Abstract: An aircraft including a device for influencing the directional stability of the aircraft is provided. The device includes a control-input device; a flight control device; a sensor device for acquiring the rotation rates, including the yaw rates, of the aircraft; and at least one actuator, which is coupled with ailerons, spoilers, an elevator and a rudder. The flight control device includes a control function generating adjusting commands for the actuators for controlling the aircraft according to control commands. The aircraft includes two tail-mounted flaps, each including an actuator connected with the flight control device, situated symmetrically to each other and on opposite sides of the fuselage, and movable between retracted and extended positions. The control function is designed such that the adjusting commands that are generated on the basis of the control commands depending on the acquired rotation rates include adjusting commands to the actuators of the tail-mounted flaps.

Abstract: A fastening arrangement for fastening a component, in particular a cabin component, to a structural component of an aircraft or spacecraft, including a structural component which has a connection surface; a fastening fitting which has a geometry matched to the geometrical shape of the structural component, has a connection portion associated with the connection surface of the structural component and is produced from a thermoplastic injection-moulding material; and an elastomeric adhesive joint for stable fastening of the connection portion of the fastening fitting to the associated connection surface of the structural component. A corresponding fastening fitting and an aircraft or spacecraft comprising a fastening arrangement of this type and/or a fastening fitting of this type are also described.

Abstract: A test system for plug-in connectors, especially for plug-in connectors in an airplane. A transmitting device which is designed for sending out a test signal to the plug-in connectors to be tested, and comprising at least one receiving device for each plug-in connector to be tested which is electrically coupled with the respective plug-in connector and which is designed for receiving the transmitted test signal and outputting an acknowledgement signal in response to receiving the transmitted test signal. Furthermore, the present invention creates an aircraft or a spacecraft and a method.

Abstract: A vehicle window with a primary window pane arrangement, a secondary window pane that is spaced apart from the primary window pane arrangement and a window funnel that extends between the secondary window pane and the primary window pane arrangement is provided. The vehicle window includes an intermediate space that is formed by the window funnel, the secondary window pane and the primary window pane arrangement, and the intermediate space is sealed and equipped with an air inlet for introducing dehumidified air into the intermediate space. Due to the seal, humid air leading to condensation and frost in the intermediate space is prevented from flowing into the intermediate space during a pressure compensation flow. The passenger comfort is enhanced due to the improved view through the window.

Abstract: Disclosed is a jig for the modelling of at least one section of an aircraft fuselage, with a framework structure and with a multiplicity of adapters for the connection of stiffening elements to the framework structure, which can be moved relative to the framework structure, and/or with a multiplicity of adapters for the modelling of profiles of stiffening elements, which can be moved relative to the framework structure.

Abstract: The application relates to a method for the electronic archiving of data objects by means of a data processing device, wherein the method comprises the following steps: receipt of a hash value tuple comprising one or a plurality of hash values, wherein each hash value is assigned to a data object, receipt of time information on the hash value tuple indicating a time period within which the hash values of the hash value tuple should be electronically archived and comparison of the time information with a predetermined time specification, wherein archiving steps are carried out if the time information specifies a time period for electronic archiving that is shorter than the predetermined time specification. The application furthermore relates to a computer program product.

Abstract: A luggage compartment for a means of transport and a means of transport with a luggage compartment are provided. The luggage compartment comprises a housing with a pivotably attached connecting element and with a sliding element. The connecting element is adapted for being pivotably attached to a first structural element and the sliding element is adapted for moving along a rail connected to a second structural element. The luggage compartment is easy to manufacture and to maintain.

Abstract: A heat exchanger for an outer skin of an aircraft comprises at least one feed line for a coolant, at least one discharge line for the coolant and at least one bundle of coolant channels through which coolant flows, wherein in the case of the heat exchanger being attached to the outer skin, the coolant channels are positioned directly on the outer skin of the aircraft, at least in areas, for dissipating heat to the surrounding environment of the aircraft. The heat exchanger may comprise cooling fins around which air flows for increasing the heat dissipation.

Abstract: A stapling device includes a stapling needle system that is guided through the base body of the stapling device. The stapling needle system can be passed through a hole in one or more components. By exerting a tensile force on the stapling needle system, the component or components can be sandwiched between the stapling needle head and base body of the stapling device. The stapling needle system can be positively locked with the base body by means of a locking device, so as to lock the stapling device in place.

Abstract: A supply system for supplying energy in an aircraft includes at least one electrical line including at least one core connectable to a pole of a current source, an electrically conductive shield, and a detection unit having at least two electrical inputs. The shield surrounds the at least one core under a distance and creates an intermediate space between the at least one core and the shield. At least one port of the detection unit is connected to the at least one core. At least another port of the detection unit is connected to at least one of the shield and the at least one core. The detection unit is adapted for detecting a differential current over the at least one core or an absolute current between the shield and a ground potential for generating a warning signal if a predetermined threshold value for the detected current value is exceeded.

Abstract: A fastening device is disclosed for releasably fastening a mechanism in the region of a floor of an aircraft or spacecraft and includes a base component and a latch component. The latch component includes at least one holding portion including a latch-component-side holding face and is movably coupled to the base component between an unlocked and a locked position. When positioned in a predefined mounting position on the floor component and/or on the base component, the holding portion of the latch component engages a fastening portion, and the latch-component-side holding face faces the mechanism-side holding face. During passage of the latch component from locked position into unlocked position a gap between the latch-component-side holding face and the mechanism-side holding face continuously widens. The invention further relates to an arrangement for a cargo loading system.

