Onset of multiple site damage and widespread fatigue damage in aging airplanes
Bibliographic record
Abstract
No abstract is available for this record. The assistant can identify its topic from the title, but cannot infer the study’s results.
Source: Not provided · Quality: missing
Research context
OpenAlex topics: Fatigue and fracture mechanics · Probabilistic and Robust Engineering Design · Mechanical Failure Analysis and Simulation
SciVX discovery tags are terminology-based. OpenAlex topics are source-provided classifications.
References (25)
Show source-provided references
1. Anon. (1993). Damage Tolerance Assessment Handbook, Volume I, Final Report, DOT/FAA/CT-93/69.1, DOT-VNTSC-FAA-93-13.1.
2. Atluri, S.N. (1986). Energetic approaches and path-independent integrals. Computational Methods in the Mechanics of Fracture, edited by Atluri, S.N., North Holland Publishers, 123–165.
3. Broek, D., Jeong, D.Y. and Thomson, D. (1994). Testing and analysis of flat and curved panels with multiple cracks. FAA/NASA International Symposium on Advanced Structural Integrity Methods for Airframe Durability and Damage Tolerance, NASA Conference Publication 3274, Part 1, 85–98.
4. Jeong, D.Y. and Tong, P. (1994). Nonlinear bulging factor based on R-curve data. FAA/NASA International Symposium on Advanced Structural Integrity Methods for Airframe Durability and Damage Tolerance, NASA Conference Publication 3274, Part 1, 327–338.
5. Jeong, D.Y. and Brewer, J.C. (1995). On the linkup of multiple cracks. Engineering Fracture Mechanics 51, 233–238.10.1016/0013-7944(94)00267-L ↗
6. Jeong, D.Y., Roach, D.P., Canha, J.V., Brewer, J.C. and Flournoy, T.H. (1995). Strain Fields in Boeing 737 Fuselage Lap splices: Field and Laboratory Measurements with analytical Correlations. Final Report, DOT/FAA/CT-95/25, DOT-VNTSC-FAA-95-10.
7. Maclin, J.R. (1992). Performance of fuselage pressure structure. 1991 International Conference on Aging Aircraft and Structural Airworthiness, NASA Conference Publication 3160, 67–74.
8. Newman, Jr., J.C., Dawicke, D.S., Sutton, M.A. and Bigelow, C.A. (1993). A fracture criterion for widespread cracking in thin-sheet aluminum alloys. 17th Symposium of the International Committee on Aeronautical Fatigue, Stockholm, Sweden.
9. Nikishkov, G.P. and Atluri, S.N. (1994). An analytical-numerical alternating method of elastic-plastic analysis of cracks. Computational Mechanics 13, 427–442.10.1007/BF00374239 ↗
10. Park, J.H. and Atluri, S.N. (1993). Fatigue growth of multiple cracks near a row of fastener holes in a fuselage lap joint. Computational Mechanics 13, 189–203.10.1007/BF00370135 ↗
11. Pyo, C.R., Okada, H. and Atluri, S.N. (1995). An elastic-plastic finite element alternating method for analyzing widespread fatigue damage in aircraft structures. Computational Mechanics 16, 62–68.10.1007/BF00369886 ↗
12. Samavedam, G. and Hoadley, D. (1994). Fracture and Fatigue Strength Evaluation of Multiple Site Damaged Aircraft Fuselages — Curved Panel Testing and Analysis, Final Report, DOT/FAA/CT-94/10, DOT-VNTSC-FAA-93-8.
13. Samavedam, G., Hoadley, D. and Thomson, D. (1993). Full-Scale Testing and Analysis of Curved Aircraft Fuselage Panels, DOT/FAA/CT-93/78, DOT-VNTSC-FAA-93-10.
14. Samavedam, G., Thomson, D. and Jeong, D.Y. (1994). Evaluation of the fuselage lap joint fatigue and terminating action repair. FAA/NASA International Symposium on Advanced Structural Integrity Methods for Airframe Durability and Damage Tolerance, NASA Conference Publication 3274, Part 2, 653–664.
15. Schijve, J. (1983). Stress intensity factors of hole edge cracks, comparison between one crack and two symmetric cracks. International Journal of Fracture 23, R111–R115.10.1007/BF00028833 ↗
16. Swift, T. (1974). The effects of fastener flexibility and stiffener geometry on the stress intensity in stiffened cracked sheet. Prospects of Fracture, Noordhoff International, Leyden, The Netherlands, 419–536.10.1007/978-94-010-2314-6_25 ↗
17. Swift, T. (1971). Development of the fail-safe design features of the DC-10. Damage Tolerance in Aircraft Structures, ASTM STP 486, American Society for Testing and Materials, Philadelphia, PA, 164–214.10.1520/STP26678S ↗
18. Swift, T. (1993). Widespread fatigue damage monitoring — issues and concerns. Proceedings of the 5th International Conference on Structural Airworthiness of New and Aging Aircraft, DGLR-Bericht 93-02, 133–150.
19. Swift, T. (1992). Damage tolerance capability. Specialists Conference on Fatigue of Aircraft Materials, Delft University of Technology.
20. Tada, H., Paris, P. and Irwin, G. (1985). The Stress Analysis of Cracks Handbook, Second Edition, Paris Productions, Inc.
21. Tong, P. (1994). Influence of fastener holes on residual strength. International Journal of Fracture 67, 351–324.10.1007/BF00032498 ↗
22. Tong, P., Greif, R. and Chen, L. (1994). Residual strength of aircraft panels with multiple site damage. Computational Mechanics 13, 285–294.10.1007/BF00350230 ↗
23. Tong, P., Greif, R., Chen, L. and Jeong D.Y. (1993). Damage tolerance of fuselage panels with widespread fatigue damage. 17th Symposium of the International Committee on Aeronautical Fatigue, Stockholm, Sweden.
24. Walker, E.K. (1970). The effect of stress ratio during crack propagation and fatigue for 2024-T3 and 7075-T6 aluminum. Effects of Environment and Complex Load History on Fatigue Life, ASTM STP 462, American Society for Testing and Materials, Philadelphia, PA, 1–14.
25. Wang, L., Chow, W.T., Kawai, H. and Atluri, S.N. (1996). Predictions of widespread fatigue damage threshold. Proceedings of the FAA/NASA Symposium on Continued Airworthiness of Aircraft Structures, Atlanta GA.