Abstract: A tank including interior and exterior skins separated by an intercalated zone and at least one inspection device. The inspection device includes a first orifice configured to establish communication between the interior zone of the tank and the intercalated zone via the interior skin, configured to be blocked by a first plug, a second orifice configured to establish communication between the intercalated zone and the exterior zone of the tank via the exterior skin, configured to be blocked by a second plug, the first and second orifices being aligned in a radial direction, an intercalated pipe connecting the interior and exterior skins, communicating with the first and second orifices and including a bellows configured to be deformed in the radial direction.

Abstract: A tank including an enclosure including a tubular body and first and second end walls at the ends of the tubular body, a plurality of equipment units positioned in the enclosure, at least one equipment support to which the equipment units are connected positioned in the enclosure and connected to the enclosure and a method of manufacturing this tank. The equipment units are fixed to the equipment support outside the enclosure, which simplifies putting them into place and limits the risks of damage. Moreover, they are all introduced into the enclosure at the same time, which makes it possible to reduce the time to manufacture the tank.

Abstract: A tank including at least first and second portions connected by a connection ring and weld seams obtained by means of a friction welding method. The connection ring includes at least a first cylindrical portion fitted in the end of the first portion, at least a first shoulder protruding toward the outer zone of the tank relative to the first cylindrical portion and at least a first transverse web positioned approximately in the same transverse plane as the first shoulder. According to this configuration, the first cylindrical portion and the transverse web ensure that the forces generated by a friction welding head during the production of the weld seam which enables the tank to be closed are absorbed.

Abstract: A storage tank for a cryogenic fluid including an inner tank that is configured to store the fluid and that is seated in an outer envelope, the inner tank and the outer envelope having a shared longitudinal axis, such that a thermal insulation volume surrounds the inner tank, and wherein the outer envelope surrounds the volume about the inner tank. The tank has at least one damping element made of a deformable material positioned between one end of the inner tank and the outer envelope to wedge the inner tank against the outer envelope. This enables a reliable sliding mechanical link to be formed between at least one end of the inner tank and the outer envelope of the tank, thereby increasing resistance to wear and facilitating assembly of the tank.

Abstract: A method for manufacturing structural rods to make it easier to manufacture a structural rod for an aircraft and to improve performance. Each rod includes a rod body and two end portions disposed at either end of the rod body along a longitudinal central rod axis, each end portion comprising at least one mounting lug that protrudes from the rod body along the longitudinal axis. The method includes producing a sandwich panel including two skins gripping a cellular inner body, at least one of the two outer skins having a skin extension for forming a part of the at least one mounting lug of at least one of the two end portions of the rod, and cutting the panel along parallel cutting lines to obtain the structural rods.

Abstract: A propulsion unit, and an aircraft, with a propeller and electric motor, including at least one intermediate element interposed between the electric motor and the propeller and configured to transmit at least thrust loads generated by the propeller, a primary structure supporting the propulsion unit, at least one interface having: a first load path, configured to transmit loads perpendicular to the axis of rotation of the propeller, linking the at least one intermediate element to a support linked rigidly to or incorporated in the primary structure, a second load path, configured to transmit loads that are parallel to the axis of rotation of the propeller, linking the at least one intermediate element to a support linked rigidly to or incorporated in the primary structure.

Abstract: A method for manufacturing a centre wing box which includes inner stiffeners, at least one of which has at least one through-hole is described. For each stiffener having at least one through-hole and having a first leg of a first U-shaped and C-shaped profile and a second leg of a second U-shaped and C-shaped profile, the method includes, for each through-hole, the steps of producing a first section of the through-hole in the first U-shaped or C-shaped profile and of producing a second section of the through-hole in the second U-shaped or C-shaped profile before the first and second U-shaped or C-shaped profiles are positioned on the mould.

Abstract: A method for manufacturing structural rods to make it easier to manufacture a structural rod for an aircraft and to improve performance. Each rod includes a rod body and two end portions disposed at either end of the rod body along a longitudinal central rod axis, each end portion comprising at least one mounting lug that protrudes from the rod body along the longitudinal axis. The method includes producing a sandwich panel including two skins gripping a cellular inner body, at least one of the two outer skins having a skin extension for forming a part of the at least one mounting lug of at least one of the two end portions of the rod, and cutting the panel along parallel cutting lines to obtain the structural rods.

Abstract: A method for manufacturing a centre wing box which includes inner stiffeners, at least one of which has at least one through-hole is described. For each stiffener having at least one through-hole and having a first leg of a first U-shaped and C-shaped profile and a second leg of a second U-shaped and C-shaped profile, the method includes, for each through-hole, the steps of producing a first section of the through-hole in the first U-shaped or C-shaped profile and of producing a second section of the through-hole in the second U-shaped or C-shaped profile before the first and second U-shaped or C-shaped profiles are positioned on the mould.