Abstract: The present disclosure refers to a method for manufacturing carbon fiber panels stiffened with omega stringers for the construction of aircraft structures, such as fuselage sections, wing panels, etc. One tubular pressure member is provided for each omega stringer of the structure to be manufactured, wherein the tubular pressure member is configured with the shape of the omega stringer. Each tubular pressure member is enclosed between the omega stringer and part of the laminate, and autoclave pressure is applied to the interior of the tubular pressure member, so that the tubular pressure member is used to consolidate the omega stringers and/or part of the laminate from the interior of these two elements, while these two elements are being co-cured or co-bonded in an autoclave. Imperfections on those internal surfaces such as resin wrinkles of the structure are reduced.

Abstract: An electric power distribution system for an aircraft is provided, which includes an engine gearbox, a power distribution center, two or more three-phase synchronous electric power generators, a neutral current transformer per generator, a single set of power feeder wires, and a single generator control unit (GCU). The generators are connected in parallel with each other, and connected with the power distribution center by the same set of power feeder wires. The GCU is electrically coupled with each generator to feed the generator with an excitation field current, and with each neutral current transformer to sense an instantaneous neutral-current value. The GCU is adapted to perform a generator voltage regulation loop based on a desired voltage value and the at least two sensed instantaneous neutral-current values by individually modifying the excitation field current of each generator.

Abstract: An aircraft aerodynamic surface (1) including a torsion box (2) having a front spar (21) and rear spar (22), a first control surface (3) including a front spar (31) and a trailing edge (32) and a second control surface (4) having a front spar (41), a trailing edge (42), and a pivot device (5, 6, 7, 8) for pivotally attaching the first control surface (3) and the second control surface (4) to the rear spar (22) of the torsion box (2), the first control surface is an inboard control surface (4) including two lateral ribs (9, 9?), six inner ribs (11, 12, 13, 14, 15, 10) and an inner spar (16), and the second control surface (3) is an outboard control surface which includes two lateral ribs (20, 20?), three internal ribs (17, 18, 19), two internal spars (24, 24?) and one internal spar (23).

Abstract: A leading edge section with laminar flow control includes: a perforated outer skin, a perforated inner skin, and a plurality of suction chambers formed between the outer skin and the inner skin. The leading edge section includes a plurality of stringers span-wise arranged at the leading edge section, and integrally formed with the outer skin, such that the inner skin is joined to the stringers. A method for manufacturing a leading edge section integrating a laminar flow control system is described, wherein a perforated inner skin is joined with a perforated outer skin having a plurality of stringers integrally formed with the outer skin, such that suction chambers are defined by a part of the outer skin, a part of the inner skin and a pair of stringers.

Abstract: An inspection tool for inspection of a hole of a metallic lug, including, a first arm, a second arm, a third arm, and a housing element, wherein the first arm, the third arm and the housing element may vary their position independently of each other in relation to the second arm. Also, the present invention discloses an inspection device for inspection of a metallic lug that comprises an inspection tool and a probe housed in the housing element, and a method for detecting cracks around metallic lug.

Abstract: A system for curing polymer matrix composite parts out of autoclave in manufacturing and repairing processes including: (i) an inner vacuum bag (3) placed over the lay-up to be cured located over a working area (15, 18) with the edges of the inner vacuum bag (3) joined to the working area by first sealing elements (8); (ii) a Perforated bulkhead (4) located over the inner vacuum bag (3), (iii) an Outer vacuum bag (2) over a perforated bulkhead (4) and over the edges of the inner vacuum bag with the edges of the outer vacuum bag (2) joined to the working area (15, 18) by second sealing elements (1), (iv) a vacuum device (5, 7, 6) and (v) a heating source (9, 20).

Abstract: A gas turbine engine for an aircraft includes a compressor, a combustion chamber, and a turbine having at least one stator, and at least one rotor. Each stator and rotor is formed by a plurality of blades, a fluid channel is formed between two consecutive blades, and each blade has two opposing surfaces. The compressor is in fluid communication with a first group of stator channels, and the combustion chamber is in fluid communication with a second group of stator channels, such that heat exchange can be performed through two opposing surfaces of at least one stator blade. The outer and the inner walls define a duct for the passage of the heated fluid through the rotor blades, and the outer wall is also arranged for directing the compressed air towards the combustion chamber.

Abstract: A boundary layer suction system adapted to a surface exposed to the circulation of a fluid. The system comprises a portion of the surface, a bifurcation element for bifurcating a mass of fluid flowing along the front face of the surface, comprising an airfoil-shaped cross-section such that the fluid is bifurcated into a first and a second flow, a slot located on the portion of the surface and downstream of the leading edge of the bifurcation element, the slot communicating the front and the rear faces of the portion of the surface, and an arrangement to provide a pressure difference between the front and the rear faces of the surface around the slot, such that a suction of the boundary layer is performed through the slot by the pressure difference.

Abstract: An air conditioning system 1 for a cabin 10 including a pressurized air source 2, a cooling air source 3, a main heat exchanger 4, a compressor 5, a manifold 6 and a mixing chamber 7. An inlet 43 to a cold side of the main heat exchanger 4 is in fluid communication with the cooling air source 3. An inlet 41 of a hot side of the main heat exchanger 4 is in fluid communication with the pressurized air source 2. An inlet 51 of the compressor is in fluid communication with the outlet 44 of the cold side of the main heat exchanger 4.

