Abstract: A pump arrangement for providing a saturated or subcooled liquid includes a tank for saturated liquid, a heat exchanger for cooling the saturated liquid, a pump, an expansion valve, and an output for feeding saturated or subcooled liquid to a consumer. A tank outlet is in fluid communication with a liquid inlet of the heat exchanger, such that saturated liquid stored inside the tank can flow into the heat exchanger designed to sub-cool the saturated liquid. A liquid outlet of the heat exchanger is in fluid communication with a pump inlet. The expansion valve outlet is in fluid communication with a coolant inlet of the heat exchanger. An expansion valve inlet is arranged for receiving and expanding a fraction of liquid flowing through the pump arrangement and routing it into the coolant input to at least partially evaporate and receive evaporation enthalpy of the liquid to be subcooled.

Abstract: A wing tip device for fixing to the outboard end of a wing, the wing defining a wing plane, the wing tip device comprising: an upper wing-like element projecting upwardly with respect to the wing plane and having a trailing edge; and a lower wing-like element fixed with respect to the upper wing-like element and having a root chord and a trailing edge, the lower wing-like element root chord intersecting with the upper wing-like element, and the lower wing-like element projecting downwardly from the intersection, wherein the upper wing-like element is larger than the lower wing-like element and the trailing edge of the lower wing-like element is adjacent the trailing edge of the upper wing-like element at the intersection, and wherein an included angle between the upper and lower wing-like elements at the intersection is less than, or equal to, 160 degrees.

Abstract: A wing leading-edge device is disclosed having a slat body having a front side with a forward skin and a back side with a rearward skin, and at least a drive arrangement having at least one lug and a slat track, wherein the back side extends between an upper spanwise edge of the forward skin and a lower spanwise edge of the forward skin. The back side is defined by a continuously curved profile contour for receiving a fixed leading edge, and the at least one lug is at least partially arranged between the back side and the front side. The slat track is coupled with the first lug. The connection points to the slat body are shifted far forward to improve the load introduction and reduce moments acting on the drive mechanism.

Abstract: A system and a method for evaluating performance of a porous skin of an aircraft including the porous skin, and a boundary layer control system. The performance evaluation system includes a first sensor providing data related to the performance of the porous skin. The performance evaluation system is further configured to clean the porous skin based on the performance of the porous skin determined using the data received from the first sensor in order to ensure that the porous skin operates at its maximum capability.

Abstract: An opening completely arranged in a skin panel of a structural portion of the aircraft is formed in the outer skin of the skin panel, and for each of the skin panels with one of the openings, an associated structural element of an electronic arrangement is separately provided. The structural element is designed and detachably fastened by a frame thereof to the outer skin in the corresponding skin panel on the side of the outer skin opposite the outer surface, such that it seals the corresponding opening such that the skin panel has at least the same pressure-tightness and at least the same strength relative to tension, pressure and shear forces which act in the skin panel in the extension direction of the outer skin as the same skin panel without the corresponding opening.

Abstract: A storage compartment arrangement for a vehicle cabin having a storage compartment, housing, closable storage compartment opening, lower compartment section in the housing, and upper compartment section in the housing. The storage compartment opening extends over the structural heights of both compartment sections. Items of luggage can be placed onto a lower horizontal pivoting edge and pushed into the lower compartment section. An upper horizontal pivoting edge is provided onto which items of luggage can be placed and can be pushed into the upper compartment section. The storage compartment opening has an upper opening edge facing an upper side of the upper compartment section and is adjoined by an auxiliary surface extending over the upper compartment section, is at an angle in a range of 10° to 50° to the separating plane, and, as the distance from the upper delimitation increases, encloses an increasing distance from the separating plane.

Abstract: To reduce vibration of movable airfoil structures, such as rudders, elevators, and ailerons, a spring device, a leaf spring for example, is mounted to an airfoil mounting structure, such as a vertical tail plane, horizontal tail plane or the wings, such that the spring device exerts a force on a cam device, which transforms the spring force into an airfoil torque. The airfoil torque is applied to the airfoil structure and thus reduces a risk of vibration. The cam device is configured to redirect the spring force such that when the airfoil structure is moved in a first direction, torque decreases and when moved in the opposite second direction the torque is zero.

Abstract: An elongate antenna assembly (1) for an aircraft including a structural section (3) and an antenna element (5), wherein the structural section (3) includes an elongate leading edge section (7) extending in a longitudinal direction (13) of the antenna assembly, a first lateral section (9), and a second lateral section (11), wherein the leading edge section (7) is curved such that the leading edge section (7) comprises a convex outer surface (15) extending in the longitudinal direction (13) of the antenna assembly (1) on a convex side (19) of the antenna assembly.

Abstract: A leading-edge arrangement for an aircraft is proposed, comprising a plurality of movable flow bodies, a supply duct, an air transfer duct, and at least one perforated tube. The movable flow bodies are arranged in a consecutive arrangement to form a row with a first end and a second end. The supply duct reaches into an interior of one of the flow bodies at the first end. The air transfer duct connects to the supply duct and extends at least through the interior of the respective flow body in the direction towards the second end. The at least one perforated tube is arranged inside at least one of the flow bodies that directly follows on. The at least one perforated tube is in fluid communication with the transfer duct. The transfer duct is configured to transfer air from the supply duct into the at least one perforated tube.

Abstract: A wing for an aircraft, including a main wing, and a leading edge high lift assembly including a high lift body, and a connection assembly connecting the high lift body to the main wing such that the high lift body is movable relative to the main wing between a stowed position and a deployed position. The connection assembly includes at least one rotation element mounted to the high lift body and mounted to the main wing rotatably about an axis of rotation. The high lift body includes a rigid portion and a flexible skin portion. The rigid portion is mounted to the rotation element. The flexible skin portion is connected to a leading edge portion of an upper skin panel of the main wing and is connected to the rigid portion of the high lift body The flexible skin portion is configured to be deformed between a stowed deformation state and a deployed deformation state, when the high lift body is moved between the stowed position and the deployed position.

