Issue 48

M. Bezzerrouki et alii, Frattura ed Integrità Strutturale, 48 (2019) 491-502; DOI: 10.3221/IGF-ESIS.48.47 501 (a) (b) (c) Figure 12 : Comparison of the ratio Linactive / L0 according to the stresses applied of the 3 models for the stresses of: (a) - Von- Mises, (b) - Shearing and (c) - Peeling.  At the depth of the adhesive layer, different stresses analyzed have low augmentation with the increase of stresses studied. Noting also that a same behaviors for models 2 and 3 for the three types of stresses.  For the comparison of inactive length, the increase in the applied stresses surely generates a decrease of the ratio L inactive / L 0 but the difference remains weak comparing the three models which confirms the effectiveness of models 2 and 3.  The modification made to the plate considerably reduces the stresses at the edge of the adhesive and therefore makes the depth of the adhesive work, which balances the stresses along overlap length. R EFERENCES [1] Baker, A., Rose, F., Jones, R. (2002). Advances in the bonded composite repair of metallic aircraft structures. 1-2. Elsevier. [2] ASTM Standards (1999). Standard Test Method for Apparent Shear Strength of Single-Lap-Joint Adhesively Bonded Metal Specimens by Tension Loading (metal-to-metal). https://www.admet.com/how-to-perform-an-adhesive-lap-joint-shear-strength-test-astm-d1002/ [3] Goland, M. and Reissner, E. (1944). J. Appl. Mech., (11), pp. A17–A24. [4] Hart-Smith, L. J. (1973). Technical Report NASA CR 112236, Douglas Aircraft Company