Abstract: A cooling system for an aircraft, including a heat exchanger for cooling a hot fluid with cooling air, an air intake for the supply of cooling air and a Coand?-effect air amplifier for the creation of a flow of cooling air.

Abstract: Tooling for manufacturing multi-spar torsion boxes with different web heights, the tooling includes a mandrel module having a hollow beam geometry which comprises a first base and a second base opposite to the first base, and two walls extending between said first base and said second base, and at least one spacer module configured for coupling with the mandrel module, wherein the web height of a multi-spar torsion box is defined by the coupling between the mandrel module and at least one spacer module. A method for manufacturing multi-spar torsion boxes with different web heights.

Abstract: A fireproof and thermal insulator product (1) including an Alkaline Earth Silicate (AES) material (2), and at least one of the following: a liquid barrier film (5), an FRP (Fiber Reinforcement Plastic) layer (4), cork (3), wherein the liquid barrier film (5) and the FRP layer (4) are staked onto the AES material (2), and wherein the cork (3) material is also staked onto the AES material (2) or embedded into said AES material (2) in where said cork (3) is configured as a plurality of strips performing a grid structure infilled with the AES material (2).

Abstract: An air management system with a set of compressed air sources for selectively supplying pressurized air to air consumer equipment according to an aircraft operation condition. Low pressure air, high pressure air, or a combination thereof may perform such supplying of compressed air depending on the aircraft operation condition.

Abstract: A device for forming a composite laminate (10) for obtaining a Z-shaped profile (1) including: a grip module (5) comprising two plates (6) configured to enclose and grip between the two plates (6) a first portion of the composite laminate (10) that will form a first flange (3), and a feed module (7) comprising two plates (8) configured to enclose between the two plates (8) a second portion of the composite laminate (10), wherein the feed module (7) is configured to heat the portion of the composite laminate (10) located between its two plates (8) and to be movable with respect to the grip module (5) parallel to the plane of the web (2) of the composite profile (1) once formed to a second position in which the two plates (8) enclose the portion of the composite laminate (10) that will form a second flange (4).

Abstract: An aeronautical composite structure configured to monitor a physical status of a bonded portion between structural components using a multi-core optical fiber. A method and system for monitoring the physical status of a bonded portion in an aeronautical composite structure also uses a multi-core optical fiber. More particularly, the invention relates to a structure and method for monitoring the physical status of a bonded portion of an aeronautical composite structure from its manufacturing to its use in flight using a multi-core optical fiber.

Abstract: A fiber composite laying method for producing a fiber composite scrim for forming a fiber composite component. The method includes supplying a reinforcement fiber band to a laying head, laying and compacting the supplied reinforcement fiber band on a laying surface at an average compaction pressure by a compaction roller, and detecting a local compaction pressure on the laid reinforcement fiber band by pressure sensors on the compaction roller.

Abstract: An operating method of a vehicle cabin air supply device comprising taking fresh air from outside the cabin, diverting the fresh air to an air exhaust during an exhaust duration period after starting the air supply device, before injecting the fresh air into the cabin, such that the fresh air injected in the cabin after the exhaust duration period minimizes unpleasant odors in the cabin. A vehicle cabin air supply device and an aircraft comprising such a device is also provided.

Abstract: A landing gear door system, including a landing gear bay including an opening and accommodating a landing gear in a retracted position, a landing gear door for opening and closing the opening, an actuator for operating the landing gear door between an open and a closed position, a lock located in the landing gear bay and latching the landing gear door in the closed position, a stop fitting located in the landing gear bay and configured to be in connection with the landing gear door at least in its latched position. The landing gear door system further includes an additional actuator configured to apply a force to the landing gear door in its closed position and to elastically deform the landing gear door towards the landing gear door bay.

Abstract: A composite laminate (2) for an airframe lifting surface comprising a set of stacked plies (10) of pre-preg material, the composite laminate (2) being surrounded by at least an edge (3) following an edge direction E along the composite laminate (2), the set of stacked plies (10) including: a first plurality (4) of plies (4.1) formed by tapes arranged parallel to the edge direction E, and a second plurality (5) of plies (5.1, 5.2, 5.3) formed by tapes arranged in a direction different to the edge direction E, wherein the thickness of at least one ply of the second plurality (5) of plies is lower than the thickness of each ply of the first plurality (4) of plies.

