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Statements

Subject Item
n2:RIV%2F00216305%3A26210%2F05%3APU48119%21RIV06-MSM-26210___
rdf:type
n11:Vysledek skos:Concept
dcterms:description
A material, called the Paraglass, has been used for the design of the ultralight composite glider, as a substitute for foam at sandwich structure. The material is used as middle lay of all coverings, which are the skin of wing, the fuselage and the tailplane. The advantage of this material is very simple and cheap technology of the structure production. The disadvantage is its weight and density. Before putting into production of aircraft, basic material tests were done to determinate tensile strength aand shear behaviour. The test results confirmed behaviour like isotropic panel. On the basis of results of initial tests and analyses, the lamination of the wing skin and fuselage was designed. Both wing and fuselage were tested and they provided the ability to carry ultimate loads. A material, called the Paraglass, has been used for the design of the ultralight composite glider, as a substitute for foam at sandwich structure. The material is used as middle lay of all coverings, which are the skin of wing, the fuselage and the tailplane. The advantage of this material is very simple and cheap technology of the structure production. The disadvantage is its weight and density. Before putting into production of aircraft, basic material tests were done to determinate tensile strength aand shear behaviour. The test results confirmed behaviour like isotropic panel. On the basis of results of initial tests and analyses, the lamination of the wing skin and fuselage was designed. Both wing and fuselage were tested and they provided the ability to carry ultimate loads. A material, called the Paraglass, has been used for the design of the ultralight composite glider, as a substitute for foam at sandwich structure. The material is used as middle lay of all coverings, which are the skin of wing, the fuselage and the tailplane. The advantage of this material is very simple and cheap technology of the structure production. The disadvantage is its weight and density. Before putting into production of aircraft, basic material tests were done to determinate tensile strength aand shear behaviour. The test results confirmed behaviour like isotropic panel. On the basis of results of initial tests and analyses, the lamination of the wing skin and fuselage was designed. Both wing and fuselage were tested and they provided the ability to carry ultimate loads.
dcterms:title
3D Fabric Application on Glider Structures Aplikace 3D tkanin na kompozitní konstrukci kluzáku. 3D Fabric Application on Glider Structures
skos:prefLabel
3D Fabric Application on Glider Structures 3D Fabric Application on Glider Structures Aplikace 3D tkanin na kompozitní konstrukci kluzáku.
skos:notation
RIV/00216305:26210/05:PU48119!RIV06-MSM-26210___
n3:strany
1-100
n3:aktivita
n17:P
n3:aktivity
P(1M0501)
n3:dodaniDat
n18:2006
n3:domaciTvurceVysledku
n10:2891131
n3:druhVysledku
n8:D
n3:duvernostUdaju
n14:S
n3:entitaPredkladatele
n12:predkladatel
n3:idSjednocenehoVysledku
552726
n3:idVysledku
RIV/00216305:26210/05:PU48119
n3:jazykVysledku
n6:eng
n3:klicovaSlova
parabeam, paraglass, form, 3D, share test, composite material
n3:klicoveSlovo
n9:form n9:parabeam n9:share%20test n9:3D n9:paraglass n9:composite%20material
n3:kontrolniKodProRIV
[7D25CF5413A7]
n3:mistoKonaniAkce
Melbourne
n3:mistoVydani
Melbourne, Austálie
n3:nazevZdroje
CD-Rom of Congress proceedings
n3:obor
n13:JU
n3:pocetDomacichTvurcuVysledku
1
n3:pocetTvurcuVysledku
1
n3:projekt
n19:1M0501
n3:rokUplatneniVysledku
n18:2005
n3:tvurceVysledku
Juračka, Jaroslav
n3:typAkce
n15:WRD
n3:zahajeniAkce
2005-03-13+01:00
s:numberOfPages
100
n5:hasPublisher
The Royal Aeronautical Society, Australia
n21:isbn
0-85825-732-7
n20:organizacniJednotka
26210