beam 16 by two elastic links 1 of course a larger number of elastic joints 1 can be used the airfoil stresses are absorbed at the fuselage 8 by the tilt of three transfer zones with two being located on the flanks of the fuselage 8 and the last one being located at the central ventral beam 16 in another example of embodiment the compartment 13 is not closed off by a central beam 16 in the same way when the airfoil 9 is located in the upper part of the central section of the fuselage 8 it is not necessary to close off the compartment 13 with a central beam 16 the use of elastic links 1 in the fastening devices pursuant to the disclosed embodiments permits making an airfoil 9 in one piece then to be fastened only once to the fuselage 8 of course it is also possible to proceed in three steps in other words to integrate the central airfoil casing 12 with the fuselage 8 before then fastening each of the two wings 10 11 in other respects the flexibility of the elastic links 1 because of the presence of the layer of elastomer 5 6 allows assembly tolerances that permit compensating for any slight misfit between the wall 15 of the fuselage 8 and the airfoil 9 the elastic links 1 of the fastening device pursuant to the disclosed embodiments allow for a hyperstatic isostatic system in the context of the airfoil junction these elastic links 1 assure the compatibility of deformations between.