Stress Intensity Factors for a Cracked Hole in a Row of Holes PDF Download
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Author: D. P. Rooke
Publisher:
ISBN:
Category :
Languages : en
Pages : 19
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Book Description
The compounding technique of obtaining stress intensity factors is applied to cracks at the edge of one hole in a row of periodically spaced holes. The cracks (one or two) lie along the line of holes and perpendicular to the uniform stress which is applied remote from the holes. This configuration models cracks at rivet holes in airframe structures reinforced with riveted stiffeners, if there is little in-plane load-transfer through the rivets. A particular feature of the solution is high accuracy of the results at short crack lengths - a necessary requirement for the reliable estimation of the lifetimes of growing cracks. (Author).
Author: D. P. Rooke
Publisher:
ISBN:
Category :
Languages : en
Pages : 19
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Book Description
The compounding technique of obtaining stress intensity factors is applied to cracks at the edge of one hole in a row of periodically spaced holes. The cracks (one or two) lie along the line of holes and perpendicular to the uniform stress which is applied remote from the holes. This configuration models cracks at rivet holes in airframe structures reinforced with riveted stiffeners, if there is little in-plane load-transfer through the rivets. A particular feature of the solution is high accuracy of the results at short crack lengths - a necessary requirement for the reliable estimation of the lifetimes of growing cracks. (Author).
Author: D.P. Rooke
Publisher:
ISBN:
Category :
Languages : en
Pages : 26
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Author: DP. Rooke
Publisher:
ISBN:
Category :
Languages : en
Pages :
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Author:
Publisher:
ISBN:
Category : Fasteners
Languages : en
Pages : 66
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Book Description
The stress-intensity factor and forces in the most highly loaded rivet and stringer were calculated for a cracked sheet with riveted and uniformly spaced stringers. Two symmetrical cases of crack location were considered - the case of a crack extending equally on both sides of a stringer and the case of a crack extending equally on both sides of a point midway between two stringers. The complete results are presented on design graphs for systematic variations of crack lengths much less than the stringer spacing. Also, the forces in the most highly loaded stringer and rivet asymptotically approach limiting values for increasing crack length. The stress-intensity factor and the limiting values of the stringer and rivet forces are smaller for stiffer or more closely spaced stringers or for more closely spaced rivets.
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 702
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Author: D.P. Rooke
Publisher:
ISBN:
Category :
Languages : en
Pages : 34
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Author: T. Nishimura
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ISBN:
Category : Crack propagation
Languages : en
Pages : 7
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Book Description
A versatile method is discussed for estimating stress intensity factors for multiple-site cracks emanating from a row of fastener holes located perpendicular to the loading direction in a finite plate. The stress intensity factor is determined by multiplying geometry factors based upon existing solutions for simpler geometries (cracks at hole, plate width, neighboring holes, and other cracks). The accuracy of the stress intensity factor is checked by comparing the solutions obtained from other literature and those calculated by the finite element method. Finally, the proposed stress intensity solution is used to estimate fatigue crack propagation for multiple-site cracks emanating from five fastener holes in a finite width plate. Through this estimate, the proposed method is assessed by comparing predictions with test results.
Author: D. S. Dawicke
Publisher:
ISBN:
Category : Airframes
Languages : en
Pages : 24
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Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 40
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Author: RC. Shah
Publisher:
ISBN:
Category : Crack propagation
Languages : en
Pages : 31
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Book Description
A procedure is formulated to derive approximate stress intensity factors for both part-through and through-the-thickness cracks originating at open holes and holes containing either loaded or unloaded close tolerance fasteners. The procedure is checked with known solutions for stress intensity factors of one or two through-the-thickness cracks emanating from an open hole in a plate subjected to uniaxial or biaxial loading. Stress intensity factors computed from this procedure for the above mentioned cases agree within seven percent of known results for the crack length to hole radius ratios, L/r, of 0.05
