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Search indexed NASA NTRS and DOE OSTI research on propulsion, heat transfer, battery materials and energy systems. Follow report and document links to the original sources.

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At least 667 records · Page 37

All sources NASA NTRS DOE OSTI

NASA NTRS1949

Plastic buckling of extruded composite sections in compression

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PLATES - BUCKLING↗

NASA NTRSDate not supplied

NASA Shell Buckling Knockdown Factor Project

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Shell Buckling↗

NASA NTRSDate not supplied

NASA Shell Buckling Knockdown Factor Project

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Shell Buckling↗

DOE OSTI2025

Influence of pore geometry and distribution on buckling under micro computed tomography

Not Available

36 MATERIALS SCIENCE↗

NASA NTRS1966

Literature survey on the buckling of conical shells

Bibliography on conical shell instability

SHELL STABILITY↗

NASA NTRS1967

Initial post-buckling behavior of toroidal shell segments.

Initial postbuckling behavior of double curvature shell segments under several loading conditions determined, using Koiter theory

ELASTIC BUCKLING↗

NASA NTRS1967

Symmetric and nonsymmetric buckling of finitely deformed eccentrically stiffened shells of revolution.

Finite difference method stability analysis of deformed eccentrically stiffened shells of revolution, accounting for finite prebuckling rotations

FINITE DIFFERENCE METHOD↗

NASA NTRS1967

Symmetric and nonsymmetric buckling of finitely deformed eccentrically stiffened shells of revolution.

Finite difference method stability analysis of deformed eccentrically stiffened shells of revolution, accounting for finite prebuckling rotations

FINITE DIFFERENCE METHOD↗

NASA NTRS1948

The Inward Bulge Type Buckling of Monocoque Cylinders IV : Experimental Investigation of Cylinders Subjected to Pure Bending

Eighteen 24S-T alclad cylinders of 20-inch diameter, with skin thickness varying between 0.012 inch and 0.025 inch and length varying between 40.5 inches and 64 inches, were tested in pure bending. They were reinforced with either 16 or 28 stringers and either 5 or 6 rings. One of the purposes of the investigation was to establish the critical value above which failure would occur by general instability and below which panel instability would take place. This value was found to be between 20 and 40 for cylinders with 16 stringers and between 16 and 74 for cylinders with 28 stringers.

LOADS - CYLINDERS, MONOCOQUE↗

NASA NTRS1948