Abstract: Integrated aircraft structure in composite material that comprises a skin and stringers (1), with the skin comprising a skin part (5) and a basic skin (3), and said structure further comprises U-shaped elements (15) each of which comprises in its turn two L-shaped sections (4a+5a and 4b+5b) together with the skin part (5), in such a way that these U-shaped elements (15) fulfil two structural functions in said structure at the same time, acting as frame feet and as skin, providing an integrated fuselage structure without rivets or joints. The invention also relates to a manufacturing process of an integrated aircraft structure in composite material.

Abstract: Based on a body (1) wherein a clamp (2) is defined, with its corresponding screws (3) and nut (4), for the tightening thereof on the battery post, said body (1) incorporates at its end opposite to the clamp (2) a pair of cylindrical necks (6-9), with parallel axes, with opposite extensions (7) and (10), said necks having different diameters, such that they determine for the terminal two individual connection areas allowing for the coupling of a broad range of cables with different sections, both unitarily and in a group, in each one of said connection areas.

Abstract: A holding and connecting device (1) for an electrical circuit (2), particularly in the form of a printed board assembly, with at least one terminal box (4) for producing an electrical connection to the electrical circuit. The holding and connecting device (1) has at least one insertion opening (5) with a circumferential opening edge (6) that has a sealed contact with an assigned, essentially circumferential edge flange (7) of the terminal box (4).