Abstract: An aircraft structure arrangement which is in particular suitable to form a part of a secondary structure of an aircraft comprises a first longitudinal profile and a first frame profile. The aircraft structure arrangement further comprises a mounting bracket which is directly attached to both, the first longitudinal profile and the first frame profile. The mounting bracket further is connectable to a component of a primary structure of the aircraft so as to fasten the first longitudinal profile and the first frame profile to the primary structure of the aircraft.

Abstract: A method for the friction stir welding of two components, in particular of two shell components of a fuselage structure of an aircraft and spacecraft, said method comprising the following method steps: positioning the two components relative to one another in such a way that a connection region is formed between the two components; friction stir welding the two components by a friction stir welding tool which penetrates the connection region in order to produce a weld which permeates the connection region with the formation of an unpenetrated weld edge portion of the connection region; and introducing internal compressive stresses, at least in the weld edge portion of the connection region. Further a device for the friction stir welding of two components, in particular of two shell components of a fuselage structure of an aircraft and spacecraft is provided.

Abstract: A data network, especially a data network for an aircraft or spacecraft, includes a primary data grid, and at least one secondary data grid, the primary data grid including primary data nodes, wherein the primary data nodes are directly or indirectly coupled in data communication with each other, and the at least one secondary data grid comprising secondary data nodes, wherein the at least one secondary data grid is configured to connect the secondary data nodes in a data communication chain and to connect the first secondary data node of the data communication chain to a first respective primary data node and/or the last secondary data node of the data communication chain to a second respective primary data node.

Abstract: A method for producing a fiber composite component, in particular for aerospace, includes the following method steps: introducing an elastic core sleeve into a prestressing mechanism; expanding the core sleeve that is introduced, for elastic prestressing of the same, by activating the prestressing mechanism; introducing a core body through an opening of the expanded core sleeve; releasing the core sleeve by deactivating the prestressing mechanism, for the snug enclosing of the core body by the core sleeve and thus for the forming of the molding core (14); and at least partly laying at least one semifinished fiber product on the molding core that is formed, for the shaping of the fiber composite component to be produced.

Abstract: A support strut for use as a primary load-bearing structural component for the hinged coupling of at least one additional primary load-bearing structural component. The support strut includes: a rod-shaped base body extending in a longitudinal direction, a fiber composite with an annular cross section, central hole originating from the first end of the base body, and with annular holes spaced apart relative to each other in the circumferential direction of the annular cross section and originating from the first end of the base body as well as running along the longitudinal direction in the base body; roving bundles imbedded in a matrix material that fills up the respective annular hole; and a hinged connecting body with a bearing receptacle for holding a swivel joint; as well as a guiding system with such a support strut and a method for manufacturing such a support strut.

Abstract: An energy-absorbing connection arrangement with a multitude of connectors for joining two components, such as a transverse member and a circular frame element, of an aircraft fuselage. Each connector comprises a headed shaft and the shafts reach through component boreholes. On the shaft ends facing away from the heads, counter-bearings are provided. At least one of the components comprises a fiber-reinforced plastic material. A head and/or counter-bearing of at least one connector rests against at least one underlay device. The underlay device is received in a guide groove in the first component, with the guide groove commencing in the region of the boreholes. The underlay device, upon exceeding a mechanical threshold load, is slidable away from the boreholes. Energy absorption takes place along a longitudinal center axis of the guide groove as a result of hole-bearing-stress failure and/or the shearing of the fiber-reinforced plastic material component.

Abstract: A component arrangement on an aircraft structure, in particular on a fuselage structure of an aircraft, with at least one mounting structure connected with the aircraft structure, and at least one component to be assigned to the aircraft structure, in particular a measuring device. At least one component carrier is provided to receive the component to be mounted, wherein the component carrier is connected with the mounting structure, and an outer surface of the component carrier, facing away from the component, extends approximately flush with an outer surface of the aircraft structure. Also a method for the installation of a component into an aircraft structure with a mounting structure including the step of connecting the component with the mounting structure via a component carrier, so that an outer surface of the component carrier, facing away from the component, extends approximately flush with an outer surface of the aircraft structure.

Abstract: An air-conditioning system for an aircraft includes a compressed air branch for conveying externally supplied and pressurized air, preferably bleed air. Furthermore, a cooling circuit for conveying preferably liquid refrigerant is provided and extends through a ram air duct. The system also includes a first heat exchanger for the heat transfer between the compressed air branch and the cooling circuit, a compressed air turbine arranged in the compressed air branch and a cooling circuit compressor arranged in the cooling circuit and mechanically coupled to the compressed air turbine. The system can have a modular design and be positioned at optimal locations in the aircraft due to the separation of the compressed air branch and the cooling circuit. In this way, the length of hot compressed air ducts can be shortened.

Abstract: A seat modification assembly for use with a passenger seat provided in a mass transport vehicle, especially an aircraft, comprises at least one seat modification element adapted to change the ergonomic seating profile of a passenger seat provided with the seat modification assembly. The at least one seat modification element comprises at least one mounting arrangement adapted for detachably mounting the seat modification element to a portion of the passenger seat.

