Abstract: An aircraft fuselage is configured to receive two tanks designed to contain liquid hydrogen. The fuselage includes a first section for a cockpit, a second section for a passenger cabin and a third section (T3) distinct from the first section (T1) and from the second section (T2). The third section (T3) includes two housings each to house a tank. The two housings are arranged symmetrically with respect to a vertical plane of symmetry (P1). This arrangement of the tanks in a section distinct from the other sections allows them to be located as close as possible to the motors that they have to supply.

Abstract: An overheat detection system for an aircraft, the system comprising a first bleed monitoring computer, BMC1, configured to identify leakages in a pneumatic system, the BMC1 including a first optical controller, a second bleed monitoring computer, BMC2, the BMC2 including a second optical controller, an optical fiber link connecting the first optical controller of the BMC1 and the second optical controller of the BMC2 for communication between the BMC1 and the BCM2 and between the first optical controller and the second optical controller, wherein the first and the second optical controllers are configured to detect overheat of the optical fiber link based on a wavelength shift of a modulated optical signal transmitted through the optical fiber link, and transmit signals to the first BMC1 and the second BMC2 based at least on the detected overheat.

Abstract: When coupling tubular parts by fitting, the seal interposed between them may roll on itself, be pinched or damaged. Now, a twisted or damaged seal no longer correctly ensures the seal-tightness and it is very difficult to detect this. The present application discloses a tool for installing a seal between two tubular parts, one male and one female, including a compression ring to encircle the male part and exert a compression on the seal before producing the join. The tool also includes a tongue that can be positioned at a chamfered surface of the female tubular part. The tongue makes it possible to offer the pre-compressed seal with the dimensions of the female part a continuous travel making it possible to prevent any twisting or other effect compromising the seal-tightness.

Abstract: A wing arrangement for an aircraft, comprising a wing having a base section and a tip section pivotably connected to base section such that the tip section is pivotable about a pivot axis between a deployed position and a stowed position. The wing arrangement also comprises a latching arrangement which includes an engagement portion, a latching actuator selectively movable between a first actuator position and a second actuator position, an elastically deformable structure, and a latching element. When the tip section is pivoted from the stowed or deployed position into an engagement position, the elastically deformable structure is initially deformed, and as the tip section pivots further into the deployed or stowed position, the elastic deformation of the elastically deformable structure decreases.

Abstract: A method for assembling a primary structure of an aircraft pylon, includes a step of fixing an angle bracket to each of the first and second lateral panels such as to obtain an L form for each of the first and second lateral panels prior to a placement of said L forms each placed against two sides of each transverse frame. This assembly technique makes it possible to reduce the mounting clearances such that it is unnecessary to fit shims, resulting in a reduction of mounting time and manufacturing costs.

Abstract: A method for assembling an aircraft pylon having a primary structure and at least one internal system at least partially positioned within the primary structure, wherein the internal system is positioned inside the primary structure before the last lateral panel of the primary structure is attached. The absence of one of the lateral panels facilitates the installation of the internal systems.

Abstract: A method for assembling a primary structure of an aircraft pylon, includes a step of fixing an angle bracket to each of the first and second lateral panels such as to obtain an L form for each of the first and second lateral panels prior to a placement of said L forms each placed against two sides of each transverse frame. This assembly technique makes it possible to reduce the mounting clearances such that it is unnecessary to fit shims, resulting in a reduction of mounting time and manufacturing costs.

Abstract: An external part of an aircraft (such as a fairing) comprising a skin made with flexible materials attached to rigid supporting elements (such as longerons and frames) arranged in, at least, two directions. The skin comprises inner inflatable panels in all bays delimited by the rigid supporting elements and/or an external inflatable panel. The skin is joined to the supporting elements so that its external surface complies with aerodynamic requirements.

Abstract: The present disclosure refers to a method for operating a landing gear system, preferably in a tricycle configuration, wherein main landing gear (MLG) and the nose landing gear (NLG) are operable from a retracted position where they are housed respectively inside landing gear bays, to a fully extended position where they are extended for landing the aircraft. According to the disclosure, the extension of the nose landing gear (NLG) is delayed in time with respect to the extension of the main landing gear (MLG), and the nose landing gear (NLG) is kept retracted during a major part of the time that the main landing gear doors (MLGD) are extended. In this manner, vibrations on the main landing gear doors are reduced and incidents caused by fatigue are also reduced, which in turn implies that the maintenance cost of the aircraft is greatly reduced.

Abstract: A fixed wing of an aircraft, having a main wing extending over a half-span with a wing box including spars extending along the spanwise direction of the main wing, ribs arranged one in back of the other viewed in the spanwise direction, and an outer skin. The wing box includes a wing box base section (K10) and a wing box adapter section, that forms the outer end area of the wing box, as viewed from the wing root, and is designed to secure a wing tip device. In its nominal state of construction, the dihedral angle of the wing box adapter section referring to the respective local spanwise direction continuously increases by at most 60 degrees from the outer rib of the wing box base section (K10) up to the outermost rib of the wing box adapter section.

