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At the middle of the repair zone (x = 0, figure 33) the in-plane failure load (per unit width) in the repair plies is F/2 (P/2 = F/2). Since the model is symmetric, the in-plane strains at failure are [63] Laminate (ε ) (ε ) (ε ) Repair Patch (ε ) (ε ) (ε ) = α11L F L x F L y F = α 21L F L s F = α 61L F R x F R y F = α11R F / 2 R s F = α 61R F / 2 = α 21R F / 2 (1) where εx, εy, and εs are the off-axis in-plane strains (see figure 35). The αij’s are the components of the compliance matrix. The superscripts L and R refer to the laminate and the repair patches, respectively.

Both the resin layer and the adhesive 30 Repair patch P Laminate P (a) Uniform lap repair Repair patch P Laminate (b) Scarf repair without external ply P Repair patch External plies P Laminate P (c) Scarf repair with external plies FIGURE 29. MODELS OF THE UNIFORM LAP AND THE SCARF REPAIRS FIGURE 30. THE INTERLAYER BETWEEN THE LAMINATE AND THE REPAIR PATCH WHEN THE REPAIR IS PERFORMED WITH WET LAY-UP (LOWER LEFT) OR PREPREG (LOWER RIGHT) 31 are treated as an “interlayer” which exhibits elastic-perfectly plastic behavior (see figure 31).

Each specimen was cured at a preset cure temperature Tc (150°, 175°, or 200°F) until the instrument indicated that full cure was reached. FIGURE 27. A TYPICAL OUTPUT OF THE MICRODIELECTROMETER The time required to reach full cure is shown in figure 26. 5°F/min, the time required to reach full cure decreased with increasing cure temperature. The failure loads of specimens cured at different temperatures are shown in figure 28. The cure temperature did not seem to affect significantly the failure load for the dry specimens tested at 70°F.

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Repair of composite laminates by Sung-Hoon Ahn


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