Abstract: In a method for operating a cooling system for cooling food on board an aircraft, a partial amount of refrigerant, which, in the rest state, is stored in a receiving space of a refrigerant container in the gaseous state of aggregation, is discharged from the receiving space of the refrigerant container into a cooling circuit of the cooling system. The partial amount of the refrigerant is directed into a liquefier arranged in the cooling circuit and converted to the liquid state of aggregation. The partial amount of the refrigerant liquefied by the liquefier is directed through a heat exchanger arranged in the receiving space of the refrigerant container. The remaining refrigerant, stored in the receiving space of the refrigerant container in the gaseous state of aggregation, is converted to the liquid state of aggregation by heat energy transfer to the partial amount of the refrigerant flowing through the heat exchanger.

Abstract: An aircraft structure, for example a wing, includes a section of skin, for example a lower wing panel, the panel defining an external (lower) surface that in use is on the exterior of the aircraft and an internal (upper) surface opposite the external surface, and a duct comprising a section of duct for transporting cooling fluid, for example air, between the internal and external surfaces of the panel from a first location in the panel to a second location that is spaced apart from the first location in a direction substantially parallel to the external surface of the panel. The cooling air cools an electronic hydrostatic actuator (EHA 4b) in the wing 2.

Abstract: The invention is based on a partition wall in an aircraft, wherein the partition wall comprises a support element and a tension-mounted material. According to the invention, the support element is composed of individually formed system components, and the tension-mounted material is supported by the support element such that an area-shaped partition wall is created in the aircraft.

Abstract: A defect recognition procedure in prepreg materials (1) draws a first transversal cross line (4b) at the beginning boundary (3b) of a defective area (2) in a prepreg material (1). A second transversal cross line (4e) at the end boundary (3e) of a defective area (2) is drawn as well. The cross lines (4b, 4e) form an angle (?) with respect to the prepreg material (1) motion direction (5). Each transversal cross line (4b, 4e) delimiting the beginning and the end of a defective area (2) has identification codes (Bi, Ei).

Abstract: The invention relates to a method for producing a fiber composite workpiece. In the method according to the invention, cross-linking silicone is used with the aid of a volatile diluent for infiltrating individual mats of a mat composite. A further object of the present invention is a device for performing the method according to the invention.

Abstract: An acoustic treatment panel includes an acoustically resistive layer that defines a surface of an aircraft that is in contact with an aerodynamic stream, a reflective layer (50) between which are arranged at least one alveolar structure (52) with a number of cells dedicated to the acoustic treatment, and de-icing cavities (58) in which hot air circulates in contact with the acoustically resistive layer to ensure a frost treatment, characterized in that it includes holes for supplying de-icing cavities (58) with hot air and in that the capacity to treat the frost is adjusted along the zones by modifying the open surface ratio that results from the holes.

Abstract: A decompression assembly (10; 10?) for an aircraft comprises a first cabin lining element (12; 12?) having a boundary area (14; 14?) and a second cabin lining element (20; 20?) having a boundary area (22; 22?), wherein the boundary area (22; 22?) of the second cabin lining element (20; 20?) is disposed at a smaller distance from an aircraft outer skin (24; 24?) than the boundary area (14; 14?) of the first cabin lining element (12; 12?). An air discharge opening (28; 28?) is disposed between the boundary area (14; 14?) of the first cabin lining element (12; 12?) and the boundary area (22; 22?) of the second cabin lining element (20; 20?) for discharging air from a cabin (18; 18?) of the aircraft into an area (30; 30?) of the aircraft located between the cabin lining elements (12, 20; 12?, 20?) and the aircraft outer skin (24; 24?).

Abstract: An aft aerodynamic fairing for a pylon for attaching an aircraft propelling assembly, including a caisson structure, a heat-shield floor, as well as a support structure for this floor comprising linking parts arranged to link two side edges of this floor to the caisson structure. The linking parts of each side edge of the floor are configured so as to allow travelling motion of the side edge relative to the caisson structure in a corresponding direction included in a plane orthogonal to a longitudinal direction of the fairing. The linking parts form a sliding link between the floor and the caisson structure, reducing the stresses induced by the deformations of these elements in use.

Abstract: A method of manufacturing “T” shaped stringers for an aircraft whereby the “T” shaped stringers have a stringer web and a stringer foot, the method comprising: a first step of hot-forming a carbon fiber laminate in order to achieve semi-stringers with an “L” shaped cross-section, a second step of placing together two hot-formed “L” shaped semi-stringers in order to form a “T” shaped stringer, a third step of co-bonding the resulting “T” shaped stringer on a cured skin with an adhesive line between them, and a fourth step of curing the obtained “T” shaped stringer inside a vacuum bag using invar alloy angles as curing tools. The invar alloy angles are cut at a radius area eliminating a part of the invar alloy angles covering the stringer foot in order to define an invar alloy piece having no foot.

