Abstract: A mounting assembly for the mounting of components in a body of a vehicle comprises at least one base element, at least one holding rail and connecting elements. The base element is designed to be arranged on the body of the vehicle. The holding rail is designed for mounting the components, and the base element and the holding rail are connected by the connecting elements so as to be spaced apart from each other.

Abstract: An arrangement for adapting the transportation behavior of material to be conveyed includes a first container, which is coupleable to a first pressure level; a second container, which is coupleable to a second pressure level; a connecting line for transporting material to be conveyed from the first container to the second container; and a pressure reduction device by which a pressure difference between the first container and the second container is controllably variable.

Abstract: An evaluation method and an evaluation system onboard an aircraft in communication with a flight management system to access a flight plan stored in memory of the flight management system, where the flight plan defines a cruising level and a minimum fuel reserve to destination objective. The evaluation system comprises circuitry to calculate a fuel consumption deviation between flight at a selected cruising altitude level and flight at an altitude level initially planned by the flight plan, where the selected altitude level is lower than the altitude level initially planned, and to determine a climb limit point from the selected cruising altitude level as a function of the fuel consumption deviation and the minimum fuel reserve objective, where the climb limit point represents the last climb point respecting the minimum fuel reserve to destination objective; and interface circuitry to provide the climb limit point and anticipative information concerning the climb limit point.

Abstract: A method of joining a first component to a second component, the method comprising preparing the first component by forming an array of elongate projections on a bond surface of the component, each projection having a centerline, a tip, and a base. The centerline at the tip of each projection is oriented at an angle with respect to the normal to the bond surface at its base, and the angular orientation of the tip centerlines varies across the array of projections. Next, the first component and a flexible layer are brought together so as to embed the projections in the flexible layer before hardening the flexible layer to form the second component. Also, a joint so formed.

Abstract: The present invention relates to a plug/socket arrangement, in particular an electrical and/or optical plug/socket arrangement of an aircraft or spacecraft, which comprises a housing and at least one insert which can be received in the housing. It further comprises a releasable connection means which is adjustable between a locked position, in which the insert and the housing are locked to one another, and an unlocked position, in which the insert and the housing are not locked to one another; and an adjustment member which is adjustable between an inoperative position, in which the adjustment member is not operatively connected to the connection means, and a release position, in which the adjustment member is operatively connected to the connection means for releasing the locked position into the unlocked position of the connection means.

Abstract: A collapsible partition is provided having a collapsed configuration and an installed configuration in which it is arranged to divide a vehicle compartment into two parts. The partition includes, but is not limited to a ducted portion comprising a duct. The duct extends within the partition from a first opening at a first end of the duct to a second opening at a second end of the duct. The duct is arranged to convey a control fluid for controlling the heat transfer between the partition and at least one of the two parts of the vehicle compartment. There is also disclosed a vehicle compartment control arrangement and a method of partitioning a vehicle compartment.

Abstract: An aircraft thermal control system includes a thermal control unit including an internal circuit, an evaporator and a condenser, the evaporator and the condenser being disposed in the internal circuit. The aircraft thermal control system further includes a cooling circuit which is thermally coupled to the evaporator of the thermal control unit, and a heating circuit which is thermally coupled to the condenser of the thermal control unit.

Abstract: The aircraft comprises: a fuel valve; an actuator for controlling the valve; and a tank panel extending between the valve and the actuator. It is arranged in such a manner that the bearing point(s) between the panel and a first one of the members selected from the valve and the actuator, and preferably the actuator, is/are provided by means of the second one of these members.

Abstract: Device for driving at least one wheel of an aircraft landing gear, which includes at least one turbine machine incorporated into the landing gear of the aircraft. Advantageously, the turbine machine is a pneumatic turbine.

Abstract: A lighting device having a plurality of light sources includes several superimposed layers. The superimposed layers include a first and a second electrically conductive layer, which are designed so as to create an alternating electrical field between the layers. The superimposed layers also have an electrically insulating layer between the electrically conductive layers and a luminescent layer between the electrically conductive layers. Electroluminescent material is arranged within the luminescent layer in several adjacent and spatially separated regions, each region forming a light source. As a result, a simulated starry sky may be provided when the lighting device is used with an aircraft interior trim panel.

