Abstract: An aircraft fuel tank arrangement for the relief of a pressure differential between the interior of the aircraft fuel tank and the ambient atmosphere is provided. The aircraft fuel tank arrangement comprises a removable cartridge received within a cartridge-receiving body located at least partially in the fuel tank, said cartridge comprising a first burstable member operable to rupture in the presence of a pressure differential between the interior of the aircraft fuel tank and the ambient atmosphere which is greater than a predetermined pressure differential.

Abstract: A morphing aerofoil comprising: a leading edge; a trailing edge; and upper and lower surfaces extending between the leading and trailing edges. An upper thermal actuation member is provided proximate the upper surface; and a lower thermal actuation member is provided proximate the lower surface opposite the upper thermal actuator. The upper and lower thermal actuation members have different thermal expansion coefficients and are positioned such that they cause the trailing edge to deflect when they expand or contract by different amounts in response to a change in ambient temperature, thereby changing a camber of the aerofoil.

Abstract: A method and a device determines an air mass flow flowing through a ram air channel having disposed therein a feed device adapted in a first operating state of the ram air channel to feed air through the ram air channel and further adapted in a second operating state of the ram air channel to be set in rotation by an air mass flow flowing through the ram air channel. The method includes the step of detecting an actual operational characteristic of the feed device that is characteristic of the air mass flow flowing through the ram air channel in the second operating state of the ram air channel as well as the step of determining the air mass flow flowing through the ram air channel on the basis of the detected actual operational characteristic of the feed device.

Abstract: A linear actuator has a housing, a piston slideable within the housing along a slide axis, a first shaft rotatable about a first axis substantially perpendicular to the slide axis, a second shaft rotatable about a second axis parallel to the slide axis, in which the second shaft and the piston are engaged to convert rotational motion of the second shaft into linear motion of the piston, and in which the first shaft and the second shaft are engaged by a ball-worm gear.

Abstract: A hydraulic drive for an aircraft includes: a gear, a first hydraulic pump and a second hydraulic pump, wherein the gear is installed in a gear housing and wherein the first hydraulic pump and the second hydraulic pump in each case are installed in a pump housing that is affixed to the gear housing, or the two together are installed in a pump housing that is affixed to the gear housing; a hydraulic supply device including a first and a second hydraulic system for operating actuators of the aircraft; and a monitoring and drive device, with the hydraulic supply device including a first hydraulic drive for coupling the latter to a first engine, and a second hydraulic drive for coupling the latter to a second engine, wherein each hydraulic drive includes: a gear drive shaft for coupling the respective hydraulic drive to an engine output shaft of the respective associated engine; two hydraulic pumps that are coupled to a gear output shaft, in each case with a connection device for connecting the hydraulic pump to

Abstract: A decompression arrangement includes first and second cabin lining elements each with an edge region, the edge region of the second being arranged at a smaller distance from an aircraft outer skin than the edge region of the first, an air discharge opening arranged between the first edge region and second edge region and which is adapted to discharge air from an inner region of the cabin delimited by the cabin lining elements into a region of the aircraft lying between the cabin lining elements and the aircraft outer skin, and a decompression element integrated in the second cabin lining element having a flap pivotable about an axis from a closed position, in which it closes a pressure equalizing opening formed in the decompression element, into a first open position, in which it opens the pressure equalizing opening if a first predetermined differential pressure acts on the decompression element.

Abstract: A method, apparatus and computer program product is disclosed for determining the strain induced at a selected point in a stiffened panel structure in response to a load, taking into account one or more out of plane (OOP) effects.

Abstract: A system for producing a fibre-reinforced composite module, such as a panel module, having an integrated stiffening structure for an aircraft or spacecraft includes a form core assembly station for assembling a plurality of form cores covered with reinforcing fibre layers to constitute at least one stiffening element of the integrated stiffening structure, a form core placement station which receives assembled form cores from the assembly station for placing or depositing the assembled form cores in or on a moulding tool, and a turning station for rotating or inverting the assembled form cores. The turning station is configured to convey or transport the assembled form cores from the assembly station to the placement station. The turning station defines a path which is configured to rotate or invert the assembled form cores as they are conveyed or moved to the placement station.

Abstract: A slat support assembly is disclosed. It comprises a slat support arm (3) having a plurality of bearing surfaces (28a, 28b, 29a, 29b) extending along its length, the slat (2) support arm being movable to deploy a slat attached to one end (4) of said slat support arm from a leading edge of an aircraft wing (1), and a plurality of bearings (27a, 27b, 31a, 31b) mountable within the wing, each bearing being in rolling contact with an associated bearing surface to support the slat support arm and guide it during deployment and retraction of the slat. At least some of the bearing surfaces and associated bearings are configured so that each bearing counteracts load applied to the slat support arm in more than one direction.

Abstract: A module in the form of a pallet or a closed container includes a grouping together of the electrical devices in an avionics bay, in which the electrical devices are interconnected and attached so as to facilitate the mounting and thus limit the time it takes to mount the electrical devices in the avionics bay.

