Abstract: A fluid tank for integration into a structure of an unmanned aircraft includes a shell having a first axial wall, an oppositely arranged second axial wall, an upper side, a lower side, and an enclosed interior, at least one receiving chamber in the interior for storing fluid, and a collection chamber, which is arranged on the lower side and which is fluidically connected to the at least one receiving chamber. The collection chamber includes a bottom surface, through which there extends a drain, wherein a covering surface is arranged above the bottom surface and covers at least a portion of the collection chamber. At least one flow opening could be arranged on an upper side of the collection chamber, which flow opening allows gas bubbles to escape in the direction of the upper side of the fluid tank.

Abstract: A connection assembly between two portions of a supply line for a cryogenic fluid, the assembly including a male nozzle arranged to be at least partially inserted into a female nozzle together forming a tight mechanical link, over a distance of a few centimeters, a thermal insulation chamber for each of the two line portions and an additional thermal insulation chamber to thermally insulate the connection zone of the two line portions, and an expansion chamber for the cryogenic fluid that is configured to be linked to a cryogenic fluid sensor, arranged about the connection zone of the two line portions. This enables two cryogenic fluid line portions to be connected without requiring one portion to be inserted into the other portion over a significant length, thereby enhancing mechanical flexibility and obviating the need for significant free space about the connection assembly to assemble and disassemble the assembly.

Abstract: A mount for a double-walled vessel includes a first support to support the mount against an outer wall of the double-walled vessel, a second support to support the mount against an inner wall of the double-walled vessel, and a flexible member connecting the first support and the second support. The first support and can be arranged at a first end of the flexible member and the second support can be arranged at a second end of the flexible member opposite to the first end. Further described are a vessel including at least one such mount as well as a vehicle including such vessel.

Abstract: A method for providing training images including receiving information about objects which is at least valid at a specific recording time. The method includes receiving an image of an area imaged at the specific recording time. The method includes estimating respective positions of the objects at the specific recording time based on the information and selecting estimated positions of respective objects from the estimated respective positions which fulfill a predefined selection criterion. The method includes generating training images by separating the imaged area into first and second pluralities of image tiles. Each of the first plurality of image tiles differs from each of the second plurality of image tiles. Each of the first plurality of image tiles images (depicts) a respective one or several of the selected positions. The method includes providing the training images. Further, a training image product and a device for providing training images are provided.

Abstract: A bypass turbofan with a nacelle delimiting a stream and including a cowl mobile in translation between an advanced position in which a window is open between the stream and the exterior, transmission systems, each of which includes at least one arm mobile in rotation between retracted and deployed positions across the stream, in which each transmission system is mobile in translation between advanced and retracted positions, for each arm, a flexible veil fastened to the arm and alternately occupying a folded or unfolded position, and, for each transmission system, an actuator configured to move the mobile cowl, the transmission system and each arm.

Abstract: A mold core for producing a component of fiber composite material with a cavity makes a particularly simple and efficient demolding process possible by the mold core extending along a longitudinal axis and in the form of a hybrid core and which includes, viewed in a cross section perpendicular to the longitudinal axis, a first core portion and a second core portion, wherein the first core portion has a thickness that is substantially greater than a thickness of the second core portion. The first core portion is formed from a first material with high stiffness and low coefficient of thermal expansion, and the second core portion is formed from a second material that differs from the first material, and is configured such that, under predetermined conditions, its form changes in a predetermined manner such that removal of the mold core from a cavity in the cured component is made easier.

Abstract: An auxiliary power unit for an aircraft. It includes an air compressor coupled to an air-drawing device for drawing in air from outside the aircraft, the compressor supplying compressed air to a manifold. The manifold is configured to supply air to an environmental control system and a start-up module of at least one propulsion system of the aircraft running on hydrogen. The manifold is also configured to supply air to a fuel cell stack arranged to provide an electric generation function configured to power non-propulsive systems of the aircraft, the fuel cell stack also being supplied with hydrogen from a tank supplying hydrogen to the at least one propulsion system of the aircraft.

Abstract: A flexible pillar for a variable geometry flight control surface including upper skin and lower skins includes an elongate shape elastic element having an and at least a first end and a second end. The flexible pillar can be disposed between the upper skin and the lower skin so the elastic element can be fixed to the upper skin at the first end of the flexible pillar and fixed to the lower skin at the second end of the flexible pillar. The flexible pillar has a rigidity along the longitudinal axis of the flexible pillar that is greater than a rigidity of the flexible pillar in shear along a transverse axis of the flexible pillar, the flexible pillar making it possible to obtain a support having a longitudinal direction and able to transmit forces between its ends without, or with little, deformation longitudinally and to be easily deformed in a transverse direction.

Abstract: A door for a thrust reversal system, an aircraft with such a door, and a method for manufacturing a door of a thrust reversal system. The door comprises a wall formed from long fibers embedded in a thermoplastic resin matrix and a network of ribs overmolded on one of the faces of the wall. A propulsion assembly of an aircraft comprises a thrust reversal system having a plurality of such doors.

