Abstract: A hydrogen tank for aircraft, including an inner vessel configured to contain hydrogen, first and second outer jacket domes having a semi-spherical shape and first L-shaped ends, a first semi-cylindrical outer jacket established on top of the first and second outer jacket domes, a second semi-cylindrical outer jacket established in the bottom of the first and second outer jacket domes. The first and second semi-cylindrical outer jackets include second L-shaped ends. The first and second L-shaped ends form L-shaped junctions to attach the first and second outer jacket domes to the first and second semi-cylindrical outer jackets.

Abstract: A device and a process for manufacturing a composite part, the device comprising four molding mandrels that can be arranged in a mold arrangement in which they form a mold for the composite part, as well as a locking mandrel configured to lock the molding mandrels in the mold arrangement and to be extracted from between the molding mandrels to release the molding mandrels from their mold arrangement. The locking mandrel extends from one longitudinal end of the molding mandrels to another opposite longitudinal end of the molding mandrels.

Abstract: A method for the assembly of frames in an aircraft shell, wherein the aircraft shell comprises a skin and a plurality of stringers co-cured with the skin, wherein the skin has a plurality of reference marks. Identifying the reference marks on the skin using a first robot with artificial vision, establishing a local reference for the positioning of each frame based on a reference mark, grabbing a frame using the first robot, establishing a relative position between the first robot and the frame based on the reference mark, positioning the frame on an inner side of the aircraft shell using the first robot, and with a second robot, drilling holes through the frame and skin, and attaching the frame to the skin with fasteners.

Abstract: A drilling machine and a drilling method including drilling a first bore in a material with a drilling machine by applying a torque to a drilling tool for imparting a rotation at a first rotational speed to the drilling tool, and applying a thrust to the drilling tool for advancing the drilling tool at a first feed speed into the material, wherein a drilling parameter is measured while drilling the first bore, and a second rotational speed and a second feed speed are determined based on the drilling parameter, then drilling a second bore at the second rotational speed and at the second feed speed.

Abstract: An exhaust muffler for an APU of an aircraft, including an exhaust gases inlet, an exhaust gases outlet, a peripheral wall configured to guide a flow of exhaust gases between the inlet and the outlet. The peripheral wall includes at least one vacuum chamber to provide thermal insulation.

Abstract: A rear pressure bulkhead comprising a dome shaped structure, and a set of built-in extension components (“petals”) homogeneously distributed along the periphery of the dome-shaped structure. This results in the dome-shaped structure being secured to a frame of the aircraft, while the extension components are secured to longitudinal structures of the aircraft. An aircraft rear fuselage is provided including such a rear pressure bulkhead so that the available cabin space, i.e., pressurized space, is extended without enlarging the fuselage.

Abstract: A manufacturing method of a control surface of an aircraft, the control surface including an upper skin, a lower skin, ribs joining the upper skin and the lower skin and located along a chordwise direction of the control surface. The manufacturing method includes the steps of providing a single composite preform comprising the upper skin, the lower skin and the ribs, and curing the single composite preform such that an integrated box comprising the upper skin, the lower skin and the ribs is formed.

Abstract: An aircraft empennage, comprising a rear fuselage section, a trimmable horizontal tail plane comprising a first and a second lateral torsion box), each comprising a front spar and a rear spar, a front fitting and a rear fitting, an actuator acting on the front fitting for a rotation of the trimmable horizontal tail plane around a hinge axis passing through the rear fitting, the front fitting comprising a first and a second front fitting units being joined to the front spars of the lateral torsion boxes, and the actuator comprising first and a second actuator units, each acting on the first front fitting unit and the second front fitting unit respectively.

Abstract: A manufacturing system (1) for manufacturing shaped laminates including: forming tools (2.1, 2.2) extending along a longitudinal direction X, located parallel to one another and configured to receive a laminate (4) between the forming tools; a shaping tool (3) extending along the longitudinal direction X and along a transversal direction Z, and configured to receive the laminate (4) on an external surface of the shaping tool, wherein the forming tools (2.1, 2.2) or the shaping tool (3) are movable in the longitudinal direction X and in the transversal direction Z, relative to the at least one of the shaping tool (3) and the two forming tools (2.1, 2.2).

Abstract: An aircraft empennage includes a vertical tail plane, a rear fuselage section attached to the vertical tail plane and including a skin and internal reinforcing members, a horizontal tail plane comprising two lateral torsion boxes and a framework located between the two lateral torsion boxes comprising a front spar, a rear spar and two ribs extending between the front and the rear spar and each adjacent to a lateral torsion box. The framework encloses a portion of the vertical tail plane along its spanwise direction. The aircraft empennage includes an attachment assembly attaching the framework to the rear fuselage section, the attachment assembly crossing the skin and extends between the internal reinforcing members of the rear fuselage section and the framework.

Abstract: An airfoil of an aerodynamic surface including: a control surface having an upper surface and a lower surface, and an actuator configured to elevate or lower the control surface, wherein at least a portion of one of the upper surface and the lower surface of the control surface is auxetic with a negative Poisson ratio, and the other of the upper surface and the lower surface of the control surface includes a material with a higher Poisson ratio.

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: A profile for a trailing edge of an airfoil, the trailing edge including flanges, and the profile is U or V shaped, is made of composite material and includes: sections joined at a first profile end and defining an inner space, and recesses arranged along the two sections towards the inner space and complementary to each other between the two sections; wherein the profile is configured to follow a theoretical aerodynamic contour of the airfoil so that the two sections partially cover the trailing edge and the flanges are housed inside the inner space, and wherein each of the plurality of recesses defines at least two joining points through which the two flange of the trailing edge and the two sections are configured to be joined each other.

Abstract: An electric propulsion unit of an aircraft including a nacelle housing an electric power system, an electric motor and a cooling system for the electric power system; the nacelle including a central fairing, a front fairing which extends from the central fairing to a front end and a rear fairing which extends from the central fairing to a rear end. The front fairing includes a protrude positioned in a lower part of the front fairing, the protrude having a front face in a transverse plane, a main air inlet of the cooling system being positioned on the front face.

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: 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 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: 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.