A simplified method of elastic-stability analysis for thin cylindrical shells /

This paper develops a new method for determining the buckling stresses of cylindrical shells under various loading conditions. In part I, the equation for the equilibrium of cylindrical shells introduced by Donnell in NACA report no. 479 to find the critical stresses of cylinders in torsion is appli...

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Detalles Bibliográficos
Clasificación:Libro Electrónico
Autor principal: Batdorf, S. B.
Autor Corporativo: United States. National Advisory Committee for Aeronautics
Formato: Electrónico eBook
Idioma:Inglés
Publicado: Washington, D.C. : U.S. G.P.O., 1947.
Colección:Report (United States. National Advisory Committee for Aeronautics) ; no. 874.
Temas:
Stability of airplanes.
Aerodynamic load.
Airplanes > Design and construction.
Avions > Stabilité.
Charge aérodynamique.
Avions > Conception et construction.
Aerodynamic load
Airplanes > Design and construction
Stability of airplanes
Acceso en línea:Texto completo

MARC

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049 |a UAMI 
100 1 |a Batdorf, S. B. 
245 1 2 |a A simplified method of elastic-stability analysis for thin cylindrical shells /  |c by S.B. Batdorf. 
260 |a Washington, D.C. :  |b U.S. G.P.O.,  |c 1947. 
300 |a 1 online resource (25 pages) 
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 Report / National Advisory Committee for Aeronautics ;  |v no. 874 
504 |a Includes bibliographical references. 
588 0 |a Print version record. 
520 |a This paper develops a new method for determining the buckling stresses of cylindrical shells under various loading conditions. In part I, the equation for the equilibrium of cylindrical shells introduced by Donnell in NACA report no. 479 to find the critical stresses of cylinders in torsion is applied to find critical stresses for cylinders with simply supported edges under other loading conditions. In part II, a modified form of Donnell's equation for the equilibrium of thin cylindrical shells is derived which is equivalent to Donnell's equation but has certain advantages in physical interpretation and in ease of solution, particularly in the case of shells having clamped edges. --  |c Provided by publisher. 
590 |a Knovel  |b ACADEMIC - Aerospace & Radar Technology 
650 0 |a Stability of airplanes. 
650 0 |a Aerodynamic load. 
650 0 |a Airplanes  |x Design and construction. 
650 6 |a Avions  |x Stabilité. 
650 6 |a Charge aérodynamique. 
650 6 |a Avions  |x Conception et construction. 
650 7 |a Aerodynamic load  |2 fast 
650 7 |a Airplanes  |x Design and construction  |2 fast 
650 7 |a Stability of airplanes  |2 fast 
710 1 |a United States.  |b National Advisory Committee for Aeronautics. 
776 0 8 |i Print version:  |a Batdorf, S.B.  |t Simplified method of elastic-stability analysis for thin cylindrical shells.  |d Washington, D.C. : U.S.G.P.O., 1947  |w (OCoLC)46875301 
830 0 |a Report (United States. National Advisory Committee for Aeronautics) ;  |v no. 874. 
856 4 0 |u https://appknovel.uam.elogim.com/kn/resources/kpSMESATC6/toc  |z Texto completo 
994 |a 92  |b IZTAP 

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