Abstract: A method for manufacturing a structural assembly comprising at least two assembly components interconnected by means of a thermoplastic plastics material, and useful in the field of aviation or space travel. First, a first assembly component and a second assembly component are provided and arranged so as to form an arrangement. Second, the arrangement is subjected to creep forming at a temperature which is selected in such a way that the thermoplastic plastics material melts at least in part during the creep forming so as to connect the first assembly component and the second assembly component. The invention further relates to structural assemblies, in particular for an aircraft or spacecraft, and to an aircraft or spacecraft comprising a structural assembly of this type.

Abstract: A system for detecting radome damage. The system comprises a sensor unit and a processing unit. The sensor unit is configured to continuously register external impacts on a radome. The processing unit is electrically connected to the sensor unit. The processing unit is configured to compare the external impacts registered by the sensor unit with reference data. The processing unit is further formed to determine, based on the comparison, whether damage to the radome has occurred due to one or more events associated with the external impacts. Furthermore, a radome comprising the system, a flying object and a corresponding method are provided.

Abstract: A system for moving loads in an aircraft, comprising a cargo hold floor and at least one roller track comprising a plurality of rollers, defining a plane of movement for the load, arranged one behind the other in the hold floor. At least one guide track is provided in the floor extending parallel to the roller track. At least one transfer vehicle is detachably received in the guide track, movable along the guide track. At least one locking device is configured, in a locking position, to block movements of a load relative to the roller track parallel to the movement plane and perpendicular to the movement plane and, in a release position, to allow relative movements. The locking device is configured to be actuated by a transfer vehicle in the guide track to shift the locking device out of the release position into the locking position, or vice versa.

Abstract: This relates to a method of manufacturing a metallic component by additive layer manufacturing. The method comprises the step of providing a layer of granular metallic material. The layer of the granular metallic material is melted by a laser beam or electron beam which applies a defined scanning strategy, which is defined in such a way that a first region of the layer is melted before a second region of the layer such that during the subsequent solidification, residual stresses emerge in the first and the second region. These residual stresses act as integrated crack stoppers of the metallic component.

Abstract: A tyre monitoring device configured to be mounted on a wheel is described. The device includes a pressure sensor for sensing an inflation pressure of a tyre on the wheel; a wireless communication interface configured to receive data indicative of a command to indicate tyre pressure; a storage storing a predetermined pressure value; an indicator configured to provide a first indication and a second indication, wherein the first indication is different from the second indication; and a processing system configured to operate the indicator to provide the first indication or the second indication responsive to receipt of the command to indicate tyre pressure, and based at least in part on the inflation pressure and the predetermined pressure value.

Abstract: To reduce complexity, solve tolerance problems and increase reliability and customer satisfaction, a door switch arrangement for a lavatory of an aircraft is provided, wherein, to generate signals which indicate a current status of the lavatory door, the door switch arrangement uses a sensor device with contactlessly operating reed sensors.

Abstract: The present invention provides an arrangement for passing a line in a load-free manner through a pressure frame of a fuselage of an aircraft or spacecraft, including an opening penetrating the pressure frame, through which opening the line is passed, the line being mechanically decoupled from the pressure frame; and a flexible sealing device arranged outside the opening at least in portions, which sealing device is simultaneously operatively connected to the line and the pressure frame for the pressure-tight separation of a first side from a second side of the pressure frame. The present invention also provides a fuselage for an aircraft or spacecraft having an arrangement of this type and an aircraft or spacecraft having an arrangement of this type or having a fuselage of this type.

Abstract: A display device for displaying an activation status of an emergency chute in an aircraft has an optical display device, an acoustic signal device, a sensor for sensing proximity of a person to the display device, and an electronic unit. The electronic unit is configured to operate the optical display device or the acoustic signal device when the detected proximity of a person is less than a predetermined limit distance. The optical display device, the acoustic signal device, the sensor, and the electronic unit form a compact unit that can be integrated into a door panel of an aircraft door.

Abstract: A method for connecting two aircraft components composed of thermoplastic composite material by a rivet. The two aircraft components are arranged, in sections, areally on one another, before bores in the two aircraft components are expanded by a mandrel element such that the bores, after the expansion, form one continuous bore for receiving the rivet. Here, the two aircraft components are locally warmed by the mandrel element such that, during the expansion of the bores, the components are thermoplastically deformed. The mandrel element is inserted through the first bore into the second bore. The rivet is introduced into the continuous bore. A system for carrying out the method is also disclosed.

Abstract: A pressure bulkhead system comprises a pressure bulkhead adapted to be connected to a fuselage of a vehicle to separate a pressurized cabin space of the vehicle from an unpressurized cabin space of the vehicle, and a peripheral pressure frame to sealingly connect the pressure bulkhead to the vehicle fuselage. The peripheral pressure frame comprises an attachment section sealingly attached to an outer rim portion of a first surface of the pressure bulkhead. The first surface, when the pressure bulkhead system is installed in the vehicle, faces the unpressurized cabin space of the vehicle. A flange section is adapted to be sealingly attached to an inner surface of the vehicle fuselage and extends in a direction facing away from the first surface of the pressure bulkhead. A flexible section interconnects the attachment section and the flange section and is flexible to accommodate cabin pressure acting on the pressure bulkhead.

Abstract: An aircraft with a drinking water supply and distribution system including a water storage tank, a consumer equipment, a pressurizer, a pressure reducer and a conduit system connecting the drinking water storage tank to the consumer equipment via the pressurizer and supplying water from the at least one water storage tank to the at least one consumer equipment. The pressurizer pressurizes water in the conduit system with a peak pressure exceeding a supply water pressure threshold. The conduit system includes flexible conduits having a maximum internal diameter of less than 8 mm. The pressure reducer is provided for reducing the pressure of water supplied to the consumer equipment below a consumer water pressure threshold. The supply water pressure threshold exceeds the consumer water pressure threshold.

