Fracture Mechanics of Thin Plates and Shells Under Combined Membrane, Bending, and Twisting Loads-Reference-Cited by-同舟云学术

Fracture Mechanics of Thin Plates and Shells Under Combined Membrane, Bending, and Twisting Loads

Published:2005-01-01 Issue:1 Volume:58 Page:37-48
ISSN:0003-6900
Container-title:Applied Mechanics Reviews
language:en
Short-container-title:

Author:

Zehnder Alan T.¹,Viz Mark J.²

Affiliation:

1. Department of Theoretical and Applied Mechanics, Cornell University, Ithaca, NY 14853–1502

2. Exponent Failure Analysis Associates, Chicago, IL 60606

Abstract

The fracture mechanics of plates and shells under membrane, bending, twisting, and shearing loads are reviewed, starting with the crack tip fields for plane stress, Kirchhoff, and Reissner theories. The energy release rate for each of these theories is calculated and is used to determine the relation between the Kirchhoff and Reissner theories for thin plates. For thicker plates, this relationship is explored using three-dimensional finite element analysis. The validity of the application of two-dimensional (plate theory) solutions to actual three-dimensional objects is analyzed and discussed. Crack tip fields in plates undergoing large deflection are analyzed using von Ka´rma´n theory. Solutions for cracked shells are discussed as well. A number of computational methods for determining stress intensity factors in plates and shells are discussed. Applications of these computational approaches to aircraft structures are examined. The relatively few experimental studies of fracture in plates under bending and twisting loads are also reviewed. There are 101 references cited in this article.

Publisher

ASME International

Subject

Mechanical Engineering

Link

http://asmedigitalcollection.asme.org/appliedmechanicsreviews/article-pdf/58/1/37/5440932/37_1.pdf

Reference101 articles.

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2. Potyondy, D., Wawrzynek, P., and Ingraffea, A., 1994, “Discrete Crack Growth Analysis Methodology for Through Cracks in Pressurized Fuselage Structures,” Harris, C., ed. FAA-NASA Int. Symp. on Advanced Structural Integrity Methods for Airframe Durability and Damage Tolerance2, pp. 581–601, NASA CP3274.

3. Harris, C.E., Newman, J.C., Piascik, R.S., and Starnes, J.H., 1997, “Analytical Methodology for Predicting the Onset of Widespread Fatigue Damage in Fuselage Structure,” FAA-NASA Symp. on the Continued Airworthiness of Aircraft Structures, pp. 63–88 DOT/FAA/AR-97/2.

4. Kirchhoff, G. , 1850, “U¨ber das gleichgewicht und die bewegung einer elastischen scheibe,” J. Reine Angew. Math. 40, pp. 51–88.

5. Sih, G., Paris, P., and Erdogan, F., 1962, “Crack-tip Stress-intensity Factors for Plane Extension and Plane Bending Problems,” ASME J. Appl. Mech. 29, pp. 306–312.

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