Abstract: An apparatus for fabricating a fiber reinforced thermoplastic composite structure is described. The apparatus comprises a localized heat source arranged to heat a portion of a stack of fiber reinforced thermoplastic material layers and an ultrasonic transducer arranged to locally introduce ultrasonic energy waves to the heated portion of the fiber reinforced thermoplastic material layers. The apparatus makes it possible to achieve ultrasonic consolidation of the layers occurs.

Abstract: A fuel system includes a fuel tank, a vent tank fluidically connected to the fuel tank ullage, the vent tank having a duct open to the ambient atmosphere and the interior of the vent tank, and a catalyst disposed in the duct, wherein the catalyst is adapted to deplete one or more reactive components of gas flowing through the duct by catalytic reaction. Also, a method for depleting one or more reactive components of gas in the fuel system, includes depleting one or more reactive components of gas flowing through the duct using the catalyst.

Abstract: A fixed wing of an aircraft, having a main wing extending over a half-span with a wing box including spars extending along the spanwise direction of the main wing, ribs arranged one in back of the other viewed in the spanwise direction, and an outer skin. The wing box includes a wing box base section (K10) and a wing box adapter section, that forms the outer end area of the wing box, as viewed from the wing root, and is designed to secure a wing tip device. In its nominal state of construction, the dihedral angle of the wing box adapter section referring to the respective local spanwise direction continuously increases by at most 60 degrees from the outer rib of the wing box base section (K10) up to the outermost rib of the wing box adapter section.

Abstract: An assembly comprising at least two non-metal components which are fixed to each other using at least one fixing system. The fixing system includes a fixing device with a fixing element which is provided with a head and a rod, and a crimping ring which is in contact with one of the components. A protection device is a part of the fixing system which delimits a cavity for confining gas around a portion of the device comprising the crimping ring. In order to improve the repeatability of the operation for positioning the protection device, a guiding device is provided which includes an assembly element on the portion of the fixing device, and an element for guiding the protection device.

Abstract: An assembly comprising at least two non-metal components which are fixed to each other using at least one fixing system. The fixing system includes a fixing device with a fixing element which is provided with a head and a rod, and a crimping ring which is in contact with one of the components. A protection device is a part of the fixing system which delimits a cavity for confining gas around a portion of the device comprising the crimping ring. In order to improve the repeatability of the operation for positioning the protection device, a guiding device is provided which includes an assembly element on the portion of the fixing device, and an element for guiding the protection device.

Abstract: A monitor for monitoring the concentration of oxygen in a fuel or in an ullage over a fuel comprises (i) a sensing element comprising a luminescent substance comprising a luminophore and a support in which the luminophore is covalently bound to the support, (ii) a light source arranged to irradiate the sensing element with light, and (iii) a photosensor arranged to detect light emitted from the luminescent substance. The luminescent substance may be, for example, a platinum porphyrin covalently bound to silica.

Abstract: An aircraft includes a hose that makes it possible to channel the pressurized air that is used in a sleeve (52) that delimits an annular chamber with the hose, with the sleeve (52) including at least one opening (54) that is delimited by an edge (58) that makes it possible to link the annular chamber and the outside of the sleeve (52), and a leak detection system that includes at least one loop (A) in the form of a threadlike element (56), characterized in that it includes a connecting device that includes a ring (60) that is connected at at least one connecting point (64) with a loop (A), and a flexible wall that delimits a hose (68) for channeling the air that extends from the edge (58) of the opening (54) up to the ring (60).

Abstract: An apparatus for fabricating a fibre reinforced thermoplastic composite structure is described. The apparatus comprises a localised heat source arranged to heat a portion of a stack of fibre reinforced thermoplastic material layers and an ultrasonic transducer arranged to locally introduce ultrasonic energy waves to the heated portion of the fibre reinforced thermoplastic material layers. The apparatus makes it possible to achieve ultrasonic consolidation of the layers occurs.

Abstract: A method of fabricating a fiber reinforced thermoplastic composite structure comprising: placing a first layer of fiber reinforced thermoplastic material on top of a second layer of fiber reinforced thermoplastic material; providing a local heating source and locally heating a portion of at least the upper layer of thermoplastic composite material; and providing an ultrasonic transducer and locally introducing ultrasonic energy waves to the heated portion of the thermoplastic material such that ultrasonic consolidation of the fiber reinforced thermoplastic occurs.

Abstract: A method of designing a structure, such as an airfoil section. A first set of candidate designs is generated in a first optimisation process, each candidate design comprising a set of M design variables associated with an M-dimensional design space. A subset of the first set of candidate designs is selected. The selected subset of candidate designs is analysed by proper orthogonal decomposition or principal component analysis to generate an N-dimensional design space defined by N design variables, N being less than M. A second set of one or more candidate designs is then generated in a second optimisation process, each candidate design comprising a set of N design variables associated with the N-dimensional design space.