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: An assembly of a pylon and of an engine with a rear engine attachment having two fittings, wherein each one has a shoe fastened to a lower spar of the pylon, two transverse arms, one front and one rear, which are as one with the shoe and offset such that the front transverse arm, respectively rear transverse arm, of one fitting bears in planar fashion against the front transverse arm, respectively rear transverse arm, of the other fitting, wherein each transverse arm is pierced with a bore, wherein the two front transverse arms and the two rear transverse arms are spaced apart parallel to the longitudinal direction and thus form a female clevis, and wherein the assembly also has a lower rod mounted articulated in the female clevis and on the engine. With such an assembly, the number of components is reduced.

Abstract: This control system takes into account the thermomechanical aspects of materials to quickly and easily determine optimal cutting conditions and to automatically control machining to preserve the integrity of the workpiece. This system includes an acquisition module configured to acquire values of a set of input parameters relating to cutting conditions and material properties of the piece, and a microprocessor configured for determining at least one operating cutting parameter representative of a cutting signal from the machining apparatus using a set of output parameters of an integrity model previously constructed during a learning phase. The integrity model connects the set of input parameters to the set of output parameters comprising specific cutting coefficients representative of the material integrity of the piece, and establishes at least one fatigue threshold of the at least one cutting operating parameter. The fatigue threshold allows control of the progress of cutting operations.

Abstract: An aircraft including a first electrical distribution busbar and a second electrical distribution busbar extending at least in part in a fuselage of the aircraft, in a longitudinal direction of the fuselage. A first electric generator is connected to the distribution conductors of the first electrical distribution busbar via a first coupling switch directly connected to the first electric generator and to the distribution conductors of the first busbar. A second electric generator is connected to the distribution conductors of the second electrical distribution busbar via a second coupling switch directly connected to the second electric generator and to the distribution conductors of the second busbar. The first coupling switch and the second coupling switch are positioned in the aircraft independently of one another.

Abstract: An inflatable suspended ceiling for a vehicle compartment, in particular for a passenger cabin of an aircraft, includes a flat fabric cover sheet configured to roof over at least a longitudinal section of an interior space along an extending direction of the vehicle compartment underneath a structural ceiling of the vehicle compartment, and a tensioning structure attached to the cover sheet to carry the cover sheet from above and having a flexible envelope enclosing at least one inflatable chamber configured to tension the cover sheet when inflated. Mounting members are attached to the tensioning structure to mount the tensioning structure to counter-mounting members on the structural ceiling in a hanged configuration.

Abstract: A method of providing a deformable shim that comprises a main structure of an at least partly cellular region. The main structure is compressible by plastic deformation from an initial volume to a deformed volume, wherein the deformed volume is smaller than the initial volume. In a deformed state, the main structure maintains the deformed volume without further or continuing compression force. Further, the main structure is arrangeable between a first aircraft component and a second aircraft component to create a predefined distance between the first and the second aircraft component.

Abstract: An induction heated tool system for receiving and heating polymer-fiber components from a starting temperature to a target temperature includes a tool part having a receiving cutout, the tool part formed from a thermally dimensionally stable material so it has a coefficient of thermal longitudinal expansion less than 10×10?6 K?1, or less than 5×10?6 K?1, or less than 4×10?6 K?1 in the plane of the largest dimension of the receiving cutout, at temperatures between the starting and target temperatures. A receiving cutout for receiving a polymer-fiber component is in the tool part, the receiving cutout delimited by a receiving surface portion so a polymer-fiber component received in the receiving cutout can lie against the receiving surface portion. A susceptor element includes a ferromagnetic material with a first Curie temperature. The susceptor element is on a surface portion of the tool part outside the receiving cutout and the receiving surface portion.

Abstract: A system for assisting the maintenance of an aircraft is configured for implementing the following steps in an iterative manner determining a spectral power density of the position of a control surface over a time window; when the spectral power density corresponds to an amplitude of oscillations of the control surface upwardly crossing this predetermined threshold, storing an excess amplitude start time; and when the spectral power density corresponds to an amplitude of oscillations of the control surface downwardly crossing this predetermined threshold: determining a time interval between the excess amplitude start time and an excess amplitude end time, during which the amplitude of oscillations of the control surface has remained above the predetermined threshold; and determining an indicator representative of the energy corresponding to these oscillations during the time interval.

Abstract: An aircraft comprising a fastening element and an engine pylon with two rear covers. Each cover includes a movable lower cover mounted articulated on a rear portion in which in the closed position, the two movable lower covers are moved together and in which in the open position, they are tilted and moved apart from each other. For each movable lower cover, a hinge system, and at least one locking system locks the two movable lower covers together in the closed position and locks each movable lower cover to the fastening element in the open position. The presence of the movable lower covers provides, inter alia, easy access to the inside of the engine pylon, and the locking system locks the movable lower covers.

Abstract: A lightning strike protection material for an aircraft includes an electrically-conductive grid with grid-forming members and nodes where grid-forming members overlap or intersect. A plurality of the grid-forming members and/or nodes include an outward-facing surface, and at least a portion of the outward-facing surface is concave.

Abstract: A multipurpose tool for flight attendants includes a telescopic arm on which two handle elements are articulated at opposite ends, which handle elements can be folded in so as to lie adjacent to one another. By folding the handle elements apart and extending the telescopic arm, the multipurpose tool can be used in a variety of ways. In addition, fold-out tools may likewise be arranged on the multipurpose tool.