Abstract: A supply system for supplying passengers in a passenger compartment of a vehicle, in particular an aircraft, includes a supply line and a number of supply modules which, for supplying the passengers, are connectable to the supply line. The supply modules are displaceable relative to one another along the supply line, the supply line having one or a plurality of supply openings by which the connection between the supply line and the supply modules can be established, each supply module furthermore being assigned at least one screen which is arranged in such a manner on the service supply line that it is displaceable along the supply line and can cover a part of the one supply opening or of the plurality of supply openings which is not used for the connection of a supply module to the supply line.

Abstract: Provided is an aircraft fuselage structure having an outer skin, a support structure arrangement comprising a multiplicity of frame elements and a floor structure arrangement having a multiplicity of floor support struts. The aircraft fuselage structure provides a connection between the floor structure arrangement and the support structure arrangement which is as simple and quick to produce as possible, while not significantly increasing the weight or weakening the structure. Either the floor structure arrangement or the support structure arrangement can have at a connection there between a male connector element or a female connector element. The male connector element can have a peg which extends in the engagement direction and which has a circumferential outer surface which is provided with a multiplicity of circumferential projections. The female connector element can have a cavity, the inner surface of which is provided with a multiplicity of circumferential tabs.

Abstract: A function-monitored guidance system for adjusting at least one system component, the guidance system including a guiding mechanism having at least one adjustment component for guiding adjustment movements of the system component to be adjusted, of which at least one adjustment component includes a sensor device for detecting a load state of the adjustment component, and a monitoring device connected functionally to the adjustment component. The monitoring device provides detection time periods for detecting sensor signals of the at least sensor device, provides a threshold value, with which the number of overshoots thereof by the sensor signals within detection time periods is determined, and determines, from the number of overshoots in each case within the detection time periods, a value for the operating state. A method for monitoring the function of a guidance system for adjusting at least one system component is also disclosed.

Abstract: The invention relates to methods and to a manufacturing device for manufacturing a sandwich component. A semifinished product arrangement is soaked with a flowable matrix material, for example a resin, in particular by an infusion method. By using the method of the invention, inherent tensile stresses introduced by the respective method and remaining in the sandwich component to be manufactured are reduced, and moreover the risk of crack formation in the course of the process, afterwards and during operation of the sandwich component is minimized.

Abstract: A device for manually painting a large surface using a spray gun connected to a paint feed line for the supply of an enamel paint and to a pressure line for the provision of compressed air. After the manual actuation of an operating switch arranged on a handle piece, the spray gun sprays the enamel paint by compressed air via a spray head to apply the enamel paint onto the surface. The spray gun includes means such that it can be moved manually along the surface. The means include an extension rod, at one end of which the spray gun is attached by the handle piece and which is configured such that, when held by an operator on an arm holder configured at the opposite end, it extends from the elbow along the forearm of the operator and beyond the distal end of the forearm.

Abstract: An aircraft cabin management panel and an aircraft cabin management system including the aircraft cabin management panel. The aircraft cabin management panel includes a user interface and a control unit configured to communicate a control instruction to at least one of a plurality of cabin components provided in an aircraft cabin upon an input received via the user interface. The control instruction enables the at least one of the plurality of cabin components to perform an operation in accordance with the control instruction.

Abstract: The present invention relates to an electric power supply system for an aircraft having a transformer-less HVDC architecture, the system including: at least one multiphase engine generator in a star configuration which provides a multiphase alternating (AC) voltage; a converting circuit for converting the multiphase AC voltage into a corresponding direct (DC) voltage for supplying at least one aircraft load; an electric power supply interface for connection with a standardized GPU plug of an external GPU, the electric power supply interface comprising a supply voltage output terminal coupled to a self-contained power source for providing a low voltage control signal for driving a GPU internal switching circuit wherein the power source is decoupled from the AC voltage and DC voltage. The present invention further relates to an aircraft and an airport power supply system.

Abstract: A connecting device for manufacturing a peeling-stress-resistant connection between two components. The connecting device includes a carrier, which has a first surface and a second surface opposing the first surface. The connecting device further includes a plurality of hook and loop elements which extend both from the first and the second surface of the carrier and each have at their free ends facing away from the first or the second surface of the carrier a hook and loop head, which is arranged to enter into a hook and loop connection with a component comprising a fiber-reinforced composite material.

Abstract: The invention pertains to a protective device for a pressure line for conveying pressurized fluids, as well as to a pressure line section with a pressure line for conveying pressurized fluids and a corresponding protective device.

Abstract: A vehicle includes a passenger compartment and a cargo compartment separated by a floor structure, and a cargo unit including a storage rack arrangement and a transport arrangement operable for selectively transporting objects between the storage rack arrangement and a predetermined transfer position in a cavity of the cargo unit. The transport arrangement includes a conveying apparatus including a table unit movable along a vertical transport path, and the vehicle includes a mounting means adapted for securing the cargo unit in a predetermined operating position inside the cargo compartment, in which an access aperture in an upper cover of the cargo unit is disposed in alignment with a through hole in the floor structure. A lift apparatus including a gripping device is operable to convey objects from the transfer position through the access aperture and the through hole between the cargo compartment and the passenger compartment.

Abstract: A construction kit for a housing structure of a monument for a cabin of a vehicle, in particular of an aircraft includes a plurality of integrally formed sandwich panels which each have two cover panels, which surround a core, and are formed with panel connecting structures which are each formed as a plug region or as a mating plug region. The mating plug region is formed so as to be complementary to the plug region in such a way that a plug region of a sandwich panel can be plugged into the mating plug region of another sandwich panel to connect the sandwich panels.