Abstract: A network node of a wireless communications network is provided in a means of transportation, for an aircraft, for ascertaining sources of interference, to a system with such a network node, to an associated method for ascertaining sources of interference of a wireless communications network provided in a means of transportation, for the aircraft, and to a computer program for executing the method. The network node includes an interference-power-ascertaining component, for ascertaining an interference power of an interfering radiation emitted from a source of interference, and a transmitting component for wireless or wirebound transmission of the ascertained interference power to a control device for determining at least one of a direction of the interfering radiation and a distance of the source of interference, including the position of the source of interference, on the basis of the ascertained interference power.

Abstract: Pultrusion methods and apparatus for manufacturing a profiled preform or FRP-component with cross-sectional segments that extend angularly to one another from a plurality of semifinished products in a quasi-continuous process, where: at least one multilayer semifinished product arrangement [of a multilayer semifinished product arrangement] is dispensed from a dispenser unit in order to manufacture the preform, with the multilayer semifinished product arrangement dispensed from the dispenser unit being fed to the forming device and including a combination of several webs of semifinished reinforcement fiber layers and at least one resin film; the semifinished product arrangement is guided through a forming device and at least one cross-sectional segment of the semifinished product arrangement is angled in order to form an angle profile, with the semifinished product arrangement being compressed in a pressing device, optionally after a hardening process, and with a longitudinal section of the preform or the comp

Abstract: A ceiling panel is configured for attaching a curtain in a cabin of a transportation device with an attachment unit, a mounting unit, and a curtain attachment unit. The ceiling panel is configured to integrate the attachment unit, the attachment unit is configured to attach the mounting unit to the ceiling panel, the mounting unit is configured to attach the curtain attachment unit, and the curtain attachment unit is configured to support the curtain.

Abstract: A cladding apparatus is provided for the interior of an aircraft that includes, but is not limited to at least one two-dimensional fabric sheet, at least one guide device, and at least one tensioning element. The guide device is configured to be attached in the interior along a direction of extension of the interior, and slidably guide the fabric sheet at least in a first section of the interior along the direction of extension. The tensioning element is, furthermore, configured to be attached in the interior, and by producing a tensile force that acts on the front edge and/or the rear edge of the fabric sheet to stretch taut the fabric sheet along the direction of extension of the interior.

Abstract: A fault-tolerant actuating system with at least one flap, adjustable on a respective wing of an aircraft, and with a control and monitoring device, includes: drive devices that are functionally connected to the control and monitoring device, with one of these drive devices in each case being associated with a flap, where each flap in each case is associated with a drive device, in each case including: two drive motors, two brake mechanisms, where each drive motor is associated with a brake mechanism for stopping rotation of the output of the respective drive motor, a differential that couples the outputs of the aforesaid to the aforesaid in a summing manner, an output shaft for coupling the output of the differential to drive connections, and a differential lock that is functionally connected to the control and monitoring device, which differential lock is coupled to the control and monitoring device in this manner, where each of the brake mechanisms as well as the differential lock can be operated by way of

Abstract: A fire fighting system for extinguishing a fire, which has a fuel cell for producing a nitrogen-enriched cathode exhaust air. The fuel cell is supplied with air and a fuel. Within the fuel cell, the air is then reduced to a determined oxygen content. The exhaust air is supplied to the fire source.

Abstract: A locking apparatus for an object that is lockable on a rail is provided such that the object may be undone in a single manual operating step. The apparatus may be used in a passenger aircraft in which it is necessary to slide seats or other built-in devices. The apparatus includes at least one first base body, at least one first locking body, and at least one first operating element. The at least one first base body is designed to be placed on top of the rail. The at least one first locking body is movably held to the at least one first base body, and is shaped to be placed into the rail. The at least one first operating element is connected to the at least one first locking body for moving the at least one first locking body in the direction of the interior of the rail.

Abstract: A cabin equipment component connection system for an aircraft comprises a plurality of connecting elements, which are adapted to be connected to a cabin equipment component in order to connect the cabin equipment component to a higher-level system of the aircraft. In at least one zone of the cabin equipment component connection system, a number and an arrangement of the connecting elements in the cabin of the aircraft are selected such that cabin equipment components that are provided in a first number and/or a first arrangement in the cabin of the aircraft are connectable to the connecting elements of the cabin equipment component connection system, and that cabin equipment components that are provided in a second number and/or a second arrangement in the cabin of the aircraft are connectable to the connecting elements of the cabin equipment component connection system.

Abstract: An interface system for use in an aircraft galley includes a first connection element. The first connection element can be connected via a first appliance connection apparatus to an internal electrical system, an internal fresh water supply system, and an internal wastewater disposal system of a first galley appliance, and can be connected via a second appliance connection apparatus to an internal electrical system, an internal fresh water supply system, and an internal wastewater disposal system of a second galley appliance. Further, the first connection element can be connected via an aircraft galley connection apparatus to a complementary aircraft galley connection apparatus of a second connection element of the interface system. The second connection element can be fixed in a compartment in the aircraft galley, so as to connect the first connection element to an electrical system, a freshwater supply system and a wastewater disposal system.

