The stability under longitudinal compression of flat symmetric corrugated-core sandwich plates with simply supported loaded edges and simply supported or clamped unloaded edges /

A theory for the elastic behavior of orthotropic sandwich plates is used to determine the compressive buckling-load parameters of flat symmetrical corrugated core sandwich plates with simply supported loaded edges and simply supported or clamped unloaded edges.

Detalles Bibliográficos
Clasificación:Libro Electrónico
Autor principal: Seide, Paul (Autor)
Autores Corporativos: Langley Aeronautical Laboratory, United States. National Advisory Committee for Aeronautics
Formato: Documento de Gobierno Electrónico eBook
Idioma:Inglés
Publicado: Washington, D.C. : National Advisory Committee for Aeronautics, 1952.
Colección:Technical note (United States. National Advisory Committee for Aeronautics) ; no. 2679.
Temas:
Plates (Engineering)
Sandwich construction.
Loads (Mechanics)
Buckling (Mechanics)
Elasticity.
Plaques (Ingénierie)
Construction sandwich.
Charges.
Flambage (Résistance des matériaux)
Élasticité.
warping.
buckling.
elasticity.
modulus of elasticity.
Elasticity
Sandwich construction
Acceso en línea:Texto completo

MARC

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088 |a NACA-TN-2679 
049 |a UAMI 
100 1 |a Seide, Paul,  |e author. 
245 1 4 |a The stability under longitudinal compression of flat symmetric corrugated-core sandwich plates with simply supported loaded edges and simply supported or clamped unloaded edges /  |c Paul Seide. 
264 1 |a Washington, D.C. :  |b National Advisory Committee for Aeronautics,  |c 1952. 
300 |a 1 online resource (30 pages) :  |b illustrations 
336 |a text  |b txt  |2 rdacontent 
337 |a computer  |b c  |2 rdamedia 
338 |a online resource  |b cr  |2 rdacarrier 
490 1 |a National Advisory Committee for Aeronautics ;  |v 2679 
500 |a "Langley Aeronautical Laboratory." 
500 |a Date of issue: April 1952. 
500 |a Report no. NACA-TN-2679. 
520 3 |a A theory for the elastic behavior of orthotropic sandwich plates is used to determine the compressive buckling-load parameters of flat symmetrical corrugated core sandwich plates with simply supported loaded edges and simply supported or clamped unloaded edges. 
588 0 |a Print version record. 
504 |a Includes bibliographical references (page 19) 
590 |a Knovel  |b ACADEMIC - Aerospace & Radar Technology 
650 0 |a Plates (Engineering) 
650 0 |a Sandwich construction. 
650 0 |a Loads (Mechanics) 
650 0 |a Buckling (Mechanics) 
650 0 |a Elasticity. 
650 6 |a Plaques (Ingénierie) 
650 6 |a Construction sandwich. 
650 6 |a Charges. 
650 6 |a Flambage (Résistance des matériaux) 
650 6 |a Élasticité. 
650 7 |a warping.  |2 aat 
650 7 |a buckling.  |2 aat 
650 7 |a elasticity.  |2 aat 
650 7 |a modulus of elasticity.  |2 aat 
650 7 |a Buckling (Mechanics)  |2 fast 
650 7 |a Elasticity  |2 fast 
650 7 |a Loads (Mechanics)  |2 fast 
650 7 |a Plates (Engineering)  |2 fast 
650 7 |a Sandwich construction  |2 fast 
710 2 |a Langley Aeronautical Laboratory. 
710 1 |a United States.  |b National Advisory Committee for Aeronautics. 
776 0 8 |i Print version:  |a Seide, Paul.  |t Stability under longitudinal compression of flat symmetric corrugated-core sandwich plates with simply supported loaded edges and simply supported or clamped unloaded edges  |w (OCoLC)667231146 
830 0 |a Technical note (United States. National Advisory Committee for Aeronautics) ;  |v no. 2679. 
856 4 0 |u https://appknovel.uam.elogim.com/kn/resources/kpSLCFSCC2/toc  |z Texto completo 
994 |a 92  |b IZTAP 

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