Hradec Kr\u00E1lov\u00E9, \u010Cesk\u00E1 republika" . "Sborn\u00EDk p\u0159\u00EDsp\u011Bvk\u016F Mezin\u00E1rodn\u00ED Masarykovy konference pro doktorandy a mlad\u00E9 v\u011Bdeck\u00E9 pracovn\u00EDky 2014" . "30130" . . "RIV/00216305:26210/14:PU111370!RIV15-MSM-26210___" . "Jura\u010Dka, Jaroslav" . "RIV/00216305:26210/14:PU111370" . "Hradec Kr\u00E1lov\u00E9" . . . . . "26210" . "MAGNANIMITAS" . . "MODIFICATIONS OF A SIMPLE I-BEAM AND ITS EFFECTS ON THE STRESS STATE"@en . . . . "MODIFICATIONS OF A SIMPLE I-BEAM AND ITS EFFECTS ON THE STRESS STATE" . . "beam, normal stress, shear stress, classical laminate theory, wing, composite"@en . . "5"^^ . "MODIFICATIONS OF A SIMPLE I-BEAM AND ITS EFFECTS ON THE STRESS STATE"@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." . "978-80-87952-07-8" .