Evaluation of fatigue crack growth behavior of GLARE3 fiber/metal laminates using a compliance method

Takamatsu, Tohru; Shimokawa, Tomotsugu; Matsumura, Takashi; Miyoshi, Yoshio; Tanabe, Yasuhiro

doi:10.1016/s0013-7944(03)00063-8

Cited by 31 publications

(14 citation statements)

References 6 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…The results for H-R01 are, however, unexpected insofar they suggest that as the crack grows and the crack growth rate increases, DK eff at the crack tip decreases. While a similar result has been reported for a GLARE specimen of approximately the same thickness at a high stress level [35], this behaviour is counter-intuitive and is probably due to asymmetry of the delaminations.…”

Section: Compliance Methodssupporting

confidence: 77%

Characterisation of fatigue crack growth and related damage mechanisms in FRP–metal hybrid laminates

Austin

Singh

Gregson

et al. 2008

Composites Science and Technology

View full text Add to dashboard Cite

Section: Compliance Methodssupporting

confidence: 77%

Characterisation of fatigue crack growth and related damage mechanisms in FRP–metal hybrid laminates

Austin

Singh

Gregson

et al. 2008

Composites Science and Technology

View full text Add to dashboard Cite

“…FMLs show fatigue crack growth life 17 times longer than monolithic Al plates even at higher loads. 28 FCGRs of FMLs can be predicted by using analytical methods, 29,30 phenomenological methods 31,32 , finite element techniques 22,[33][34][35][36][37] and boundary element methods. Analytical models 28 used to describe the crack growth behaviour of FMLs are preferred by aircraft designers, but accurate development and validation of these analytical models require both experimental validation and finite element method verification.…”

Section: Introductionmentioning

confidence: 99%

Investigation of fatigue crack growth rate in CARALL, ARALL and GLARE

Asghar

Nasir

Qayyum

et al. 2017

Fatigue Fract Eng Mat Struct

View full text Add to dashboard Cite

Fibre metal laminates (FMLs) are being used to manufacture many structural components in aerospace industry because of their very high strength to weight ratios, yet the exact model for estimating fatigue crack propagation in FMLs cannot be developed because of many variable parameters affecting it. In this research, tensile strength, fatigue life and fracture toughness values of 2/1 configuration carbon reinforced aluminium laminate (CARALL), aramid reinforced aluminium laminate and glass laminate aluminium reinforced epoxy specimens have been investigated. Mechanical, chemical and electrochemical surface treatments were applied to AA 1050 face sheets to improve the adhesive properties of the laminates. The specimens were prepared using vacuum assisted resin transfer moulding technique and were cut to desired shapes. Fatigue tests were conducted on centre notched specimens according to ASTM Standard E399. Real time material data and properties of adhesive were used in definition of numerical simulation model to obtain the values of stress intensity factor at different crack lengths. It was observed that CARALL shows very superior tensile and fatigue strength because of stress distribution during failure. Numerical simulation model developed in this research accurately predicts fracture toughness of aramid reinforced aluminium laminate, CARALL and glass laminate aluminium reinforced epoxy with less than 2% error. An empirical analytical model using experimental data obtained during research was developed which accurately predicts the trend of FMLs fatigue life.

show abstract

“…From an engineering perspective (or from an experimental practice), the bridging effect of the fibre layer has been taken as fact, on which further analysis and model development has been based (Marissen 1988;Takamatsu et al 1999Takamatsu et al , 2003Wu 1998, 1999;Alderliesten 2007a). The fibre layers are insensitive to the occurring fatigue stresses and bridge the crack.…”

Section: Theoretical Backgroundmentioning

confidence: 99%

“…The majority of papers being published on these topics report fatigue and fracture experiments on various coupon specimens, analysis of observation and development of understanding by means of empirical or theoretical models (Marissen 1988;Takamatsu et al 1999Takamatsu et al , 2003Wu 1998, 1999;Alderliesten 2007a). Other papers originate from the theoretical fracture mechanics background and attempt to develop theoretical models describing the phenomena based on mathematical derivations rather than experimental observations (He and Hutchinson 1989;Dollar and Steif 1991;Lu 1996;Chan et al 1993;Fleck 2004, 2006).…”

Section: Introductionmentioning

confidence: 99%

On crack tunneling and plane-strain delamination in laminates

Alderliesten

2007

Int J Fract

View full text Add to dashboard Cite

Previous numerical work on crack tunnelling and plane-strain delamination in layered solids is evaluated with static and fatigue experiments and analysis. It is concluded that the translation of the theory derived for static fracture to fatigue loading is not as straightforward as initially assumed. Details such as delamination location, stress state, plasticity and modemixity need further consideration to obtain a theory that is sufficiently adequate to describe the static and fatigue phenomena observed in practice. Keywords

show abstract

Evaluation of fatigue crack growth behavior of GLARE3 fiber/metal laminates using a compliance method

Cited by 31 publications

References 6 publications

Characterisation of fatigue crack growth and related damage mechanisms in FRP–metal hybrid laminates

Characterisation of fatigue crack growth and related damage mechanisms in FRP–metal hybrid laminates

Investigation of fatigue crack growth rate in CARALL, ARALL and GLARE

On crack tunneling and plane-strain delamination in laminates

Contact Info

Product

Resources

About