A Method of calculating the compressive strength of Z-stiffened panels that develop local instability /

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A method, based on the elastic theory for plate buckling and test results for 24S-T aluminum-alloy Z-stiffened panels, is shown for calculating the compressive strength of Z-stiffened panels that develop local instability. This method can be used to calculate the critical compressive stress above, a...

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Detalles Bibliográficos
Clasificación:Libro Electrónico
Autor principal: Gallaher, George L. (Autor)
Autor Corporativo: United States. National Advisory Committee for Aeronautics
Otros Autores: Boughan, Rolla B.
Formato: Documento de Gobierno Electrónico eBook
Idioma:Inglés
Publicado: Washington, D.C. : National Advisory Committee for Aeronautics, 1947.
Colección:Technical note (United States. National Advisory Committee for Aeronautics) ; no. 1482.
Temas:
Plates (Engineering)
Strains and stresses.
Buckling (Mechanics)
Mathematical analysis.
Plaques (Ingénierie)
Contraintes (Mécanique)
Flambage (Résistance des matériaux)
Analyse mathématique.
stress.
strain.
warping.
buckling.
Mathematical analysis
Strains and stresses
Acceso en línea:Texto completo
Descripción
Sumario:A method, based on the elastic theory for plate buckling and test results for 24S-T aluminum-alloy Z-stiffened panels, is shown for calculating the compressive strength of Z-stiffened panels that develop local instability. This method can be used to calculate the critical compressive stress above, as well as within, the elastic range. For stresses above three-fourths the compressive yield stress the method can be used for the approximate determination of the average compressive stress at maximum load.
Notas:"November 1947."
NACA TN No. 1482.
Descripción Física:1 online resource (15 pages) : illustrations, tables
Bibliografía:Includes bibliographical references.
ISBN:9781680156102
1680156101

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