Abstract: A method for producing a composite component including a bottom layer, cover layer and honeycomb structure, including applying the honeycomb structure to the bottom layer wherein honeycomb chambers are formed. Honeycomb chambers are filled in a reinforcement region with a granular material and granular material is removed from other honeycomb chambers wherein each honeycomb chamber is filled up to a granular-material filling height and honeycomb chambers outside the reinforcement region are free of granular material. The cover layer is applied to the honeycomb structure wherein the honeycomb chambers are closed. The composite component is heated so the granular material in the honeycomb chambers expands to fill it with granular material and the cover layer, the bottom layer, the honeycomb structure and the expanded granular material harden, the density of the expanded granular material in the honeycomb chambers filled with granular material being dependent on the granular-material filling height.

Abstract: A closing aid for a luggage compartment flap is described, which closing aid comprises an actuating element, a movement element and a connecting element. The actuating element is integrated in a locking mechanism of the luggage compartment flap. The connecting element connects the actuating element to the movement element and transmits a movement of the actuating element to the movement element such that the luggage compartment flap fastened to the movement element is moved at least part of the way from an open position to a closed position. A luggage compartment and a vehicle having a closing aid of this type are also described.

Abstract: Leakage detection for pressurized fuel tanks. To provide facilitated leakage detection, a leakage detection device for pressurized fuel tanks for storing a pressurized fuel includes a fuel-sensing tracer and a light-wave conducting component. The fuel sensing tracer is configured to alter its optical properties in the presence of a predetermined fuel. The light-wave conducting component is in optical contact with the fuel sensing tracer. Light travelling within the light-wave conducting component is modifiable by altered optical properties of the fuel sensing tracer such that modified light is indicative of the presence of fuel at the location of the fuel sensing tracer.

Abstract: A fastening apparatus and fastening arrangement for fastening a cabin interior component, aircraft cabin and aircraft. To improve installation time and maintenance time, a modular fastening apparatus makes the decoupled rotational attachment of cabin interior components to the attachment structure possible, which attachment structure is in turn supported by the primary structure of the aircraft. The cabin interior component, for example a luggage bin, can be fastened simply by the fastening apparatus. The fastening apparatus includes an inner sleeve which can be plugged over a predefined fastening tube. The fastening apparatus can compensate for tolerances between the attachment structure and the cabin interior component and can prevent transmission of undesired forces and torques.

Abstract: A wing for an aircraft is disclosed having a fixed wing, a foldable wing tip portion mounted to the fixed wing via a hinge rotatable about a hinge axis between an extended position and a folded position, and an actuation unit for actuating the foldable wing tip portion for movement about the hinge axis. The wing includes a brake unit for securing the foldable wing tip portion in the folded position, and the brake unit is formed separately from the actuation unit.

Abstract: A wing for an aircraft is disclosed including a main wing, a slat, and a connection assembly movable connecting the slat to the main wing. The connection assembly includes an elongate slat track, wherein the front end of the slat track is mounted to the slat, wherein the rear end and the intermediate portion of the slat track are mounted to the main wing by a roller bearing including a guide rail mounted to the main wing and a first roller unit mounted to the rear end of the slat track and engaging the guide rail. The roller bearing includes a second roller unit mounted to the main wing and engaging an engagement surface at the intermediate portion of the slat track.

Abstract: A fluid transport device includes a conduit unit having a wall for separating an inside from an outside of the conduit unit. The device also includes an energy supply unit coupled to the conduit unit and configured to provide electrical energy based on a temperature gradient between the inside and the outside of the conduit unit. The device also includes a monitoring unit configured to monitor a state of the conduit unit and to generate data representative for the state of the conduit unit. The energy supply unit supplies the electrical energy to the monitoring unit, thereby enabling the monitoring unit to monitor the state of the conduit unit. A method for manufacturing a fluid transport device is also described.

Abstract: An actuation unit for actuating a foldable wing tip portion of a wing for an aircraft is disclosed including a motor configured to be mounted to a fixed wing for an aircraft, a drive pinion driven rotationally by the motor, a first rack configured to be mounted to the fixed wing, a second rack configured to be mounted to the foldable wing tip portion, a third rack configured to be mounted to the fixed wing movably along a defined first movement path and drivingly engaged by the drive pinion, and a transfer pinion mounted to the third rack rotatably about an axis of rotation extending perpendicular to the first movement path.

Abstract: A mold assembly for manufacturing a composite part with a stiffener, the mold assembly includes a bottom mold configured to form a first surface of the composite part, wherein the bottom mold has at least one elongated recess configured to form a stiffener in the composite part; a feeder unit having a shape corresponding to the at least one elongated recess, wherein the feeder unit is configured to fit at least partially into the at least one elongated recess; and a top mold configured to form a second surface of the composite part opposite to the first surface. Also a method of manufacturing a composite part using such a mold assembly, which includes draping a flat laminate over the bottom mold and pushing portions of the laminate into the at least one elongated recess.

Abstract: A cooling system containing a two-phase refrigerant that comprises a condenser, an evaporator and a conveying device. The evaporator is integrated in a heat source or thermally coupled thereto. Gaseous refrigerant from the evaporator is expanded in an expander, converted into mechanical energy and used to drive a generator for generation of electricity. Furthermore, an aircraft comprising a cooling system, wherein an electrical drive is supplied with electricity from a fuel cell, cooled using the cooling system, and the generator of the cooling system.