Abstract: A fuel cell system (10) comprises a fuel cell (14) and an evaporative cooling system (16), which is in thermal contact with the fuel cell (14), in order that heat generated by the fuel cell (14) during operation of the fuel cell (14) is absorbed through evaporation of a cooling medium and is removed from the fuel cell (14). The fuel cell system (10) further comprises a device (22) for sensing the pressure in the evaporative cooling system (16). A control unit (24) is adapted to control the operating temperature of the fuel cell (14) in dependence on signals that are supplied to the control unit (24) from the device (22) for sensing the pressure in the evaporative cooling system (16), in such a way that the cooling medium of the evaporative cooling system (16) is transferred from the liquid to the gaseous state of matter by the heat generated by the fuel cell (14) during operation of the fuel cell (14).

Abstract: An arrangement for receiving a curtain rail for a curtain for partitioning at least two regions in a cabin of a vehicle includes a bottom facing the floor of the cabin, and a top facing the ceiling of the cabin. The bottom is essentially planar and is designed to receive the curtain rail. The top is designed to cover the space between a curtain held in the curtain rail and the ceiling of the cabin of the vehicle. The bottom includes means for the variable-position holding of attachment points to which the curtain rail can be fastened. Consequently the curtain rails can be affixed flexibly and so as to be subsequently changeable within the region of the arrangement, thereby contributing to such arrangements so as to be able to be standardized for a multitude of imaginable cabin layouts of a vehicle, to be able to minimize individual customization work and construction expenditure.

Abstract: An integrated bracket assembly for attachment to a convex outer corner surface of a torsion box of an aerofoil structure, the bracket assembly comprising a bracket strip having a plurality of brackets arranged spaced side by side, and connected by an infill rail integrally formed with the bracket strip, wherein the infill rail has a concave surface for mating with the convex surface of the torsion box. The torsion box may be of a “U-box” construction where a front spar and a rear spar are integrally formed with either an upper or lower torsion box cover to form an omega-shaped unitary component, and the other cover is attached to the omega-shaped component to provide an enclosed volume. The bracket strip may be used for attaching a leading/trailing edge structure of the aerofoil to the torsion box.

Abstract: The present invention relates to a method for predicting the reliability of an aircraft system (S) onboard an aircraft, constituted by a plurality of elements. The operation of the aircraft is constituted by a sequence of cycles, each cycle comprising a flight phase and a ground station phase. The method of reliability prediction allows in particular calculation of the breakdown probability of the aircraft system at each cycle of operation of the aircraft. The present invention can also estimate the rate of operational interruption of this system.

Abstract: An aircraft nacelle includes a wave attenuation panel which limits or prevents the propagation of at least one wave produced during the pumping of the power plant and includes a layer that is in contact with the air flow that can allow passage of the at least one wave, at least one alveolar structure, and a reflective or impermeable layer, wherein the wave attenuation panel is inserted between the air intake and the power plant, and the layer that is in contact with the air flow ensures the continuity of the aerodynamic surfaces that are arranged downstream and upstream and the wave attenuation panel includes inserts that can be inserted between the air intake and the power plant so as not to crush the wave attenuation panel.

Abstract: The invention relates to a method for checking the formation of ice on an aircraft in flight, characterized in that the method comprises: the estimation (S4) in real time of a quantity of ice (SWC) forming on at least one zone of the aircraft according to flight conditions and the comparison (S5) between the estimated quantity of ice (SWC) and a predetermined quantity of ice (SWCmax; SWCTHR).

Abstract: A method of joining a first component to a second component, the method comprising forming an array of projections extending from a bond surface of the first component, the projections having a plurality of different profiles; and embedding the array of projections in the second component formed of a plurality of laminate plies, wherein each projection profile is adapted to best transfer load into a respective one of the laminate plies. The resultant joint is able to transfer load more progressively between the two components leading to improved tensile strength.

Abstract: An aircraft landing gear comprising: a shock-absorbing main leg having a sprung part for attachment to an aircraft and an un-sprung part including a slider and an axle carrying at least one wheel, the wheel having a toothed ring gear; a drive transmission mounted externally on the sprung part, or on the un-sprung part, of the main leg, the drive transmission having at least one motor and a drive pinion for meshing with the toothed ring of the wheel; and an actuator for lifting the drive transmission into and out of driving engagement with the toothed ring and for maintaining the driving engagement as the landing gear deflects during a ground taxiing operation. Also, a method of operating the aircraft landing gear.

Abstract: The invention provides a cure tool 10, the tool having a working face 11 for placing a component 20 to be cured upon, wherein the tool is provided with a channel 12 along a length of the working face of the tool. The tool may be further provided with an inflatable member 15 in a length of the channel. The invention also provides a method for curing a component, a component that has been cured by the method and an aircraft comprising one or more components that have been cured by the method.