Damage indicators evolution during cyclic loading of composite plate with hole

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Abstract

Novel experimental method, which provides quantitative description of damage indicators evolution caused by fatigue loading of composite specimens with stress concentrators, was developed. Damage parameters are derived as deformation response to artificial notch inserting. This notch is extended from the edge of central through hole in plane rectangular specimen under constant external load. Current values of damage indicators are obtained at different stages of fatigue loading. These data reveal dependencies of required parameters on loading cycle number. The damage accumulation function for involved cycle range is quantitatively constructed on this base. It is found that this function is related to the first stage of the process investigated. The results obtained represent the essential link in the design of further experiments.

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About the authors

A. S. Dzuba

Zhukovsky Central Aerohydrodynamic Institute

Author for correspondence.
Email: dzuba@tsagi.ru
Russian Federation, Zhukovsky, Moskovskaya obl.

S. I. Eleonsky

Zhukovsky Central Aerohydrodynamic Institute

Email: juzzepka@mail.ru
Russian Federation, Zhukovsky, Moskovskaya obl.

M. D. Zajtsev

Zhukovsky Central Aerohydrodynamic Institute

Email: zaytcev@list.ru
Congo, Zhukovsky, Moskovskaya obl.

V. S. Pisarev

Zhukovsky Central Aerohydrodynamic Institute

Email: VSP5335@mail.ru
Russian Federation, Zhukovsky, Moskovskaya obl.

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Supplementary files

Supplementary Files
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2. Fig. 1. Scheme of the studied samples: a) drawing; b) artificial notch, loading scheme and damage indicators.

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3. Fig. 2. Sample CDC_4. Interference fringe patterns obtained in terms of the in-plane component of the displacements u (a) and v (b). Initial notch length = 0 with increments of = 3.01 mm (left notch) and = 2.52 mm (right notch). Average notch length = 2.76 mm.

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4. Fig. 3. Sample CDC_1. Interference fringe patterns obtained in terms of the in-plane component of the displacements u (a) and v (b). Initial notch length = 0 with increments of = 2.52 mm (left notch) and = 2.94 mm (right notch). Average notch length = 2.74 mm.

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5. Fig. 4. Dependences of damage indicators µ [μm] on the number of loading cycles.

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6. Fig. 5. Numerical integration of the normalized evolution of the damage parameter.

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7. Fig. 6. Normalized dependences of damage parameters on the number of loading cycles Nnorm.

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8. Fig. 7. Dependence of the damage accumulation function Dm on the number of loading cycles.

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9. Fig. 8. Traditional diagram illustrating damage accumulation in laminated composite materials.

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