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Calculation of Load Distribution in Stiffened Cylindrical Shells

Description: "Thin-walled shells with strong longitudinal and transverse stiffening (for example, stressed-skin fuselages and wings) may, under certain simplifying assumptions, be treated as static systems with finite redundancies. In this report the underlying basis for this method of treatment of the problem is presented and a computation procedure for stiffened cylindrical shells with curved sheet panels indicated. A detailed discussion of the force distribution due to applied concentrated forces is given, and the discussion illustrated by numerical examples which refer to an experimentally determined circular cylindrical shell" (p. 1).
Date: June 1938
Creator: Ebner, H. & K├Âller, H.
Partner: UNT Libraries Government Documents Department

The Strength of Shell Bodies: Theory and Practice

Description: "The monocoque form of airplane construction has introduced a number of new problems to the stress calculator and the designer. The problems for the stress calculator fall into two groups: the determination of the stress condition (shell statics) and the determination of the failing strength (shell strength). The present report summarizes the most important theoretical and experimental results on this subject" (p. 1).
Date: September 1937
Creator: Ebner, H.
Partner: UNT Libraries Government Documents Department

The Strength of Shell and Tubular Spar Wings

Description: The report is a survey of the strength problems arising on shell and tubular spar wings. The treatment of the shell wing strength is primarily confined to those questions which concern the shell wing only; those pertaining to both shell wing and shell body together have already been treated in TM 838. The discussion of stress condition and compressive strength of shell wings and tubular spar wings is prefaced by several considerations concerning the spar and shell design of metal wings from the point of view of strength.
Date: February 1940
Creator: Ebner, H.
Partner: UNT Libraries Government Documents Department

Methods and Formulas for Calculating the Strength of Plate and Shell Constructions as Used in Airplane Design

Description: "This report is a compilation of previously published articles on formulas and methods of calculation for the determination of the strength and stability of plate and shell construction as employed in airplane design. In particular, it treats the problem of isotropic, orthotopic, and stiffened rectangular plates, thin curved panels, and circular cylinders under various loading conditions. The purpose of appending the pertinent literature references following the subjects discussed was to facilitate a comprehensive study of the treated problems" (p. 1).
Date: February 1936
Creator: Heck, O. S. & Ebner, H.
Partner: UNT Libraries Government Documents Department