Abstract: A force measuring system is provided for measuring forces on a rotating body that includes, but is not limited to a force measuring device, which is mounted on the rotating body, as well as a position sensing unit for detecting the rotation of the rotating body and an evaluation unit, which is connected to the force measuring device and the position sensing unit. The evaluation unit is configured for recording a force value measured by the force measuring device depending on the detected position of the rotating body. The force measuring system allows the forces and torques on a rotating body to be determined precisely and as flexibly as possible, independently of the prevailing rotation speed of the rotating body.

Abstract: An engine simulator for wind tunnel models exhibits a turbine with an inlet for a pressurized fluid and an outlet for a relieved fluid, a flow-type body arranged downstream from the turbine, a jacket that at least partially envelops the flow-type body with the formation of a gap, and at least two electrodes. A downstream end of the flow-type body is provided with a heater coating comprised of a matrix material that contains a conductivity additive and is connected with the electrodes for applying an electrical voltage. This may make it possible to prevent ice formation on the trailing edge of the flow-type body.

Abstract: The invention relates to a method for joining cured stringers to at least one structural component of an aircraft or spacecraft, including placing the stringers onto the at least one structural component, depositing and pressing respective vacuum film strips such that each strip is attached to a pair of stringers and present between the pair of stringers with the use of vacuum sealing means in such a manner that a continuous vacuum arrangement, comprising the covering vacuum films and the vacuum film strips, is formed, and pressurized joining of the stringers to the at least one structural component by means of the continuous vacuum arrangement formed.

Abstract: A non-destructive determination of material characteristics of an aircraft component is provided. To provide a simple determination of material characteristics, which can be implemented economically, it is provided to make available image data of a layer, which can be detected from outside using electromagnetic radiation, of a workpiece to be examined; to detect first areas having a first pixel characteristic using the image data; and to detect second areas having a second pixel characteristic using the image data; the first pixel characteristic being associated with a fiber inlay of a fiber composite layer; and the second pixel characteristic being associated with an at least part-crystalline thermoplastic polymer of the fiber composite layer, which thermoplastic polymer is in a crystalline state; and to determine a relationship of the first areas to the second areas.

Abstract: A system is provided for the detection of deposits in a fluid line that includes, but is not limited to a measuring body, and ultrasonic transducer and an ultrasonic receiver and at least one evaluation unit connected to the ultrasonic transducer and the ultrasonic receiver. The ultrasonic transducer transmits an ultrasonic signal and the ultrasonic receiver receives response signals generated by reflections in the fluid line. From known geometric changes in shape of the fluid line, resulting response signals are finally filtered out of the response signal sequence and from the remaining response signals relating to the deposits, the distances can be calculated between the ultrasonic transducer and the deposits.

Abstract: The invention pertains to a relief valve (10) for being arranged on an opening (10) of a fuselage shell of an aircraft, wherein the opening (10) has a front opening edge (9a) and a rear opening edge (9a), and wherein the relief valve (10) features: a cover (13) that is arranged on the fuselage shell by means of an opening and closing device in order to open and close the opening (10) of the fuselage shell, and a prestressing device for prestressing the cover (13) into an initial position, wherein a guide plate (23) is arranged on the cover (13) by means of a mounting device (20), wherein the guide plate is spaced apart from the cover (13) and extends along the cover (13), and wherein the invention furthermore pertains to a fuselage part with such a relief valve (10) for being installed into an aircraft fuselage with a fuselage shell and a plurality of fuselage frames arranged on the inside of the fuselage shell, as well as to an aircraft fuselage with such a fuselage part.

Abstract: An aircraft area comprises a door, a door aisle and a main aisle. A storage cabinet for emergency equipment objects is disposed adjacent to the door aisle and/or the main aisle, and has an access point that is reachable from the door aisle and/or the main aisle.

Abstract: A cabin attendant seat comprising a carrier element which comprises a backrest section and a base section that carries said backrest section. A seat element is fastened to the carrier element. At least one first stowage compartment is integrated into said carrier element. A section of a rear wall of the carrier element is inclined, at least along a section of the stowage compartment integrated into said carrier element, in such a way that a cross-sectional area of said carrier element increases in the direction of the base section of said carrier element.

Abstract: An aircraft door includes an outer skin configured as a panel structure; and a rear body structure configured as an integral cast structure and operatively connected to the panel structure so as to provide rigidity.

Abstract: A device for boundary layer suction on the outer skin of an aircraft, on which outer skin a surface where drawing off by suction can take place comprising openings is connected to a suction source by way of at least one suction line, wherein the surface where drawing off by suction can take place is formed by at least one panel-shaped composite component that comprises an extruded profile, made of light metal, as a base body, which extruded profile comprises several suction channels that are open towards the outer skin, onto which base body, for the purpose of forming the outer skin, a micro-perforated metal cover sheet has been applied in the region of the surface where drawing off by suction can take place.

Abstract: Disclosed is a reinforcing material for the local reinforcement of a component formed with a composite material, in particular in areas of force introduction and/or connecting areas. The reinforcing material is formed by a metallic sheet-like formation, the metallic sheet-like formation having a surface with increased roughness to improve adhesion and a coating applied to the surface to provide a seal and improve the bond with the composite material. As a result of the presence of a coating on the metallic sheet-like formation, once it has been rolled up on supply rolls, said sheet-like formation can be drawn off from the supply rolls and at the same time processed in an automated manner by means of known computer-controlled laying devices with CRP prepreg materials in web form by laying layer by layer to produce components, in particular of large format, for aircraft.