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  Partner: UNT Libraries Government Documents Department
 Serial/Series Title: NACA Technical Memorandums
 Collection: Technical Report Archive and Image Library
The stress criterion of a tension member with graded flexural stiffness : contribution to the problem of "clamping effect" outside of the elastic range

The stress criterion of a tension member with graded flexural stiffness : contribution to the problem of "clamping effect" outside of the elastic range

Date: September 1, 1936
Creator: Kaul, Hans W
Description: The approximate size of the stress criterion of a bar on two supports stressed beyond the elastic range is assessed by an approximation. The calculation proceeds from the premise of "substitute flexural stiffness" so defined that the part stressed beyond the elastic range may be considered as following Hooke's law when determining the flexural deformation quantities. For the determination of the substitute flexural stiffness, it is presumed that the material is already stressed so much beyond the yield point as to be strain-hardened. The data are directly applicable to materials having no definite yield point. For the rest, von Karman's method for compressed and subsequently deflected bars serves as basis for the calculation.
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The stress distribution in shell bodies and wings as an equilibrium problem

The stress distribution in shell bodies and wings as an equilibrium problem

Date: February 1, 1937
Creator: Wagner, H
Description: This report treats the stress distribution in shell-shaped airplane components (fuselage, wings) as an equilibrium problem; it includes both cylindrical and non-cylindrical shells. In particular, it treats the stress distribution at the point of stress application and at cut-out points.
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Stressed coverings in naval and aeronautic construction

Stressed coverings in naval and aeronautic construction

Date: January 1, 1928
Creator: Kahn, L L
Description: We propose to make a study of the difficulties in using stressed coverings and their appropriate solutions. Fatigue and buckling are also discussed.
Contributing Partner: UNT Libraries Government Documents Department
Stresses developed in seaplanes while taking off and landing

Stresses developed in seaplanes while taking off and landing

Date: July 1, 1932
Creator: Verduzio, Rudolfo
Description: In the case of seaplanes, the lack of elastic shock absorbers, the presence of which might be quite dangerous, especially in taking off, makes it necessary to give some consideration to the phenomenon of landing. Special consideration must be given the process of taking off, since even moderately rough water may develop rather large stresses. The purpose of this communication is to show what has been accomplished in Italy and other countries and to draw a few useful conclusions.
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The stresses in columns under combined axial and side loads

The stresses in columns under combined axial and side loads

Date: July 1, 1922
Creator: Arnstein, Karl
Description: The problem before us is to determine the total stresses in an axially loaded column of any degree of restraint which is also subject to transverse bending both from a uniformly distributed load and from concentrated loads.
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Stresses in reinforcing rings due to axial forces in cylindrical and conical stressed skins

Stresses in reinforcing rings due to axial forces in cylindrical and conical stressed skins

Date: January 1, 1938
Creator: Drescher, K & Gropler, H
Description: At the ends of a monocoque fuselage concentrated axial forces in the skin must generally be taken up. Such axial forces must also be taken up in the case of other members where axial forces from the neighboring stressed skin construction must be considered. In order to take up these axial forces two bulkheads or reinforcing frames may be arranged at the positions where the forces are applied. If these bulkheads are in the form of rings, bending moments are set up in them. In the present paper computations are performed for obtaining the value of these bending moments.
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Stresses in single-spar wing constructions with incompletely built-up ribs

Stresses in single-spar wing constructions with incompletely built-up ribs

Date: January 30, 1940
Creator: Reinitzhuber, F
Description: It is shown that the force distribution resulting from incomplete ribs in single spar wing structures may be determined with the aid of the shear field method by a statistically indeterminate computation. A numerical computation is given of the force distribution of a wing structure whose two neighboring incomplete ribs with web missing in half the section are torsionally loaded.
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The stresses in stiffener openings

The stresses in stiffener openings

Date: February 1, 1942
Creator: Marguerre, K
Description: The present study treats as a typical example a ring the center line of which is produced by the intersection of two circular cylinders of different diameter. Three load cases are analyzed: (1) Axial and circumferential stresses in both cylinders, the cylinder stresses themselves to be in the ratio conformal to the cylinders loaded under internal pressure. (2) Pure longitudinal tension in the large cylinder. (3) Pure shear (torsion) in the large cylinder. To simplify the calculation, it is assumed that the ring, compared to the shell, is very strong, so that its deformations have no perceptible effect on the stress condition in the shell. This provides an upper limit for the ring stresses actually produced in a shell design, for, according to the theory of stressed skin statics the shells, by elastic flexibility of the ring, regroup the forces deposited on it in such a manner that the ring is relieved.
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Stresses Produced in Airplane Wings by Gusts

Stresses Produced in Airplane Wings by Gusts

Date: January 1, 1932
Creator: Kussner, Hans Georg
Description: Accurate prediction of gust stress being out of the question because of the multiplicity of the free air movements, the exploration of gust stress is restricted to static method which must be based upon: 1) stress measurements in free flight; 2) check of design specifications of approved type airplanes. With these empirical data the stress must be compared which can be computed for a gust of known intensity and structure. This "maximum gust" then must be so defined as to cover the whole ambit of empiricism and thus serve as prediction for new airplane designs.
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Structural and economic limits to the dimensions of airships

Structural and economic limits to the dimensions of airships

Date: August 1, 1924
Creator: Crocco, G A
Description: In opposition to the advantage of larger dimensions, there is one disadvantage, namely, the weight of the structure increases more rapidly than the buoyancy. It is not possible, however, to determine a general law. In order to formulate one having the merit of simplicity, we will divide the structure into two parts: one subject to tensile and compressive stresses, varying directly as the ascensional or lifting forces; the other subject to varying stresses of the surface areas.
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