Abstract: A floor fixing assembly for releasable fixing of a leg of a frame to a vehicle floor comprises at least one retaining peg which can be fixed to the vehicle floor. The floor fixing assembly furthermore comprises a frame fixing element, which is configured to be connected to the leg of the frame and comprises at least one receiving space for receiving the retaining peg. A clamping device is configured to be introduced into the receiving space of the frame fixing element in order to connect the frame fixing element to the retaining peg by form fit.

Abstract: A propulsion assembly including a turbomachine attached to a pylon, and a fire-fighting system, the turbomachine including fire zones, the fire-fighting system including two reservoirs of pressurized extinguishing agent in the pylon and a distribution line connecting the reservoirs to nozzles. The distribution line includes connected pipes having a low point between the reservoirs and the nozzles, and, for each low point, a fluid drainage device for evacuating fluid. The drainage device includes a fluid passage for fluid evacuation from the distribution line and a mechanism for shutting off the fluid passage, the mechanism movable under effect of distribution line pressure, between a first position where it opens the fluid passage and a second position where it closes the fluid passage, the second position being reached when the pressure in the distribution line is greater than or equal to a predetermined pressure.

Abstract: An assembly is disclosed including a first component, a second component, and a spacer component. The first component has a first interface surface. The second component has a second interface surface with a curvature different to the curvature of the first interface surface. The second component is connected to the first component such that the second interface surfaces faces the first interface surface. The spacer component is disposed between the first interface surface and the second interface surface and is configured to be pivotable relative to the first interface surface.

Abstract: The invention provides a drive system for rotating a wheel of an aircraft landing gear. The drive system includes a motor operable to rotate a drive pinion, and a driven gear adapted to be mounted to the wheel. The drive system has a first configuration in which the drive pinion is capable of meshing with the driven gear to permit the motor to drive the driven gear and a second configuration in which the drive pinion is not capable of meshing with the driven gear. The drive system includes a linear positioning actuator for moving the drive pinion relative to the driven gear. The positioning actuator has a first end and a second end, the first end having a pivotal connection with a pivot axis spaced at a fixed distance from an axis of rotation of the driven gear, and the second end having a pivotal connection with a pivot axis spaced at a fixed distance from an axis of rotation of the drive pinion.

Abstract: A composite assembly with a laminate of fibre plies impregnated with a laminate matrix material is disclosed having pad of fibre plies impregnated with a pad matrix material, and a part with a body with protrusions which extend from the body and penetrate at least some of the fibre plies of the pad. The pad is bonded to the laminate by a stepped lap joint or a scarf joint. The assembly is manufactured by pressing the protrusions into the pad, and after the protrusions have been pressed into the pad, curing a pad matrix material impregnating the pad, and bonding the pad to the laminate.

Abstract: An internal structure of a primary exhaust duct of a turbomachine, which has a primary wall allowing air to pass through orifices and forming an internal surface of the primary exhaust duct, an interior skin arranged inside the primary wall, and at least one separator of which a first edge region is attached to the interior skin and which has two geometries. A change from the first geometry to the second takes place when the temperature of the separator exceeds a first temperature, and the change from the second to the first takes place when the temperature of the separator drops below a second temperature. The coefficient of expansion of the separator is greater than that of the interior skin. The variation in the geometry of the separators depending on the temperature of the engine eases assembly at ambient temperature due to the compression of the separators.

Abstract: A pivoting connection device connects at least two components and comprises a guide ring, positioned in an orifice of a first branch of a clevis, which guide ring has a tubular body together with a flange pressing against the interior face of the first branch, a cylindrical shaft connecting the clevis and an arm, having a first end stop, configured to prevent translational movement of the cylindrical shaft in a first sense and a second end stop configured to prevent translational movement of the cylindrical shaft in a second sense, the opposite to the first sense, an immobilizing system configured to immobilize the cylindrical shaft in terms of rotation with respect to the guide ring, the guide ring comprising a first longitudinal groove or slot configured to allow the first end stop to pass.

Abstract: An aircraft air conditioning system comprising an ambient air line, for ambient air to flow through, connected to supply ambient air to a mixer of the aircraft air conditioning system. An ambient air compressor is arranged in the ambient air line for compressing the ambient air flowing there through. A refrigerating apparatus comprises a refrigerant circuit for a refrigerant to flow through, including a refrigerant compressor arranged in the refrigerant circuit. The refrigerant circuit is coupled thermally to the ambient air line to transfer heat from the ambient air to the refrigerant before the ambient air is supplied to the mixer. A cabin exhaust air turbine is connected to a cabin exhaust air line, is coupled to the ambient air compressor arranged in the ambient air line, and is configured to expand the cabin exhaust air flowing through the cabin exhaust air line and to drive the ambient air compressor.

Abstract: An anti-icing protection system for an aircraft engine nacelle, the nacelle comprising an inner shroud provided with at least one acoustic panel, an air intake lip forming a leading edge of the nacelle, the protection system comprising a heat exchanger device including at least one heat pipe configured to transfer heat emitted by a heat source to the acoustic panel or panels.

Abstract: An aircraft engine attachment connecting an attachment body and a primary structure of an aircraft pylon, the engine attachment comprising a shear pin immobilized in translation by a first immobilization system that comprises a shoulder and a removable stop that are integral with the primary structure, between which a flange of the shear pin is immobilized, and a second immobilization system that comprises a stop plate, connected by at least one removable link to the primary structure, which closes the first hole, at least in part.