Abstract: A lightning and corrosion protection arrangement for a joint between an outer metallic part (11) and an aircraft structural component (13) completely or partially made of CFRP by means of a row of metallic rivets (15), that comprise inner and outer metallic layers (21, 25) and an intermediate dielectric layer (23), the inner metallic layer (21) in contact with said structural component (13) being thinner and bigger than the outer metallic layer (21) in contact with the metallic part (11), the intermediate dielectric layer (23) extending in an area bigger than the area of the foot (12) of the metallic part (11) by a predetermined minimum linear distance D1 between its edges, the outer metallic layer (25) extending in an area bigger than the area of the intermediate dielectric layer (23) by a predetermined minimum linear distance D2 between its edges.

Abstract: The system supplies oxygen for a flight crew member of an aircraft and has an oxygen source, an oxygen mask, and a circuit connecting the oxygen source to the oxygen mask. The system is integrated into an aircraft seat, which has at least one foot bearing a sitting surface and a back. The oxygen source may be a cylinder of gaseous oxygen under pressure. The oxygen mask can be housed in a compartment inside the sitting surface of the seat.

Abstract: An aircraft landing gear arrangement comprises a nose landing gear assembly and at least one main landing gear assembly. The nose landing gear assembly has a nose landing gear wheel with a high energy brake apparatus therein. The main landing gear assembly has a main landing gear wheel with a high energy brake apparatus therein and a main landing gear wheel with a motor therein. The motor is used for driving the main landing wheel during taxiing of the aircraft.

Abstract: A monument is provided for a cabin of transportation, for example a lavatory monument, a kitchen or galley monument or a storage monument to be fitted in an aircraft, in a helicopter, in a ship or boat, in a train or in a caravan or trailer. A mounting system is also provided with one or several monuments and transportation with a monument installed therein. The monument for the cabin of the transportation includes, but is not limited to a flexible attachment element for attaching the monument to the cabin of the transportation means. The flexible attachment element is designed in such a manner that attachment of the monument can take place in a region of relative positions of the monument relative to the cabin of the transportation.

Abstract: An aircraft includes a heat exchanger between a first fluid that flows into the narrow pipes of the exchanger and that is able to contain solid elements that can melt, and, a second fluid to be cooled. The heat exchanger includes a device for preheating the first fluid upstream from the pipes of the exchanger, a number of pipes arranged in at least one plane that intersects the direction of flow of the first fluid, whereby the spacing between two adjacent pipes is suitable for retaining the solid elements of large dimensions and for allowing them to pass only when they have melted at least partially.

Abstract: The invention relates to an aircraft protection device for protecting potentially exposed aircraft structures from direct impacts and a method of protecting an exposed edge of an aircraft component. The method includes the steps of winding filament around a foam core to create an impact protection device. A portion of the filament winding and foam core is removed from the impact protection device to create a receiving section whereby the receiving section is configured to correspond to and receive the exposed edge of the aircraft component. The impact protection device is secured to the exposed edge of the aircraft component such that the exposed edge is received in the receiving portion of the impact protection device.

Abstract: A system for flushing a vacuum toilet in an aircraft, with a bowl drain for removing toilet waste water from a bowl, a drain line, a bypass flow line for feeding-in air, a drainage valve and a waste water line. The bowl drain and the bypass flow line are connectable to the drain line, and the drainage valve on the input side is connectable to the drain line, and on the output side is connectable to a waste water line. In an implementation of the vacuum toilet as a vacuum urinal, the system may provide either water flushing or waterless flushing.

Abstract: The present invention relates to a coated object comprising at least (a) a metal layer, (b) a coupling layer, (c) an inner polymer layer, and (d) a substrate surface, wherein the coupling layer (b) is arranged between layers (a) and (c) and connects said layers, the polymer layer (c) being arranged on the substrate surface (d) and the sum of the diameters of layers (a) and (b) being between 5 nm and 500 nm. The invention also relates to methods and devices for producing the object.

Abstract: A conduit protection system, comprising: a conduit for carrying a fluid; a sealed vessel surrounding the conduit along a protected zone of the conduit; and a valve moveable between a first position for obstructing fluid flow through the protected zone of the conduit and a second position for enabling fluid flow through the protected zone of the conduit, wherein the valve is biased to the first position, and wherein the valve is fluidically coupled to the sealed vessel such that a positive pressure within the sealed vessel is operable to move the valve to the second position against the bias. Also, a method for protecting a fluid carrying conduit.

Abstract: A device for revising a low-altitude flight phase of a flight path of an aircraft includes an input unit configured to allow an operator to input parameters to define an intermediate flight section (Si) which has to be inserted into a low-altitude flight phase, and a processing unit configured to calculate a profile relating to the intermediate flight section (Si) using input parameters, and to automatically insert this profile into the flight phase between a first upstream part (P1) and a second downstream part (P2) so as to establish a revised flight phase (PR).