Abstract: An aircraft structure is provided with load-bearing hollow structural elements that form an aircraft fuselage. The cavities in the structural elements are designed as air ducts for an air conditioning system of the aircraft. An aircraft is also provided with such an aircraft structure.

Abstract: A wingtip device for a wing is provided. The wingtip device has an inner end and an outer end, and in which the local dihedral of the wingtip device increases or reduces from the inner end to the outer end, with a pressure-side flow surface and a suction-side flow surface. At least two ancillary wing sections are arranged on the wingtip device, projecting in each case from the flow surface of the wingtip device. The ancillary wing sections in each case form an interface with the surface of the wingtip device; which interfaces are located spaced apart from one another. A wing with such a wingtip device is also provided.

Abstract: The invention relates to a system (10) for configuring an aircraft passenger cabin, said system comprising a first database (12) that stores cabin equipment component data pertaining to cabin equipment components selected for and included in a configuration of the aircraft passenger cabin. In addition, said system (10) comprises a second database (14) that stores configuration rules pertaining to the configuration of the aircraft passenger cabin. Finally, the system (10) comprises a unit (16) for generating a documentation, configured in such a way that documentation of the configured aircraft passenger cabin is generated on the basis of at least one user-defined configuration parameter, on the basis of the cabin equipment component data stored in the first database (12), and on the basis of the configuration rules stored in the second database (14).

Abstract: A connection arrangement for at least two abutting components to be firmly connected to one another, includes a self-piercing rivet having a rivet head for punching of a hole and subsequent riveting of the components, wherein a washer is allocated to the self-piercing rivet at the distal end region opposite to the rivet head, with the washer including a frontal area for the insertion of a circular indentation to create a firm compression connection between a hole in the washer and the distal end region of the self-piercing rivet.

Abstract: The invention pertains to a composite panel with a first cover layer, a second cover layer and a first core layer that is arranged between the first cover layer and the second cover layer and features a plurality of cells that are separated from one another by walls at least in certain areas, wherein the first cover layer features a draining layer. The inventive composite panel may be distinguished from a composite panel according to the state of the art in that a second core layer with a plurality of cells that are separated from one another by walls at least in certain areas is arranged between the first cover layer and the first core layer.

Abstract: A method of manufacturing in which a robot arm is used to pick up a workpiece which is subsequently scanned by a scanner and positioned relative to a manufacturing system for manufacturing in order to eliminate the use of a bespoke jig.

Abstract: A device for acoustically scaring avian species includes means for emitting an acoustic sequence including the repetition of a combination of at least three categories of different synthetic signals, including warning signals representative of alert noises from birds of prey, interspecies distress signals, and taking-flight signals from various species representing beatings of wings.

Abstract: A force introduction fitting for lightweight constructional components comprises at least one radial force introduction surface, at least one axial force introduction surface, and at least one receiving means for holding the force introduction fitting and for introducing loads into the force introduction fitting. The radial force introduction surface and the axial force introduction surface enclose a hollow space. The radial force introduction surface and the axial force introduction surface form a single-piece component. Such a force introduction fitting can be produced with the use of a selective laser melting method. The force introduction fitting can thus be adjusted in a particularly flexible manner to the load conditions, comprises particularly advantageous materials characteristics and features a lightweight construction.

Abstract: A system for evacuating persons from a vehicle includes a light signal generating device, which is adapted to emit at least one visual light signal that indicates at least one preset escape route for at least one person to be evacuated.

Abstract: The present invention is concerned with a system for the oxygen supply of persons in an aircraft. In order to provide the simplest possible system, which is suitable in particular for a reconfiguration of the seat devices (12), the system has at least one oxygen line, one oxygen feed, and multiple attachment points for oxygen masks (24), the oxygen line extending in the longitudinal direction and the attachment points being connected to the oxygen line. The attachment points are preferably situated linearly and are spaced apart from one another in the longitudinal direction.

Abstract: A drilling machine drills at a multiplicity of target locations on a component. Two robots, calibrated with calibration data, move the component in a 6-D coordinate system. A metrology system ascertains the position of the component relative to the drilling machine. The movement of the robots is effected by commands generated by off-line programming. The component is moved relative to the drilling machine to a target position, ready for drilling, by a closed-loop process in which the differences in position between the expected position (the target position) and the actual position (as viewed by the metrology system) are corrected.