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edited by S. N. Atluri, C. E. Harris, A. Hoggard, N. Miller, and S. G. Sampath, Wolfe Associates, Alpharetta, GA
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Newman, J. C., Jr., Bigelow, C. A., and Dawicke, D. S., "FiniteElement Analyses and Fracture Simulation in Thin-Sheet Aluminum Alloy," Durability of Metal Aircraft Structures, edited by S. N. Atluri, C. E. Harris, A. Hoggard, N. Miller, and S. G. Sampath, Wolfe Associates, Alpharetta, GA, 1992.
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(1992)
Durability of Metal Aircraft Structures
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Newman Jr., J.C.1
Bigelow, C.A.2
Dawicke, D.S.3
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50
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12944277693
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Discrete Crack Growth Analysis Methodology for Through Cracks in Pressurized Fuselage Structures
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edited by C. E. Harris, NASA Langley Research Center, Hampton, VA
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Potyondy, D. O., Wawrzynek, P. A., and Ingraffea, A. R., "Discrete Crack Growth Analysis Methodology for Through Cracks in Pressurized Fuselage Structures,"Proceedings of the FAA/NASA International Symposium on Advanced Structural Integrity Methods for Airframe Durability and Damage Tolerance, edited by C. E. Harris, NASA Langley Research Center, Hampton, VA, 1994, pp. 581-602.
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(1994)
Proceedings of the FAA/NASA International Symposium on Advanced Structural Integrity Methods for Airframe Durability and Damage Tolerance
, pp. 581-602
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Potyondy, D.O.1
Wawrzynek, P.A.2
Ingraffea, A.R.3
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51
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0008447748
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Development of Advanced Structural Analysis Methodologies for Predicting Widespread Fatigue Damage in Aircraft Structures
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edited by C. A. Bigelow, Federal Aviation Administration, Washington, DC
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Harris, C. E., Starnes, J. H., Jr., and Newman, J. C., Jr., "Development of Advanced Structural Analysis Methodologies for Predicting Widespread Fatigue Damage in Aircraft Structures,"Proceedings of the FAA-NASA 6th International Conference on the Continued Airworthiness of Aircraft Structures, edited by C. A. Bigelow, Federal Aviation Administration, Washington, DC, 1995, pp. 139-164.
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(1995)
Proceedings of the FAA-NASA 6th International Conference on the Continued Airworthiness of Aircraft Structures
, pp. 139-164
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Harris, C.E.1
Starnes Jr., J.H.2
Newman Jr., J.C.3
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