Force/Stiffness Technique for Nondestructive Buckling Testing

Jones, Robert E.; Greene, B. E.

doi:10.2514/3.58655

Cited by 5 publications

(1 citation statement)

References 3 publications

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“…(Application of the force-stiffness method is dependent on proper identification of the failure mode.) 12 Thus, it appears that although the inserts suppressed the general instability mode of failure, they did not adequately prevent distortion of the fluted tube. It is therefore apparent that extensive analytical and experimental study of the fluted tubular configuration will be required if its potential structural efficiency is to be attained.…”

Section: Fluted Tubular Configurationmentioning

confidence: 96%

Evaluation of Bead-Stiffened Metal Panels

Shideler

Bohon

Greene

1976

Journal of Spacecraft and Rockets

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Potential weight efficiency for bead-stiffened panels has been demonstrated through fabrication and testing. Theoretically optimum design concepts were identified, and small specimens were tested under combined compression, shear, and bending to determine local buckling failure loads and to verify theory. Large optimized panels were then designed and tested under combined loads. Correlation of test data for large circular tubular panels with theory was conservative and consistent, and indicated reliable and acceptable design theory. Tests of fluted tubular panels indicated general instability failures at loads far below the design values because of nonlinear distortions. Further study of the fluted tubular configuration will be required if its potential weight efficiency is to be attained. Nomenclature F^= compression yield stress N x = panel axial compression load Nxy = panel shear load p = pressure q = heating rate R B ,R C ,R S = ratios of actual stress to critical stress for bending, compression, and shear, respectively T = temperature t = rime p = density

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Section: Fluted Tubular Configurationmentioning

confidence: 96%

Evaluation of Bead-Stiffened Metal Panels

Shideler

Bohon

Greene

1976

Journal of Spacecraft and Rockets

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Continuous Filament Advanced Composite Isogrid: A Promising Structural Concept

Rehfield¹,

Deo²,

Renieri

1980

Fibrous Composites in Structural Design

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This paper summarizes research performed to explore the potential of a new, promising structural concept--continuous filament advanced composite isogrid. This is the first attempt to evaluate load bearing capacity of the concept. Preliminary data has been obtained by the design, fabrication and test of flat panels as wide columns. Inconsistency in manufacturing is clearly identified as the major reason for scatter in observed data, a problem which would be minimized in a production environment. In spite of scatter, the results presented are a major step toward inspiring the necessary confidence in the use of this concept in airframe structure.

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