Airbus Operations Patente

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

The present invention pertains to a production system (50) for the automated assembly of vehicle components (1), in particular for the automated assembly of structural components of an aircraft or spacecraft (100). The production system (50) comprises vehicle components (1) being provided with status sensors (10), each status sensor (10) being configured to determine status data (12) of the respective vehicle component (1), positioner units (2) being configured to grip the respectively associated vehicle component (1) at mounting points (7) and move the respectively associated vehicle component (1) into an assembly position (3), a position-measurement system (4) being configured to determine the assembly position (3) of each vehicle component (1), force sensors (5) being configured to determine at least one of reaction forces and moments of each gripped vehicle component (1) at the mounting points (7) in the assembly position (3), and a computer-based control system (30) being in data communication with the vehicle components (1), the positioner units (2), the position-measurement system (4) and the force sensors (5), and being configured to control the positioner units (2) based on the determined status data (12), the determined assembly positions (3) and the determined reaction forces and moments of the vehicle components (1).

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

The present invention discloses a fireproof polymer matrix composite structure which comprises a CFRP lay-up having a first side and a second side, and a first GFRP layer located on the first side of the CFRP lay-up or on the second side of the CFRP lay-up. The CFRP layer may be of tape of carbon fibre, or fabric of carbon fibre. Furthermore, the present invention discloses an aircraft that comprises said fireproof polymer matrix composite structure.

A high voltage conductor (100) for transmitting high voltage is provided. The high voltage conductor comprises a power wire (140), a fault detection unit (160), and a monitoring unit (170). The power wire (140) is configured for transmission of electrical energy. The fault detection unit (160) is configured for detecting an electromagnetic field emanated by the power wire, and the monitoring unit (170) is configured for detection of degradation in an isolation of the high voltage conductor. The monitoring unit is connected to the fault detection unit and is configured to receive an electrical signal induced in the fault detection unit, which electrical signal is induced as a result of a degradation of the isolation of the high voltage conductor. Thus, degradation of the isolation of the high voltage conductor may be recognized at an early stage.

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

Method of manufacturing a three-dimensional object (22) by means of additive manufacturing as well as to a corresponding system for carrying out the method and a dispensing head for use in the method. The three-dimensional object (22) comprises a three-dimensional component (21). The method comprises providing a substrate (20, 20"), and successively forming on the substrate (20, 20") a plurality of layers (23, 23'), wherein each layer is formed in a pattern corresponding to a three-dimensional component (21) being manufactured and wherein each layer (23, 23') is formed by dispensing a curable material from a nozzle (5, 5') of a dispensing head (4, 4', 4") and subsequently curing the curable material (8). The three-dimensional object (22) is constituted by the combination of the substrate (20, 20") and the three-dimensional component (21), wherein the substrate (20, 20") has a non-planar surface portion and the three-dimensional component (21) is formed at least in part on the non-planar surface portion in such a manner that it is fixedly secured to the substrate (20, 20"). During forming of at least one of the layers (23, 23') and/or between forming of at least two adjacent ones of the layers (23, 23') a relative movement between the substrate (20, 20") and the dispensing head (4, 4', 4'') is effected such that in a substrate coordinate system the dispensing head (4, 4', 4") moves along a non-linear path over the non-planar surface portion.

Zusammenfassung wird geladen …

A pressurized aircraft fuselage, comprising a pressure bulkhead (1) installed on a fuselage structure (2), which forms a barrier between an internal pressurized cabin area (3) and an outside area (4), wherein the edge of the pressure bulkhead (1) is circumferentially attached to the fuselage structure (2) by fastening means, wherein the fastening means comprise a pair of ring-shaped attachment frames (5a;5b) made of an open or hollow profile, which are disposed at each side of the pressure bulkhead (1) respectively, in order to form a clamping connection for the pressure bulkhead towards the fuselage structure (2).

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

A Divider element for an aircraft cabin is disclosed comprising a frame member (3) forming a closed ring wherein the frame member (3) may assume an expanded state and a collapsed state, wherein in the expanded state the frame member (3) extends in a plane and defines a first area which is surrounded by the frame member (3) and wherein in the collapsed state the frame member (3) defines a second area which is surrounded by the frame member (3), the second area being smaller than the first area, and a flexible sheet member (27) which is fixed to the frame member (3) and dimensioned such that when the frame member (3) is in the expanded state, it extends over the area defined by the frame member (3).

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

Die Erfindung betrifft eine Mischerbaugruppe zur Vermischung zweier Luftströme in einem Lüftungssystem. Die Mischerbaugruppe umfasst eine Mischkammer, die einen Einlass und einen Auslass und eine die Mischkammer begrenzende Mischkammerwand umfasst, sowie eine die Mischkammerwand zumindest abschnittsweise umgebende Ummantelung. Die Ummantelung bildet und begrenzt einen Zwischenraum zwischen der Mischkammerwand und der Ummantelung. Die Mischerbaugruppe umfasst ferner ein Filterelement, das den Zwischenraum mit einer Umgebung der Mischerbaugruppe fluidisch verbindet, wobei der Zwischenraum mit der Mischkammer fluidisch verbunden ist. Fluid kann so durch das Filterelement in den Zwischenraum und weiter in die Mischkammer strömen. Ferner sind ein Stauraum mit einer Mischerbaugruppe, ein Flugzeug mit solch einem Stauraum und ein Verfahren zum Herstellen einer Mischerbaugruppe in einem Flugzeug beschrieben.

The present invention relates to a cabin module having a sanitary unit for an aircraft. In order to make available a space-saving sanitary unit having a toilet which offers improved user convenience to persons with restricted mobility, a cabin module (10) for an aircraft is provided which has a sanitary unit (12). The sanitary unit has a toilet cubicle (14) with a toilet (16). The toilet cubicle is formed by four side walls (18a, 18b, 18c, 18d) and the toilet is arranged on a first side wall (18a). A first access door (20) is arranged in a second side wall (18b), which extends transversely to the first side wall and adjoins the first side wall. A surface which is designed to at least partially accommodate a wheelchair is provided as an option within the toilet cubicle. The cabin module is configured to be installed with the second side wall transversely to a direction of flight. The first side wall 18a is aligned with an external wall in the installed state.

Zusammenfassung wird geladen …

The present invention provides a display device for a vehicle. It comprises a housing (11), a display screen, and at least one functional unit (1, 1') comprising an operating element, each being a switch unit or a communication unit. Each of the at least one functional unit (1, 1') is adapted to be releasably coupled to the housing (11) and comprises an insertion portion (3) and an operating element support portion (4, 4') supporting the respective operating element, and a first contact arrangement (6) provided on the insertion portion (3) and electrically coupled to the operating element. The housing (11) comprises at least one functional unit coupling arrangement, each adapted to be selectively and releasably coupled to at least one of the at least one functional unit (1, 1') and comprising a cavity inside the housing (11) for receiving the insertion portion (3) of the at least one functional unit (1, 1'), a second contact arrangement in the cavity, a retaining means, and an opening (20) in an exterior wall (19) of the housing (11) communicating the cavity with the exterior of the housing (11). The opening (20) and the cavity are sized and arranged in such a manner that for coupling one of the at least one functional unit (1, 1') to the housing (11) the respective insertion portion (3) can be inserted through the opening (20) into the cavity into a predetermined operating position in which the insertion portion (3) is releasably retained by the retaining means such that the first contact arrangement (6) is electrically connected to the second contact arrangement, and in which the operating element support portion (4, 4') and the operating element are positioned exterior to the housing (11) such that the operating element is accessible for a user.

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …