Add to ORKGThis 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
The present study treats as a typical example a ring the center line of which is produced by the int...
The structural analysis of arbitrary solid cantilever wings by small-deflection thin-plate theory is...
This lecture concerns the combining effects in airplane wings so as to save some of the dead weight
This report treats the stress distribution in shell-shaped airplane components (fuselage, wings) as ...
The monocoque form of airplane construction has introduced a number of new problems to the stress ca...
Thin-walled shells with strong longitudinal and transverse stiffening (for example, stressed-skin fu...
Report analyzes the stresses in a fuselage of the built-up type in which the shear is taken by diago...
This report is a compilation of previously published articles on formulas and methods of calculation...
This paper described the identification of the maximum value of stress that acts at the wing-fuselag...
The analysis of various types of shell under combined bending and torsion is discussed. The calculat...
In practice the actual maximum stress is greater than the stress determined by the simple girder the...
On the wing structures of modern high speed aircraft, in particular, the comparatively high-service ...
Equations are derived for the stress distributions caused by three types of loading on infinitely lo...
The stress relations to the fabric and the rib consequent upon a change of spacing between ribs in a...
The author gives a survey of the principles of stress analysis and design of airplane structures, an...
The present study treats as a typical example a ring the center line of which is produced by the int...
The structural analysis of arbitrary solid cantilever wings by small-deflection thin-plate theory is...
This lecture concerns the combining effects in airplane wings so as to save some of the dead weight
This report treats the stress distribution in shell-shaped airplane components (fuselage, wings) as ...
The monocoque form of airplane construction has introduced a number of new problems to the stress ca...
Thin-walled shells with strong longitudinal and transverse stiffening (for example, stressed-skin fu...
Report analyzes the stresses in a fuselage of the built-up type in which the shear is taken by diago...
This report is a compilation of previously published articles on formulas and methods of calculation...
This paper described the identification of the maximum value of stress that acts at the wing-fuselag...
The analysis of various types of shell under combined bending and torsion is discussed. The calculat...
In practice the actual maximum stress is greater than the stress determined by the simple girder the...
On the wing structures of modern high speed aircraft, in particular, the comparatively high-service ...
Equations are derived for the stress distributions caused by three types of loading on infinitely lo...
The stress relations to the fabric and the rib consequent upon a change of spacing between ribs in a...
The author gives a survey of the principles of stress analysis and design of airplane structures, an...
The present study treats as a typical example a ring the center line of which is produced by the int...
The structural analysis of arbitrary solid cantilever wings by small-deflection thin-plate theory is...
This lecture concerns the combining effects in airplane wings so as to save some of the dead weight