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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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Asymptotic and particular solutions of conical shells subjected to lateral normal loads, discussing membrane forces, bending effects and boundary conditions for moments and shearing force
Calculation of forces, moments, strains, and displacements occurring in deformation of conic shell under action of force load and nonuniform heating - hypergeometrical functions
Vibration analysis on ring stiffened conical shell reentry configuration
Acoustic radiation efficiency and structural vibration characteristics of truncated conical shells
Vibration and flutter tests of pressurized thin walled truncated conical shell
Two ring-stiffened magnesium conical shells with a 120 deg apex angle and a 4.6-meter diameter were loaded to failure by a uniform external pressure. The cones differed from one another only in the number of internal stiffening rings. Test specimen details, test procedure, and test results are discussed. Both buckling and prebuckling data are compared with appropriate theoretical predictions. Measured strains in skin and rings agreed well with theoretical predictions. Extensive imperfection measurements were made and reported on both cones in the as fabricated condition.
Basic equations and solutions for conical shells of linearly varying thickness subjected to lateral loads
Postwrinkling nonlinear behavior of conical shell of revolution subjected to bending loads
Prediction of vibration frequencies and modes for free-free truncated conical shells, using Rayleigh-Ritz method
Design procedure for end rings of isotropic conical shells loaded by external pressure
Thermal effect on isotropic conical shells of linearly varying thickness
Post-wrinkling nonlinear behavior of conical shell of revolution subjected to bending loads
Equations for stability analysis on truncated conical shells with elastic edge restraint
Supersonic asymmetric flutter and divergence characteristics of truncated conical shells with ring-supported edges under three types of flow-induced instabilities
1. Criteria are presented for the elastic instability of thin single and multilayer conical and cylindrical shells under combined axial load and external pressure. These criteria, used in design analysis, are based on theoretical results and the correlation of these results with readily available experimental data. 2. A summary is included of the studies at Avco RAD of shells under static or dynamic loads.
Edge constraint effect on buckling of sandwich and ring stiffened conical shells under external pressure
Theoretical and experimental vibration and buckling results for blunt truncated conical shells with ring supported edges
Design study methods and results for a composite reinforced base ring for the conical aeroshell structure of the planetary lander vehicle for Project Viking, an unmanned mission to Mars, are presented. The aeroshell is a ring and stringer-stiffened conical shell structure having a half angle of 70 degrees with a large base ring mounted at the outer edge of the cone and a large pay-load ring in the interior with many smaller rings spaced along the inside shell surface. The purpose of the structure is to develop the aerodynamic drag required to decelerate the lander in the Mars atmosphere to facilitiate a soft landing. The design of a shell structure of this complexity requires the use of the latest technology available in a large general-purpose shell buckling program. The large general-purpose non-linear shell buckling program (BOSOR 2) which was used for this purpose is described.