Abstract: An air supply system comprising at least two bleed sources configured to provide bleed air, wherein each bleed source comprises an engine or an auxiliary power unit and an oil as lubricant for the engine or the auxiliary power unit. The system also includes at least one air conditioning pack for cooling the bleed air from the bleed sources, and a plurality of bleed ducts, wherein each bleed duct connects one of the bleed sources to the at least one air conditioning pack. The system further comprises a plurality of detectors, wherein each detector is associated with a bleed source and the plurality of detectors are configured for detecting substances specific for the oil.

Abstract: A turbofan has a nacelle delimiting a duct for a bypass flow and comprises a fixed structure comprising a guide vane support with guide vanes, a mobile cowl able to move in translation between an advanced position and a retracted position, arms, each one being mobile in rotation between a stowed position and a deployed position and comprising a distal end and a proximal end, a flexible screen, of which an exterior edge is attached to the guide vane support rearward of the guide vanes, and wherein the distal end of each arm is fixed along the interior edge, actuators to cause the mobile cowl to move, and an operating system which moves each arm. Replacing the reversal doors and their drive mechanisms with the flexible screen and the set of rotationally-mobile arms allows a reduction in weight.

Abstract: An emergency localization device for initiating an emergency measure, wherein the emergency localization device comprises a control unit, at least one acceleration sensor and at least one position sensor, the control unit being configured to receive a plurality of motion and/or position parameters from the acceleration sensor and/or from the position sensor, and by evaluating the plurality of motion or position parameters to determine a risk level for an emergency using a predefined logic, and to initiate an emergency measure if the calculated risk level exceeds a predefined threshold. The emergency localization device is reliable, robust and largely independent of aircraft-mounted systems.

Abstract: A door arrangement for an aircraft comprising a door designed to close an aperture in an outer skin of the aircraft, and a articulated arm which is fixed by a first end to the door and which is designed to move the door in at least two translational directions and at least two rotational directions. An aircraft area with this door arrangement and an aircraft having such an aircraft area are furthermore provided. The aircraft area comprises a door aperture arranged in an outer skin of an aircraft, and a door arrangement. Here the door of the door arrangement may be designed to close the door aperture from an inside of the outer skin, and the articulated arm of the door arrangement may be fixed to the aircraft area.

Abstract: An aircraft of the type disclosed here includes an aircraft fuselage, a wing assembly, a tail assembly, and a surface structure containing a lightning protection device. The surface structure is arranged on the aircraft fuselage, the wing assembly, and the tail assembly. The lightning protection device has a plurality of electrically conductive elements, which are arranged at least as a group of elements in the surface structure. The electrically conductive elements belonging to a group are arranged parallel to one another, at least in some section or sections, and have different spacings with respect to one another, at least in two regions.

Abstract: A method for forming fiber composite preforms, the preform (1) include a web (2), a flange (3) and a bent part (2.1), and the method includes: laying-up a laminate (4) onto a tooling (5), the laminate (4) comprising lateral and transverse edges (4.1, 4.2) and the tooling (5) comprising a male part (7) comprising a surface (7.1) and a lateral wall (7.2), the web (2) being configured to be located over the surface (7.1) of the male part (7) and the flange (3) being configured to be located over the lateral wall (7.2) of the male part (7); forming the preform (1) over the male part (7); clamping the lateral edges (4.2) of the laminate (4) to the tooling (5) such that the web (2) and the flange (3) of the laid-up laminate (4) are kept under tensional loads, and bending a longitudinal portion of the male part (7).

Abstract: An indicator generating method for generating an indicator which is suitable for maintenance prediction of a water heating system is proposed. A power state indication device generates a high power consumption signal if a heating device of the water heating system is activated. The time duration of the activation is such an indicator, if no water flow is present. Furthermore, the time interval between subsequent activations is such an indicator. A predictive maintenance method processes these condition-based indicators and determines a remaining useful lifetime according to a predictive maintenance model. The predictive maintenance device outputs a maintenance signal indicating required maintenance, if the remaining useful lifetime drops below a predetermined threshold. The methods may be performed by water heating systems or beverage makers.

Abstract: A boom for an electrical harness, including a straight bar extending in a longitudinal direction, and several supports distributed along and attached to the bar, to which supports at least one electrical harness is connected in operation. The bar includes at least two parts configured to slide relative to one another in the longitudinal direction so that a length of the bar can be adjusted.

Abstract: An aircraft rear engine attachment connecting a primary structure of a pylon and an engine of an aircraft. The rear engine attachment includes first and second rods, each of them including at least two parts, a first part including at least one support orifice, accommodating a support link bar, configured to connect the rod directly or indirectly to the primary structure, at least one second part including at least one engine orifice, accommodating an engine link bar, configured to connect the rod directly or indirectly to the engine, and also detachable link elements for connecting the first and second parts oriented parallel to the direction of the rod.

Abstract: A stowage and removal system for an accommodation space for storing rollable containers in a vehicle is provided. It preferably has a rail system in the floor region of the accommodation space, on which rail system a transfer plate is movable, which transfer plate can assume a storage position and an insertion and removal position for the container. The storage position of the container is provided with its rear wall in the region of the rear wall of the accommodation space. The insertion and removal position is provided in the region of an insertion opening, arranged oppositely in relation to the rear wall, for the insertion and removal of a container into the accommodation space.