General Method for Optimizing Composite Patch Repairs

Abstract:

The aim of this work is to define a general method for the optimization of composite patch repairing. Fracture mechanics theory shows that the stress intensity factor tends towards an asymptotic limit K_∞. This limit is given by Rose’s formula and is a function of the thicknesses and mechanical properties of the cracked plate, the composite patch and the adhesive. The proposed approach consists in considering this limit as an objective function that needs to be minimized. In deed lowering this asymptote will reduce the values of the stress intensity factor hence optimize the repair. However to be effective this robust design must satisfy the stiffness ratio criteria. The resolution of this double objective optimization problem with Matlab program allowed us determine the appropriate geometric and mechanical properties that allow the optimum design; that is the selection of the adhesive, the patch and their respective thicknesses.

• Periodical: Advanced Materials Research (Volumes 1120-1121)
• Pages: 670-674
• DOI: https://doi.org/10.4028/www.scientific.net/AMR.1120-1121.670
• Online since: July 2015
• Authors: Abdelmadjid Ait Yala*, Abderrahmanne Akkouche
• Keywords: General Method, Objective Function, Optimization, Patch Repair, Stress Intensity Factor

References

[1] A.A. Baker, 'Repair of cracked or Defective Metallic Aircraft Components with Advanced Fibre. Elsevier Applied Sciences Publishers Ltd. Pp 153-181, (1984).

DOI: 10.1016/0263-8223(84)90025-4

[2] Baker, A. A., and Jones, R., Bonded Repair of Ainraft Structure, Martinus-Nijhoff Publishers, Dordrecht, 1988, p.57.

[3] Jones, R., and Callinan, R. J., Analysis of Composite Laminates and Fibre Composite Repair Schemes", Fiber Science and Technology, Vol. 15, 1981, pp.199-207.

DOI: 10.1016/0015-0568(81)90004-x

[4] Sun, C.T., Klug, J., and Arendt, C., "Analysis of cracked aluminium plates repaired by bonded composite patchesn, AIAA Journal, Vol. 34, 1996, pp.369-374.

DOI: 10.2514/3.13073

[5] Chue, C. H., Chang,L. C., and Tsai, J. S., 'Bonded Repair of a Plate with Central Inclined Crack Under Biaxial Loading, Composite Structures, Vol. 28, 1994, pp.39-45.

DOI: 10.1016/0263-8223(94)90004-3

[6] Chue, C.H., Lin, L. A., and Wang, S. C., Optimum Selection of Ply Orientation in Bonded Repair under Biaxial Loadingn , Engineering Fracture Mechanics, Vol. 48, 1994, pp.91-101.

DOI: 10.1016/0013-7944(94)90146-5

[7] R. Brighenti Roberto , A. Carpinteri ,S. Vantadori , A genetic algorithm applied to optimisation of patch repairs for cracked plates . Computer methods in applied mechanics and engineering . Vol. 196, no1-3, pp.466-475, (2006).

DOI: 10.1016/j.cma.2006.07.004

[8] George J, Tsamasphiros Applied Composite Materials Volume 10, Number 3. Mai (2003).

[9] A. Ait Yala, A. Megueni , Optimisation of Composite Patches Repairs With the Design of Experiments Method, Materials and Design 30 (2009) 200-205.

DOI: 10.1016/j.matdes.2008.04.049

[10] Ting T., Jones R. , Chiu W.K., Marshall J.H. , Green J.M., Composite Repairs to Rib Stiffened Panels . Composite Structures 1999; 47: 737-743.

DOI: 10.1016/s0263-8223(00)00046-5

[11] Callinan R.J., Sanderson S., keely D., Finite elements analysis of an F-111 lower wing skin fatigue crash repair, DSTO, Melbourne. DSTO-TN -0067; (1997).

[12] Jones R., Chiu W.K., Composite repairs to cracks in metallic components. Composite Strucrures 1999; 44, pp.17-29.

DOI: 10.1016/s0263-8223(98)00108-1

[13] Rose L.R.F. An application of the inclusion analogy for bonded reinforcements. Int. Journal Solid Structure . (1981).

[14] Baker, A.A. Crack Patching; Experimental Studies, Practical Applications, in Bonded Repair of Aircraft Structures. 107-172. A.A. Baker and R. Jones, editors. Dordrecht: Martinus Nijhoff Publishers, (1988).

DOI: 10.1007/978-94-009-2752-0_6