An Experimental Study on the Tensile Behavior of the Cracked Aluminum Plates Repaired with FML Composite Patches
Repairing of the cracks by fiber metal laminates
(FMLs) was first done by some aeronautical laboratories in early
1970s. In this study, experimental investigations were done on the
effect of repairing the center-cracked aluminum plates using the FML
patches. The repairing processes were conducted to characterize the
response of the repaired structures to tensile tests. The composite
patches were made of one aluminum layer and two woven glassepoxy
composite layers. Three different crack lengths in three crack
angles and different patch lay-ups were examined. It was observed
for the lengthen cracks, the effect of increasing the crack angle on
ultimate tensile load in the structure was increase. It was indicated
that the situation of metal layer in the FML patches had an important
effect on the tensile response of the tested specimens. It was found
when the aluminum layer is farther, the ultimate tensile load has the
highest amount.
[1] R.Y. Qin, H.P. Schreiber, Adhesion at partially restructured polymer
surfaces, Colloids Surf. A: Physicochem. Eng. Aspects 156 (1999) 85-93.
[2] Vlot A. Historical overview. In: Fibre metal laminates; an
introduction.Dordrecht: Kluwer Academic Publishers; 2001.
[3] GuocaiWu, Yang. Jenn-Ming, Journal of Metals 57 (1) (2005) 72-79.
[4] M. Hagenbeek, C. Van Hengel, O.J. Bosker, C.A.J.R. Vermeeren,
Applied Composite Materials 10 (2003) 207-222.
[5] J.J. Homan, International Journal of Fatigue 28 (4) (2006) 366-374.
[6] Po-Yu Chang, Jenn-Ming Yang, et al., Fatigue and Fracture of
Engineering Materials and Structures 30 (2007) 158-1171.
[7] Po-Yu Chang, Po-Ching Yeh, Jenn-Ming Yang, (2008) Static behavior
of notched and un-notched fiber metal laminates with hybrid boron/glass
fibers, Submitted to Modeling and Simulation in Materials Science and
Engineering
[8] Clearfield HM, McNamara DK, Davis GD. In: Brinson HF, Brinson HF,
editors. Engineered materials handbook, Vol. 3. Adhesives and sealants.
ASM International; 1990. p. 260.
[9] A. Chukwujekwu Okafor, Navdeep Singh, U.E. Enemuoh, S.V. Rao,
Design, analysis and performance of adhesively bonded composite
patch repair of cracked aluminum aircraft panels Composite Structures
71 (2005) 258-270
[10] ASTM D 2651, -American Society for Testing and Materials (ASTM),
West Consnohocken, USA, 1995 Standard Guide for Preparation of
Metal Surfaces for Adhesive Bonding.
[11] Huntsman Advanced materials data sheet for Araldite LY5052-1
/Aradure 5052-1, www.huntsman.com/advanced_ materials, 2007.
[12] Advanced materials data sheet for Araldite 2015,
www.huntsman.com/advanced_ materials.
[13] Wegman RF. Surface preparation techniques for adhesive bonding.
William Andrew Inc. NOYES PUBLICATION; 1989.
[14] www.instron.com
[1] R.Y. Qin, H.P. Schreiber, Adhesion at partially restructured polymer
surfaces, Colloids Surf. A: Physicochem. Eng. Aspects 156 (1999) 85-93.
[2] Vlot A. Historical overview. In: Fibre metal laminates; an
introduction.Dordrecht: Kluwer Academic Publishers; 2001.
[3] GuocaiWu, Yang. Jenn-Ming, Journal of Metals 57 (1) (2005) 72-79.
[4] M. Hagenbeek, C. Van Hengel, O.J. Bosker, C.A.J.R. Vermeeren,
Applied Composite Materials 10 (2003) 207-222.
[5] J.J. Homan, International Journal of Fatigue 28 (4) (2006) 366-374.
[6] Po-Yu Chang, Jenn-Ming Yang, et al., Fatigue and Fracture of
Engineering Materials and Structures 30 (2007) 158-1171.
[7] Po-Yu Chang, Po-Ching Yeh, Jenn-Ming Yang, (2008) Static behavior
of notched and un-notched fiber metal laminates with hybrid boron/glass
fibers, Submitted to Modeling and Simulation in Materials Science and
Engineering
[8] Clearfield HM, McNamara DK, Davis GD. In: Brinson HF, Brinson HF,
editors. Engineered materials handbook, Vol. 3. Adhesives and sealants.
ASM International; 1990. p. 260.
[9] A. Chukwujekwu Okafor, Navdeep Singh, U.E. Enemuoh, S.V. Rao,
Design, analysis and performance of adhesively bonded composite
patch repair of cracked aluminum aircraft panels Composite Structures
71 (2005) 258-270
[10] ASTM D 2651, -American Society for Testing and Materials (ASTM),
West Consnohocken, USA, 1995 Standard Guide for Preparation of
Metal Surfaces for Adhesive Bonding.
[11] Huntsman Advanced materials data sheet for Araldite LY5052-1
/Aradure 5052-1, www.huntsman.com/advanced_ materials, 2007.
[12] Advanced materials data sheet for Araldite 2015,
www.huntsman.com/advanced_ materials.
[13] Wegman RF. Surface preparation techniques for adhesive bonding.
William Andrew Inc. NOYES PUBLICATION; 1989.
[14] www.instron.com
@article{"International Journal of Mechanical, Industrial and Aerospace Sciences:55888", author = "A. Pourkamali Anaraki and G. H. Payganeh and F. Ashena ghasemi and A. Fallah", title = "An Experimental Study on the Tensile Behavior of the Cracked Aluminum Plates Repaired with FML Composite Patches", abstract = "Repairing of the cracks by fiber metal laminates
(FMLs) was first done by some aeronautical laboratories in early
1970s. In this study, experimental investigations were done on the
effect of repairing the center-cracked aluminum plates using the FML
patches. The repairing processes were conducted to characterize the
response of the repaired structures to tensile tests. The composite
patches were made of one aluminum layer and two woven glassepoxy
composite layers. Three different crack lengths in three crack
angles and different patch lay-ups were examined. It was observed
for the lengthen cracks, the effect of increasing the crack angle on
ultimate tensile load in the structure was increase. It was indicated
that the situation of metal layer in the FML patches had an important
effect on the tensile response of the tested specimens. It was found
when the aluminum layer is farther, the ultimate tensile load has the
highest amount.", keywords = "Crack, Composite patch repair, Fiber metal laminate (FML), Patch Lay-up, Repair surface, Ultimate load", volume = "6", number = "1", pages = "139-5", }