A simplified method of elastic-stability analysis for thin cylindrical shells
By: by S.B. Batdorf
Contributors: United States. National Advisory Committee for Aeronautics
Series: Report / National Advisory Committee for Aeronautics -- no. 874; Report (United States. National Advisory Committee for Aeronautics) -- no. 874.
Publisher: U.S. G.P.O.
Published: 1947
Place of publication: Washington, D.C
Language: eng
Number of pages: 25
ISBN-13: 9781680156454
Subjects: Stability of airplanes; Aerodynamic load; Airplanes; Design and construction
Description: 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. --
Notes: Includes bibliographical references.