Abstract: An engine bleed air system of an aircraft, comprising a heat exchanger which comprises a rectangular core with a rectangular outlet section, a cylindrical outlet duct and a transition area between the rectangular outlet section of the rectangular core and the cylindrical outlet duct, and at least a downstream system, further comprising a flow deflector located at least in the cylindrical outlet duct, such that the outlet flow characteristics homogeneity are improved and a particular flow deflection and distribution of the outlet flow is achieved, avoiding the damage of the at least one downstream system. The invention also provides a method for homogenizing the temperature of the outlet flow of a heat exchanger outlet in an engine bleed air system of an aircraft.

Abstract: A lightweight shield for aircraft protection against threat of high energy impacts, which comprises, a structural layer that has a first side and a second side, the first side being intended for receiving the impact, and a ballistic material layer for absorbing high energy impacts, having a first side and a second side. The first side of the ballistic material layer is faced to the second side of structural layer and joined to the structural layer via a progressively detachable interface and, the second side of the ballistic material layer is a free surface.

Abstract: A system for testing bonded joints that comprises a swing tool, an actuator, pressure measuring device and a first fixing arrangement. The actuator of the system is configured to apply a compression force or a traction force on the swing tool in order to separate two elements, and the pressure measuring device is configured to measure the force applied on the swing tool. A method for testing bonded joints using the system is also provided.

Abstract: An aircraft with an auxiliary power unit attached to the aircraft fuselage via an attachment system. The auxiliary power unit is placed inside the aircraft fuselage structure. The attachment system comprises a plurality of structural wires that link the auxiliary power unit to the aircraft fuselage structure. An attachment device is located at the end of each structural wire to connect the structural wire to the aircraft fuselage structure. Each attachment device comprises a metallic plate adjacent to the aircraft fuselage structure and a layer of damping elastomeric material adjacent to the metallic plate. The metallic plate is placed between the layer of damping elastomeric material and the aircraft fuselage structure. The attachment device is joined to the aircraft fuselage structure by attachment fasteners.

Abstract: The present invention relates to a door for closing an opening in a structure, including: a body arranged to be capable of abutting against a first side of the opening; at least one clamping member configured to be capable of abutting against an opposite second side of the opening; and a fastener arranged to fasten or release the clamping member relative to the body. The clamping member is moveable relative to the body between a first position where the clamping member abuts against the second side of the opening so as to clamp the structure between the body and the clamping member and a second position where the clamping member allows the door to be opened. The present invention further relates to an aircraft including the above door.

Abstract: This disclosure relates to the manufacturing of a leading edge section with hybrid laminar flow control for an aircraft. A manufacturing method involves: providing an outer hood, a plurality of elongated modules, first and second C-shaped profiles having comprising cavities, and an inner mandrel; assembling an injection molding tool by placing each profile on each end of the inner mandrel, arranging a first extreme of each elongated module in one cavity of the first profile and a second extreme of the module in another cavity of the second profile, both cavities positioned in the same radial direction; and placing the hood on first and second profiles to close the tool. Further, the injection molding tool is closed and filled with an injection compound comprising thermoplastic and short-fiber. Finally, the compound is hardened and demolded.

Abstract: A propulsion engine comprising at least a first propulsion unit including a first fan encased by a geared ring and a gas turbine engine driving a first shaft connected to the first fan, at least a second propulsion unit including a second fan encased by a geared ring connected to a second shaft operatively coupled to an electric machine and at least an electric storage device connected to the electric machine. The geared rings are configured to transmit torque between the fans so that they can rotate in conjunction (directly or through an intermediate gear) when they are driven by at least one of said first and second shafts. The propulsion engine is arranged for controlling the torque to be supplied to the assembly of the first and second fans by the gas turbine engine and/or by the electric machine acting as a motor or as a generator.

Abstract: A sandwich structure architecture for high speed impact resistant structure includes sandwich skins which enclose a sandwich core formed by a plurality of spacing layers and a plurality of trigger layers, wherein these layers are stacked alternatively in the core. The walls of the trigger layers are thicker than the walls of the spacing layers and/or the walls of the trigger layers include at least one part inclined with respect to the walls of the spacing layers. The spacing and the trigger layers are made of the same type of material, preferably composite materials or metallic materials. The structure is capable of absorbing high-speed impacts, and at the same time can be used as load carrying structure in aircraft fuselages, wings, vertical or horizontal stabilizers.

Abstract: The present disclosure refers to a method for measuring thickness in any type of carbon fiber component, even in components having parts with different thickness and integrating at least a second material. The method includes measuring with the maximum and minimum real thickness of the component, and measuring with ultrasonic equipment the time that the ultrasound takes to propagate across the component part with maximum and with minimum thickness, calculating a thickness correction value, and calculating an ultrasound test speed from said thickness correction value, said measured times, and said measured maximum and minimum real thickness. Then, the total thickness of each of the parts of the component are measured, using ultrasounds with the same calculated ultrasound test speed, and the thickness correction value is applied to each of the measuring total thickness of each part, to determine a corrected carbon fiber thickness for each part.

Abstract: A self-destruction device adapted to be installed in a propeller blade, the self-destruction device including a detector adapted to detect a release of the propeller blade, a warning mechanism adapted to send a release alarm in the event of the detector detecting release of the propeller blade, and a destruction mechanism adapted to destroy the propeller blade in the event of receiving a release alarm from the warning mechanism. An engine and an aircraft are also provided.

Abstract: A leading edge for an airfoil comprising a torsion box, the leading edge comprising a leading plate and a first inflatable element suitable for being filled with air. The leading plate comprises a convex side and a concave side. The first inflatable element is in contact with at least part of the concave side, thus reinforcing the leading plate. An airfoil comprising such a leading edge is also provided.