Impact Damage and Residual Strength Analysis of Composite Panels with Bonded Stiffeners

Madan, Ram C.; Shuart, Mark J.

doi:10.1520/stp24108s

Cited by 3 publications

(3 citation statements)

References 2 publications

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“…E st /E sk , is applied through the centroid of the beam cross section, and thus can be obtained as (16) where L denotes the distance between two remote load elements of the stringer.…”

Section: Displacements Of Skin Stringer and Adhesive Or Rivetmentioning

confidence: 99%

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Impact Damage Tolerance Analysis of Stiffened Composite Panels

Chen¹,

Shen²,

Junyang³

2001

Journal of Composite Materials

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An approach based on a displacement compatibility model is presented for both riveted and bonded stiffened composite panels containing impact damage. This represents the first application of the displacement compatibility model to the failure analysis of impacted stiffened composite panels, and some newresults are obtained for the impact damage tolerance properties of stiffened composite panels. In the present analysis, the previous displacement compatibility model for a stringer/orthotropic skin panel is improved for a stringer/unbalanced skin panel. The impact damage is simplified as an elliptic hole based on the compressive failure mechanisms of impacted composite laminates and stiffened panels. Predictions for failure loads and damage arrest capability agree well with experimental results for several composite panel configurations. The important results obtained in this study are: (1) damage arrest capability is dominated by the strength of the skin/stringer attachment; (2) distinct two-stage failure shows that the riveted panels have significant damage arrest capability due to the high shear strength of the rivets; and (3) since the very low shear strength of the skin/stringer attachment, the co-cured panels have no damage arrest capability.

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“…E st /E sk , is applied through the centroid of the beam cross section, and thus can be obtained as (16) where L denotes the distance between two remote load elements of the stringer.…”

Section: Displacements Of Skin Stringer and Adhesive Or Rivetmentioning

confidence: 99%

“…Madan and Shuart [16] developed a method for compression after impact strength prediction of stiffened composite panels. First, the residual strengths of cracked skin laminate coupons were predicted using the point stress failure criterion [17].…”

Section: Introductionmentioning

confidence: 99%

Impact Damage Tolerance Analysis of Stiffened Composite Panels

Chen¹,

Shen²,

Junyang³

2001

Journal of Composite Materials

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“…Adhesive bonding is an accepted and often preferred method of joining composite laminates, avoiding section loss and notch stress concentrations. However to date relatively little research has been conducted on the impact of bonded composite laminates, [11][12][13]. The work presented in this paper has been carried out to provide a preliminary investigation of bonded composite joint impact performance as a pilot study for BAE Systems.…”

Section: Introductionmentioning

confidence: 99%

Impact of Adhesively Bonded Composite Joints with Edge Effect

Farrow

Potter

Fisher

et al. 2000

Advanced Composites Letters

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A pilot project has been carried out to investigate the effect of impact on single-lap bonded composite joints based on AS4-8552 laminates and Cybond BR4535A adhesive. Low velocity impacts at an energy level sufficient to cause barely visible impact damage, were conducted on single lap joint specimens at different joint positions. Impact caused delaminations in the upper and lower laminates and localised through-thickness cracking in the adhesive. Residual tensile joint strengths of the impacted joint specimens with near-edge damage were reduced to approximately 50% of the un-impacted value. Failure surface inspections revealed localised through-thickness adhesive shear cracking as a governor of the original impact delamination pattern in the laminates and laminate delamination as the cause of ultimate tensile failure.

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