Abstract: A joint construction for an aeronautical structure made from composite material having an internal structural element and an adjoining skin element which define the aeronautical structure, which includes a coupling element disposed between and contiguous with the internal structural element and the adjoining skin element, wherein the coupling element has opposing adjoining diagonally configured end portions which form a wedge shaped diagonal joint therebetween which terminates at the internal structural element at one end and the skin element at the other end, and a plurality of rivets extending from the internal structured element to the adjoining skin, across the coupling element and across the diagonal joint.

Abstract: Pressure compensation device (100) deployed in an element that contains a flammable substance that compensates pressures between interior (101) of the element and exterior atmosphere (102) in which said element is deployed, by means of a continuous primary circulation (300) of air through primary channel (103) in said device (110) that communicates interior (100) and exterior (102) of the element, further comprising a secondary channel (104) integrated in the device (100) itself, communicating interior (102) and exterior (102) of the element, comprising said secondary channel (104) in the interior zone of the element a sheet (105) such that, in the event primary continuous circulation (300) of air through primary channel (103) is interrupted, said continuous circulation continues through secondary circulation (400) of air to interior (101) of the element, this secondary circulation (400) of air being capable of breaking sheet (105) of secondary channel (104).

Abstract: Aircraft component with panels (11) stiffened with stringers (15) configured with a central section (17) and some feet (19) in which there are zones of potential intersections or interferences of said stringers (15) with spars (25) and ribs (27), in which the configuration of the ends of the stringers (15) affected by said intersections or interferences includes a first section (41) in which the height of the central section (17) of the stringer (15) is reduced until it disappears and the width of the feet (19) is increased until it reaches a predetermined width A and a second section (43) with some extended feet (23) of said predetermined width A and no central section (17), including in said first section (41) the mechanical means (31) for binding the end of the stringer (15) to the skin (13). The invention also relates to a method for manufacturing said panels (11).

Abstract: Aircraft component with panels (11) stiffened with stringers (15) configured with a central section (17) and some feet (19) in which there are zones of potential intersections or interferences of said stringers (15) with spars (25) and ribs (27), in which the configuration of the ends of the stringers (15) affected by said intersections or interferences includes a first section (41) in which the height of the central section (17) of the stringer (15) is reduced until it disappears and the width of the feet (19) is increased until it reaches a predetermined width A and a second section (43) with some extended feet (23) of said predetermined width A and no central section (17), including in said first section (41) the mechanical means (31) for binding the end of the stringer (15) to the skin (13). The invention also relates to a method for manufacturing said panels (11).

Abstract: Arrangement of a circumferential joint of structural elements with a coupling element manufactured in composite material in a aeronautic structure, which comprises: two sections (13, 15) of skin (11) manufactured in a composite material with an external surface (17) and an internal surface (19); an internal structural element (41); a plurality of rivet rows (12) and a coupling element (21) to facilitate the joint of adjoining skin (11) sections (13, 15), with an external surface (23) and an internal surface (25), manufactured in composite material in a plurality of separate parts (27, 29), with the ends of each pair of adjoining parts (27, 29) being formed in a wedge shape, with one of them pointing to the skin (11) and the other to the internal structural element (41) and with their inclined faces overlapping (31,33).