Fatigue testing and buckling characteristics of impacted composite specimens

Melin, Lars; Schön, Joakim; Nyman, Tonny

doi:10.1016/s0142-1123(01)00081-0

Cited by 39 publications

(23 citation statements)

References 10 publications

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“…Experimentally, Fig. 4 from Butler et al (2007) directly supports initiation of growth in the loading (longitudinal) direction and images from Melin and Schön (2001) and Melin et al (2002) display growth in the same direction although it is not apparent in which direction, longitudinal or transverse, propagation first occurred. Analytically, Chai and Babcock (1985) show that it is possible for growth to initiate in the longitudinal direction for isotropic and orthotropic sublaminates, depending on the geometry and depth of the critical delamination.…”

Section: Analytical Modelmentioning

confidence: 76%

“…The plate model was tested for validation purposes on a range of laminates with varying materials and lay-ups taken from the literature by Curtis et al (1993), Melin and Schön (2001), Melin et al (2002) and Chen et al (2001). These papers used differing test data and a brief summary of each is given below.…”

Section: Experimental Examplesmentioning

confidence: 99%

“…HTA/6376 coupons (Melin and Schön, 2001;Melin et al, 2002) BVID was introduced into coupons of 6.24 mm thick HTA/6376 material with a so-called zero dominated (ZD) lay-up [45, À45, 0, 90, 45, À45, 0 2 , (45, À45, 0, 90) 2 , 45, À45, 0 2 , 45, À45, 0, 90] S and a quasi isotropic (QI) lay-up [(90, À45, 45, 0) S , (0, 45, À45, 90) S ] 3 using an impact energy of 27 J. Note because of the asymmetry of the HTA/6376 QI laminate it is necessary to establish impact and back faces in order to give the correct lay-up for the sublaminate involved in propagation.…”

Section: Experimental Examplesmentioning

confidence: 99%

“…Melin and Schön (2001) report this critical level to be at a depth of around 10-20% of the total thickness. The plate model is applied to the example problems reported in the experimental studies of Curtis et al (1993), Melin and Schön (2001), Melin et al (2002) and Chen et al (2001). The model is also used to show whether the initial propagation is stable or unstable, and to evaluate sensitivity to parametric variation.…”

Section: Introductionmentioning

confidence: 99%

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Post-buckled propagation model for compressive fatigue of impact damaged laminates

Rhead

Butler

Hunt

2008

International Journal of Solids and Structures

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a b s t r a c tAn analytical model for prediction of compressive fatigue threshold strains in composite plates with barely visible impact damage (BVID) is presented. The model represents the complex damage morphology as a single circular delamination at a critical level and calculates the strain at which thin-film buckling of the circular delaminated region occurs. The threshold strain is defined as the strain at which the strain energy release rate for the fracture of post-buckled delaminated plies along the delamination is equal to the critical Mode I value (G 1C ) for the resin. The model predicts the critical through-thickness level for delamination, the stability of delamination growth and also the sensitivity to experimental error in geometric measurements of the damage area. Results obtained using the model show an agreement of fatigue strain to within 4% of experimental values for four sets of data reported in the literature.

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Section: Analytical Modelmentioning

confidence: 76%

Section: Experimental Examplesmentioning

confidence: 99%

Section: Experimental Examplesmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Post-buckled propagation model for compressive fatigue of impact damaged laminates

Rhead

Butler

Hunt

2008

International Journal of Solids and Structures

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“…The CAI fatigue data of CFRP materials were published in related reports. [1][2][3][4][5][6][7][8][9][10][11][12][13][14][15][16][17][18] A recent report published from the federal aviation administration (FAA) of the US Department of Transportation is especially useful to ascertain fatigue behavior (including CAI fatigue) of modern carbon fiber composites. [18] In that article, many CAI fatigue data were reported.…”

Section: Introductionmentioning

confidence: 99%

Fatigue behavior and lifetime distribution of impact-damaged carbon fiber/toughened epoxy composites under compressive loading

Ogasawara

Sugimoto

Katoh

et al. 2013

Advanced Composite Materials

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This paper presents fatigue lifetime data of impact-damaged carbon fiber/toughened epoxy composites under compressive loading to elucidate the lifetime prediction methodology based on statistical approaches. Drop-weight impact damage was induced to a composite specimen with impact energy of 6.7 J/mm in accordance with ASTM D7136. Postimpact fatigue tests were conducted using a test fixture defined in ASTM D7137 under compression-compression loading (R = 10) at room temperature. The maximum compressive stress (S min ) was 200, 210, 220, 230, and 240 MPa, and the total number of specimens was 31. The compression-after-impact strength and fatigue lifetime show considerable scattering. This result is apparently derived from the variation in impact damage size. A simple statistical model based on the weakest link theory was proposed for predicting the lifetime of impact-damaged composite laminates. Results show that the experimentally obtained data were confirmed consistently using this model. The ratio between the endurance limit at 10 6 and 10 7 cycles and the initial static strength was estimated as 0.74 and 0.68 as B-basis allowable values.

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Residual capacities of uniaxially compressed, delaminated composite panels

Völlmecke

2010

Proc Appl Math and Mech

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The mechanical buckling and postbuckling behaviour of a delaminated panel under uniaxial compression is investigated using a semi-analytical geometrically nonlinear panel model. A Rayleigh-Ritz procedure based on trigonometric displacement functions is used in conjunction with minimum energy principles to ascertain the mechanical response of the panels. The model includes the effect of delamination propagation resulting from the buckling of the laminates utilizing a discrete cohesive zone model. With the model developed, a detailed assessment of the residual capacity of the panel is provided due to its capability of tracing the equilibrium paths far into the postbuckling range.

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Fatigue testing and buckling characteristics of impacted composite specimens

Cited by 39 publications

References 10 publications

Post-buckled propagation model for compressive fatigue of impact damaged laminates

Post-buckled propagation model for compressive fatigue of impact damaged laminates

Fatigue behavior and lifetime distribution of impact-damaged carbon fiber/toughened epoxy composites under compressive loading

Residual capacities of uniaxially compressed, delaminated composite panels

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