Abstract: A device for joining, in particular, composite structure elements with metallic structure elements of an aircraft. The device includes a junction element, provided with a first longitudinal partition wall fastened to a metallic panel, integral with a stiffener comprising a vertical core and at least one baseplate, with a second longitudinal partition wall, fastened to a composite panel, and with a lower branch to which are connected the proximal extremities of the said first and second longitudinal partition walls. The device further includes a first fitting element, provided with a first pick-up fitting body on the said stiffener and with a first heel and a second fitting element, provided with a second pick-up fitting body on the composite panel, and with a second heel, the heels of the fitting elements being fastened to the lower branch, on both sides of the lower branch, opposite each other.

Abstract: A device for joining, in particular, composite structure elements with metallic structure elements of an aircraft, comprising a junction element, provided with a first longitudinal partition wall fastened to a metallic panel, integral with a stiffener comprising a vertical core and at least one baseplate, with a second longitudinal partition wall, fastened to a composite panel, and with a lower branch to which are connected the proximal extremities of the said first and second longitudinal partition walls, the device comprising, moreover, a first fitting element, provided with a first pick-up fitting body on the said stiffener and with a first heel and a second fitting element, provided with a second pick-up fitting body on the composite panel, and with a second heel, the heels of the fitting elements being fastened to the lower branch, on both sides of the lower branch, opposite each other.