Characterization of fatigue crack growth in aluminium panels with a bonded composite patch

Composite Structures

Volumn 37, Issue 3-4, 1997, Pages 321-334

  Naboulsi, S ^a   Mall, S ^a  

^a AIR FORCE INSTITUTE OF TECHNOLOGY   (United States)

Author keywords

[No Author keywords available]

Indexed keywords

ALUMINUM; BONDING; COMPUTATIONAL METHODS; CRACK PROPAGATION; FATIGUE TESTING; FINITE ELEMENT METHOD; PLATES (STRUCTURAL COMPONENTS); SHEAR DEFORMATION; STRESS INTENSITY FACTORS; STRUCTURAL PANELS;

MINDLIN PLATES; PARIS LAW;

COMPOSITE STRUCTURES;

EID: 0031084182     PISSN: 02638223     EISSN: None     Source Type: Journal    
DOI: 10.1016/S0263-8223(98)80003-2     Document Type: Article

References (17)

1. Baker, A.A. and Jones, R., Bonded Repair of Aircraft Structures, Chapter 4-5. Martinus Nijhoff Publishers, 1988.
2. Jones, R., Bonded repair of damage. J. Aero. Soc. (India) 1984, 36, 193-201.
3. Rose, L.R.F., An application of the inclusion analogy for bonded reinforcements. Int. J. Solids Structures 1981, 17, 827-838.
4. Ratwani, M.M., A parametric study of fatigue crack growth behavior in adhesively bonded metallic structures. J. Engng Mats and Tech. 1978, 100, 46-51.
5. Sun, C.T., Klug, J. and Arendt, C., Analysis of cracked aluminum plates repaired with bonded composite patches. AIAA Journal 1996, 34(2), 369-374.
6. Young, M.J., Rooke, D.P. and Cartwright, D.J., Analysis of patched and stiffened cracked panels using the boundary element method. Int. J. Solids Structures 1992, 29(17), 2201-2216.
7. Naboulsi, S. and Mall, S., Modeling of cracked metallic structure with bonded composite patch using three layer technique. Composite Structures 1996, 35, 295-308.
8. Naboulsi, S. and Mall, S., Thermal effects on adhesively bonded composite patch repair of cracked aluminum panels. Theoretical and applied fracture mechanics, 1997, 26, 1-12.
9. Ratwani, M.M., Analysis of cracked adhesively bonded laminated structures. AIAA Journal 1979, 17, 988-994.
10. Sun, C. T. and Arendt, C., Bending effects of unsymmetric adhesively bonded composite repairs on cracked aluminum panels. In Proceedings FAA/NASA Int. Symposium on Advanced Structural Integrity Methods for Airframe Durability and Damage Tolerance, Part I, Hampton, Virginia, May 4-6, 1994.
11. Rybicki, E.F. and Kanninen, E.F., A finite element calculation of stress intensity factors by a modified crack closure integral. Engng Fracture Mechanics 1977, 9, 931-938.
12. Young, M.J. and Sun, C.T., On the strain energy release rate for a cracked plate subjected to out-of-plane bending moment. Int. J. Fracture 1993, 60, 227-247.
13. Denney, J. J. and Mall, S. Effect of disbond on fatigue behavior of cracked aluminum panel with bonded composite patch. In Proceedings of the 37th AIAA/ ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Material Conference, volume part I, pp. 14-21, Salt Lake City, April 15-17, 1996.
14. Standard test methods for measurement of fatigue crack growth rates. ASTM E64, 1991.
15. Baker, A.A., Repair efficiency in fatigue-cracked aluminum components reinforced with boron/epoxy patches. Fatigue and Fracture of Engineering Materials and Structures 1993, 16, 753-765.
16. Cherry, M. C., Investigation of residual strength and fatigue life of unstiffened aluminum panels with multiple site damage. Master's thesis, Department of Aeronautics and Astronautics, Air Force Institute of Technology, Wright-Patterson AFB, USA, 1995.
17. Rose, L.R.F., A cracked plate repaired by bonded reinforcements. Int. J. Fracture 1982, 18, 135-144.