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Author: National Aeronautics and Space Administration (NASA) Publisher: Createspace Independent Publishing Platform ISBN: 9781722113919 Category : Languages : en Pages : 26
Book Description
The experimental stress intensity factors for various chevron notched four point bend specimens are presented. The experimental compliance is verified using the analytical solution for a straight through crack four point bend specimen and the boundary integral equation method for one chevron geometry. Excellent agreement is obtained between the experimental and analytical results. In this report, stress intensity factors, loading displacements and crack mouth opening displacements are reported for different crack lengths and different chevron geometries, under four point bend loading condition. Calomino, Anthony and Bubsey, Raymond and Ghosn, Louis J. Glenn Research Center RTOP 505-63-12...
Author: National Aeronautics and Space Administration (NASA) Publisher: Createspace Independent Publishing Platform ISBN: 9781722113919 Category : Languages : en Pages : 26
Book Description
The experimental stress intensity factors for various chevron notched four point bend specimens are presented. The experimental compliance is verified using the analytical solution for a straight through crack four point bend specimen and the boundary integral equation method for one chevron geometry. Excellent agreement is obtained between the experimental and analytical results. In this report, stress intensity factors, loading displacements and crack mouth opening displacements are reported for different crack lengths and different chevron geometries, under four point bend loading condition. Calomino, Anthony and Bubsey, Raymond and Ghosn, Louis J. Glenn Research Center RTOP 505-63-12...
Author: GR. Sarrafi-Nour Publisher: ISBN: Category : Compliance Languages : en Pages : 5
Book Description
Various fracture tests employing chevron-notched flexure specimens require accurate measurement of the specimen loading-point compliance at least through the achievement of the maximum load. Conventionally this compliance is determined by monitoring the center-point deflection on the specimen and then correcting the measured displacements for the compliance of the test setup, determined through separate calibration tests. A simple and accurate indirect determination of the compliance under flexure load condition, which is not affected by the compliance of the test setup used for fracture testing, was introduced previously. This method has been verified for flexure specimens containing throughthickness cracks. The present work deals with the application of the indirect compliance measurement method to chevron-notched flexure specimens. The original governing relation, previously verified for a specimen with a through-thickness crack, is modified based on finite element analysis results so as to be applicable to the chevronnotched specimens. After modification, this method is shown to lead also to accurate determination of the loading-point compliance in tests involving chevron-notched specimens.
Author: Richard Carl Bradt Publisher: Springer Science & Business Media ISBN: 9780306410222 Category : Technology & Engineering Languages : en Pages : 698
Author: National Aeronautics and Space Administration (NASA)
Author: National Aeronautics and Space Administration (NASA)
Author: Anthony Martin Calomino
Author: John H. Underwood
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Author: GR. Sarrafi-Nour
Author: Richard Carl Bradt
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