Abstract: A base module and an aviation computer system having the base module includes a printed circuit board, an integrated power supply and communication connector, a SMARC connector, and an FMC connector. A power supply circuit supplies the SMARC connector and the FMC connector with power from dedicated power supply contacts of the integrated power supply and communication connector, and a communication circuit connects the SMARC connector to dedicated communication contacts of the integrated power supply and communication connector. In addition, signal lines are provided on the printed circuit board in order to connect dedicated input/output contacts of the SMARC connector to corresponding dedicated input/output contacts of the FMC connector.

Abstract: A method for integrating a fuel cell unit into a vehicle structural component, includes determining an available receiving space in an interior structural component of the vehicle, providing two casing parts assembleable to a closed casing, providing a fuel cell having an anode, a cathode and an electrolyte, assembling the casing parts and the fuel cell to form the fuel cell unit, and inserting the fuel cell unit into the receiving space. A casing part is additively manufactured such that the fuel cell unit precisely fits into the receiving space. A casing part includes an exterior fuel inlet and an interior fuel distributor for leading a fuel from the inlet to a fuel outlet couplable with the fuel cell. A casing part includes an exterior oxidant inlet and an interior oxidant distributor for leading an oxidant from the inlet to an oxidant outlet couplable with the fuel cell.

Abstract: A wing for an aircraft, including a main wing, a slat, and a connection assembly for movably connecting the slat to the main wing, such that the slat is movable between a retracted position and at least one extended position. The connection assembly includes a first connection element and a second connection element, both movably mounted to the main wing and mounted to the slat, wherein the second connection element is spaced apart from the first connection element in a wing span direction. The wing further includes a drive unit provided at the main wing and connected to the slat for initiating movement of the slat. An object, to prevent skew cases of the slat, is achieved in that the connection assembly includes a rotatable sync shaft rotatably engaging both the first connection element and the second connection element for sync movement of the first and second connection elements.

Abstract: A system for handling containers in a freight compartment of a vehicle has a stowage device with a frame in which there are formed devices for receiving containers, at least one robot arm, each with a base a handling tool, a guide device mountable on the frame, and a control unit. The robot arm uses the handling tool to receive and move containers to and from the devices. The guide device moves the robot arm along at least one guide axis. On demand, the control unit actuates the robot arm(s) and the guide device such that a container is received from the respective device by the handling tool and is made available at a predetermined transfer position outside the frame, or such that a container is received by the handling tool at the transfer position and inserted into a device.

Abstract: An adapter rail system for mounting objects to a floor rail in a vehicle includes an elongate adapter rail element, an arresting element and a movement rail element. The adapter rail element has a surface contour having regularly consecutively arranged neckings and widenings, which surface contour corresponds to an opening contour of a floor rail, which includes regularly consecutively arranged grid openings, which are penetrated by a slit. The adapter rail element has protrusions extending perpendicular to the plane spanned by the surface contour and are each arranged in the region of a necking. The arresting element has a surface contour corresponding to the opening contour of at least one grid opening. The arresting element is dimensioned to be flush between two adjacent protrusions of the adapter rail element onto the adapter rail element. The movement rail element is connectable with the protrusions of the adapter rail element.

Abstract: A microelectronic module for cleaning a surface is described. The microelectronic module comprises at least one voltage converter for converting a provided first voltage into a higher, lower, or identical second voltage. The module also comprises at least one actuator. The actuator comprises at least one generator for generating an ionic current, an electrical plasma, harmonic components and/or an electrostatic field from the second voltage which is provided by the voltage converter. At least the voltage converter and the actuator are disposed on a thin-film, planar substrate. At least most of at least one object adhering to the surface is removed by the actuator.

Abstract: The disclosure relates to a composite panel member for an airframe of an aircraft or spacecraft, the composite panel member having a laminated or sandwich structure including: a first outer layer extending over a first side of the panel member; a second outer layer extending over a second side of the panel member; a core layer between the first and second outer layers; and at least one support element configured as an electrical conductor and provided within the core layer between the first and second outer layers. In this regard, the at least one support element extends within the core layer substantially parallel to the first and second outer layers.

Abstract: An flow body comprises a curved suction skin having a first perforation, a leading edge and two skin sections extending therefrom, wherein each skin section has an outer end facing away from the leading edge, an interior suction duct having a second perforation and extending through an inside of the curved suction skin in a distance from the leading edge, and two sidewall members, connected to the outer ends, wherein the sidewall members are made of a composite material. The suction skin comprises a profiled contour shape, which determines a pressure distribution over at least one of the two skin sections when air flows over the curved suction skin, wherein the pressure distribution comprises a stagnation point, a suction peak and a subsequent local pressure maximum downstream of the suction peak, wherein the first perforation extends from a stagnation point on the suction skin to the local pressure maximum.

Abstract: A passenger seat system for a transport means has a carrier structure which can be attached, fixedly with respect to a structure, and a seat having a seat frame displaceable and arrestable on the carrier structure, a bottom side lying on the carrier structure, and a top side holding a seat surface. The seat frame has an arresting device and has an operating unit, coupled to the arresting device. The operating unit is movable into an arresting position and an unlocking position, is coupled to a traction mechanism. The arresting device has an arresting body, coupled to the traction mechanism, is forced by action of a pressure spring into an engagement position, and can be moved by the traction mechanism into a release position and has a locking unit, coupled to the traction mechanism, locking the arresting body in the engagement position and releasing the locking by the traction mechanism.