Abstract: A self-aligning connector for data and/or power transmission includes a base plate, a plurality of data and/or power contact elements arranged on the base plate, first and second positioning means attached to the base plate, a mounting means and a frame assembly connecting the base plate to the mounting means and comprising a plurality of frames. Each frame is directly connected to exactly two elements selected from a group consisting of the plurality of frames, the mounting means and the base plate. Each frame is tiltable at least about one axis and/or displaceable in at least one direction with respect to each element it is directly connected to. A connector assembly includes a first self-aligning connector and a second connector. A vehicle includes a first compartment and a second compartment separated by a wall, a bellows assembly and the connector assembly.

Abstract: An electrical system for an aircraft is provided. The system comprises an inverter for transforming a first alternating current from an on-board network having a variable frequency into a second alternating current, and at least a first electrical load and at least a second electrical load, which are configured to be operated simultaneously by the second alternating current.

Abstract: A method of producing a panel for lining or cladding an aircraft interior, such as an aircraft cargo hold includes arranging at least one resin layer of a thermo-plastic polymer and at least one reinforcement layer of reinforcement fibers upon one another in a stack, wherein each resin layer extends adjacent and/or substantially parallel to each reinforcement layer; and consolidating the stack to form a panel by applying heat and pressure to the stack. The pressure is applied to the stack in a direction substantially perpendicular to a primary plane of the layers. The pressure is applied to the stack in a non-constant distribution over the primary plane. A corresponding panel for lining or cladding an aircraft interior, such as a cargo hold is also described.

Abstract: An emergency power supply system for providing hydraulic power and electric power in an aircraft includes a fuel cell having an electric outlet for providing electric power, a conversion unit couplable with at least one of an AC bus and a DC bus and the electric outlet, and at least one hydraulic pump having a reconfigurable electric motor and a motor control unit and being couplable with a hydraulic system for providing hydraulic power. The conversion unit is adapted for converting a supply voltage of the electrical outlet to at least one of an AC voltage matching a predetermined voltage at the AC bus and a DC voltage matching a predetermined voltage at the DC bus. The reconfigurable electric motor is couplable with the fuel cell and the AC bus and is adapted for being operated by the supply of electric power either from the fuel cell or the AC bus.

Abstract: An aircraft having at least two separate aircraft fuselages is provided. The aircraft includes a first wing arrangement with at least two non-connected wing sections, and a second wing. In each case the wing sections of the first wing arrangement extend from the outside of an aircraft fuselage towards the outside. The second wing is arranged between insides of the at least two aircraft fuselages. Connecting regions of the first wing arrangement and of the second wing are arranged so as to be offset relative to each other at least on an X-Z-plane of an aircraft-fixed coordinate system. Consequently, the first wing arrangement and the second wing do not influence each other as a result of downwash, and in addition it is possible to do without horizontal stabilizer units that generate downthrust.

Abstract: According to the invention a main-load bearing skin shell for a structural component is provided, wherein the skin shell for being affixed to a support component comprises an outer edge section with an outer edge and comprises: a connection region that does not comprise a core layer, which connection region extends along the edge with the inner skin section and the outer skin section, wherein in an end region of the core layer along the outer edge section of the skin shell reinforcement devices are integrated that project through the shear-force-absorbing core layer.

Abstract: An apparatus for electrically connecting and attaching an electrical device to a wall in a vehicle is provided. The apparatus provides a universal base plate with a first connection region with a first electrical connector arranged therein and a universal rear wall with a second connection region with a second electrical connector positioned therein. The universal base plate comprises attachment means for attachment to a wall in a vehicle, wherein the universal rear wall is designed to form part of an electrical device or to be attached thereto. The rear wall and the base plate comprise largely corresponding directions of extension and are designed to be brought into mechanical engagement with each other, wherein during mechanical engagement the first and the second connection regions are arranged adjacent to each other in such a manner that the first electrical connector and the second electrical connector establish a mutual connection.

Abstract: The present disclosure relates to a fastening arrangement for plate-shaped facing components. The fastening arrangement includes at least one profiled rail comprising legs in a cross-section, an intermediate space being formed between these legs and configured to hold a peripheral portion of at least one of the facing components. A first one of the legs of the profiled rail includes at least one opening which extends into the first leg in a transverse direction of the profiled rail. The fastening arrangement also includes at least one fixing element which is equipped with at least one extension. The extension is designed such that it can be pressed into the opening in the first leg to fix the facing component so that the extension protrudes into the intermediate space and portions thereof come into frictional contact with the peripheral portion of the facing component held in the intermediate space.

Abstract: A disposable seating-surface cover for a toilet-seat flap is configured to cover a seating surface of a toilet-seat flap in order to avoid contact between a user and the toilet-seat flap. The disposable seating-surface cover includes a deformable or foldable base section with an aperture. The disposable seating-surface cover further includes at least one adhesive section which is arranged on or in the base section and is made of a paramagnetic or ferromagnetic material.