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Analytical Developments in Support of the NASA Aging Aircraft Program with an Application to Crack Growth from Rivets
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Abstract
The NASA Airframe Structural Integrity Program is a multi-disciplinary program to develop analysis methodology, a fracture data base, and improved methods of NDE detection of disbonds and cracks. As part of this program, analysis tools to predict crack growth rates and fracture propagation in shell structures are being developed.
This paper describes a finite element model of crack growth in layered structures, such as lap splice joints. The model is developed using separate two-dimensional meshes of individual layers which can overlap in space. These layers can be connected with either rivet elements or by adhesive elements. Cracks can be modeled in any layer, with automatic remeshing during crack growth.
Using the model, an investigation was made of the effect of rivet interference on fatigue crack growth from a loaded rivet hole. It was found that the interference reduced the stress intensity factor range significantly, resulting in slower crack growth.
Citation
Swenson, D., Gondhalekar, S., and Dawicke, D., "Analytical Developments in Support of the NASA Aging Aircraft Program with an Application to Crack Growth from Rivets," SAE Technical Paper 931223, 1993, https://doi.org/10.4271/931223.Also In
References
- Baumgart B. G. 1975 “A Polyhedron Representation for Computer Vision,” AFIPS Proceedings 44 589 596
- Dawicke D. S. Phillips E. P. Swenson D. V. Gondhalekar S. R. 1992 “Crack Growth from Loaded Rivet Holes,” International Workshop on Structural Integrity of Aging Airplanes Atlanta, Georgia
- Erdogan F. Sih G. C. 1963 “On Crack Extensions in Plates Under Plane Loading and Transverse Shear,” A.S.M.E. Journal of Basic Engineering 85 519 527
- Gerstle W. H. Martha L. Ingraffea A. R. 1987 “Finite and Boundary Element Modeling of Crack Propagation in Two - and Three - Dimensions,” Engineering with Computers 2 167 183
- Harris Charles E. 1991 “NASA Airframe Structural Integrity Program,” Structural Integrity of Aging Airplanes Springer-Verlag 433 484
- Hussain M. A. Pu S.L. Underwood J. H. 1974 “Strain Energy Release Rate for a Crack Under Combined Mode I and Mode II,” Fracture Analysis, ASTM, STP 560 2 28
- Saouma V. E. Ingraffea A. R. 1981 “Fracture Mechanics Analysis of Discrete Cracking,” Colloquium on Advanced Mechanics of Reinforced Concrete International Association of Bridge and Structural Engineers Delft 393 416
- Shaw R. D. Pitchen R. G. 1978 “Modifications to the Suhara-Fukuda Method of Network Generation,” International Journal for Numerical Methods in Engineering 12 93 99
- Sih G. C. 1974 “Strain-Energy-Density Factor Applied to Mixed-Mode Crack Problems,” International Journal of Fracture Mechanics 10 305 321
- Swenson D. V. Ingraffea A. R. 1988 “Modelling Mixed-Mode Dynamic Crack Propagation Using Finite Elements: Theory and Applications” Computational Mechanics 3 187 192
- Swenson D. V. Chih-Chien C. Derber T. 1992 “Analytical and Experimental Investigation of Fatigue in Lap Joints,” Advances in Fatigue Lifetime Predictive Techniques, ASTM STP 1122 Mitchell M. R. Landgraf R. W. American Society for Testing and Materials Philadelphia 449 459
- Underwood P. 1983 “Dynamic Relaxation,” Computational Methods for Transient Analysis 1 Belytchko T. Huges J. R. North Holland, Amsterdam
- Wawrzynek P. Ingraffea A. R. 1987 “Interactive Finite Element Analysis of Fracture Processes: An Integrated Approach,” Theoretical and Applied Fracture Mechanics 8 137 150
- Weiler K. 1985 “Edge-Based Data Structures for Solid Modeling Curved-Surface Environments,” IEEE Comp. Graph. & App. 5 1 21 40
- Woo T. C. 1985 “A Combinatorial Analysis of Boundary Data Structure Schemata,” IEEE Computer Graphics & Applications 5 3. 19 27