Abstract: A sound wave absorbing laminate composite material structure for an aircraft including stacked plies of a hybrid composite material, wherein each of the hybrid composite material plies includes first polymer material tows parallel to a warp direction, second polymer material tows parallel to a weft direction, and sound absorbent material tows parallel to the warp direction, wherein the first and second polymer material tows carbon or glass fiber reinforcing polymer.

Abstract: A composite forming station for forming a T-profile composite part from a planar laminate. The composite forming station includes in-line rollers arranged along a forming direction, wherein a thickness and/or edge angle each roller is greater than the preceding roller, wherein the rollers gradually splay apart feet sections of the planar laminate to convert the laminate to the T-profile composite part.

Abstract: A composite structure, including a laminate that includes a set of plies, the laminate extending between a first edge and a second edge and including a rising ramp and a falling ramp. The rising ramp includes a starting point and an upper point and the falling ramp includes the upper point and an end point. Plies are partially located over their preceding ply and alternatively extend from the first edge or the second edge and are shorter than the ply located before the preceding ply so that their ends are stepped successively until they reach the top of the ramp.

Abstract: A multispar lifting surface including a multispar torsion box having corner reinforcements, a movable control surface, and an axial rod fitting. The movable control surface includes a movable element, a hinged connection joined to the movable element, and an axial rod joining the hinged connection to the rear spar of the multispar torsion box. The axial rod fitting is configured to join the axial rod and the multispar torsion box; and includes a longitudinal profile resting against the rear spar, and a lug joined to the longitudinal profile at one end and to the axial rod at another end; the lug defining a plane including the longitudinal axis of the axial rod. This multispar lifting surface is able to support sideward forces without any additional structure.

Abstract: A method to modify an aircraft including: disconnecting a first engine control device from command cables and transmission cables, wherein the first engine control device is in a fuselage section forward of a pressure bulkhead; replacing the engine control device with a jumper connector positioned in the fuselage section, wherein the jumper connector electrically connects the command cables to the transmission cables; installing a second engine control device in the fuselage aft of the pressure bulkhead, wherein the second engine control device is in an engine compartment of the fuselage; connecting the second engine control device to transmission cables at a location at or near the pressure bulkhead; connecting sensor cabling directly to the second engine control device, and connecting the engine control device directly to the engine.

Abstract: A trailing edge for a composite lifting surface is disclosed having a spar, an upper panel and a lower panel each having a free edge, a seal, and an elongated profile located on the panels following a spanwise direction of the trailing edge. An elongated profile including a web extending along the spanwise direction of the trailing edge, and having first and second flange portions, and a transition zone in between the first and second flange portions extending at different heights with respect to each other. The first flange portion is configured to hold at least a part of the seal underneath, and the second flange portion is configured to contact the panel so that the first flange portion secures the seal to the panel, and the second flange portion secures the elongated profile to the panel.

Abstract: A flight control surface comprising a main body comprising an upper and lower cover, upper and lower skins and a core member, a prolongation of their length over the length of the core member defining a stepped area. A trailing edge of the control surface comprises a U-shaped profile enclosing the prolongation, the U-shaped profile extending towards the main body in the chordwise direction up to the stepped area and comprising a section that progressively decreases. The trailing edge comprises a first and a second set of rivets located in the prolongation, the first set of rivets joining the upper and lower covers and the second set of rivets joining the U-shaped profile, the upper covers and the lower covers.

Abstract: A method for manufacturing the trailing edge ribs and the bearing ribs of trailing edges of aircraft lifting surfaces, in which the trailing edge ribs and the bearing ribs are made by joining simple C-shaped parts and/or simple L-shaped parts so as to obtain the final trailing edge ribs and bearing ribs. The manufacturing of the simple C-shaped parts uses the same tooling both for the trailing edge ribs and the bearing ribs, and the manufacturing of the simple L-shaped parts uses the same tooling both for the trailing edge ribs and the bearing ribs.

Abstract: An aircraft installation of a pneumatic system of an aircraft with different compressed air sources for supplying pressurized air to air consumer equipment. Either an air bleed system, electrical compressors, or a combination thereof may perform such supplying of compressed air depending on the aircraft operation condition, for instance the flight altitude or specific flight phases. Also, a turbofan engine, and a method for supplying compressed air to air consumer equipment are disclosed.

Abstract: A duct for a bleed system of an aircraft, wherein the duct extends from an inlet section to an outlet section along a longitudinal axis, and wherein the duct comprises a continuous piece arranged on and protruding from the internal wall of the duct. The duct is subject to temperature gradients in order to reduce the temperature of the warmest airflow closer to the inner wall rather than rapidly mix the airflow.