Abstract: The invention pertains to an aircraft with at least one passenger cabin that comprises at least one door entry area for the passengers and for the flight attendants that is visually separated from the passenger cabin and referred to as a space unit. Variable or mobile elements assigned to at least one partition wall/one monument of the space element can be arranged in the space unit that can be used as a disposition zone during the flight phase in order to realize working areas or service and/or comfort facilities for passengers or for the flight attendants.

Abstract: A water disinfection system includes a water disinfection device, having a UV light generator for the UV treatment of water, and a water pipe, having a first pipe portion and a second pipe portion and a third pipe portion which branches off between the first and the second pipe portion. The water disinfection device includes a first water connection and a second water connection. The first water connection is connected to the first pipe portion. The second water connection is connectable to a water reservoir which is to be provided. The second pipe portion is connectable to a water source which is to be attached. The third pipe portion is connectable to a tap for water, so as to be able in this way to provide an improvement in the water quality.

Abstract: A method for the repair of a sandwich plate having a core structure, a top surface layer and a bottom surface layer and a plurality of honeycomb-shaped cells includes providing at least one penetrating drill hole in at least one of the top surface layer and the bottom surface layer above one of the plurality of honeycomb-shaped cells in a damaged region of the sandwich plate, injecting a stabilising material into the honeycomb-shaped cell, and filling the damaged region with a filler material.

Abstract: An arrangement including a supporting structure and a reproduction of an aircraft passenger cabin, arranged inside the supporting structure. The aircraft passenger cabin is on a 1:1 scale for receiving components of cabin systems. The supporting structure is composed of standardized elements, for receiving components of the cabin system. The cabin fittings including standardized supports and connections so that the components of the cabin system can be tested under operating conditions.

Abstract: A seat bench transport device for transporting a bench of seats for a vehicle, comprising a chassis, a retaining rail pair that is arranged on the chassis and including two retaining rails extending parallel to one another for accommodating seat bench feet. The lengthwise sides of these rails that face one another are open at least in sections and the lengthwise sides thereof that face away from one another each have at least one locking section. A displacement mechanism moves the retaining rails transversely relative to one another.

Abstract: The present invention provides for devices and methods for the transmission of data over nodes of a specific network. A device may comprise at least two network nodes, a bus having a transmitting line and a receiving line for interconnecting the network nodes. The respective network node has a fault protection circuit which is to bypass the network node in the event of a fault and is capable of reversing the polarity of the transmitting line and of the receiving line, a detection means for detecting a reverse in polarity of the transmitting line and of the receiving line by the respective upstream network node, and a fault-locating means for locating a fault in the upstream network node when a reverse in polarity of the transmitting line and of the receiving line has been detected.

Abstract: An air guiding element for an aircraft air-conditioning system includes a distributing pipe having an air inlet opening arranged in the region of an end face of the distributing pipe and an air discharge opening arranged in the region of a generated surface of the distributing pipe. The air guiding element further comprises a flow diverting element having a first section connected to the air discharge opening of the distributing pipe and a second section arranged downstream of the first section relative to the direction of the air flow through the air guiding element. The second section is configured to deflect the air as it flows through the second section at an angle of approximately 45 to 135° relative to the direction of the air flow through the first section, and a diffuser which is arranged downstream of the second section.

Abstract: A support structure for an air supply arrangement for air conditioning aircraft passenger cabins. The air supply arrangement comprises an centrally controlled cabin ventilation system and an individually adjustable cabin ventilation system. The support structure includes: a first section for receiving and/or integrating cabin ventilation system components, a second section for receiving and/or integrating passenger emergency oxygen supply components and a third section comprising a plurality of receiving devices. Each receiving device receives and releasably secures an active module for individually adjustable cabin ventilation. The third section has at least the number of receiving devices required for at least one receiving device to be associated with each seating row for a maximum number of seating rows arrangeable in the cabin A supply system includes at least one such support structure and one of the active modules. A method is provided for configuring a corresponding supply system.

Abstract: A passenger monitoring and directing system for use in an aircraft cabin is provided. This system includes at least one information unit to be arranged in the aircraft cabin and at least one passenger monitoring device. The information unit includes at least one monitoring portion and the passenger monitoring device is assigned to the information unit and arranged relative to its monitoring portion in order to monitor the passengers through the monitoring portion of the information unit.

Abstract: A joining apparatus for joining together structural components of an aircraft, includes positioning means for holding the structural components to be joined in a defined desired position, in which the structural components can be fixedly joined together by means of a joining device that can be moved relative to the structural components by way of guiding means, wherein the positioning means encompass a formative frame structure that is detachably secured to the structural components to be connected along the joining edges outside in the edge area, and serves as a guiding means for the joining device movably secured hereupon.

Abstract: A method for final assembly of at least two aircraft includes assembling the at least two aircraft in a transverse direction on a carousel, the at least two aircraft disposed side-by-side, and rotating the carousel on a vertical rotation axis 360°.

Abstract: A pressurized aircraft fuselage includes a pressure bulkhead installed on a fuselage structure, which forms a barrier between an internal pressurized cabin area and an outside area. The edge of the pressure bulkhead is circumferentially attached to the fuselage structure by movable fastening means. The movable fastening means includes at least one clamping element which is arranged inside a trapezoidal shaped mounting bracket which corresponds to an inserted edge of the pressure bulkhead, in order to form a clamping connection for the pressure bulkhead towards the fuselage structure.

Abstract: A method for mounting interior components in an aircraft includes premounting a first interior component and premounting a second interior component. At least one of the first and the second interior component is secured to a mounting device and the first and second interior components are connected to form an individual module. A plurality of individual modules secured to the mounting device are interconnected to form a large module which is secured to the mounting device. The large module is detached from the mounting device and transported to a final-mounting position in an aircraft fuselage element. The detached large module is then mounted in the aircraft fuselage element.

Abstract: A method for a thermal joining of two thermoplastic components includes arranging at least one reactive sheet entity in a mating zone between the two thermoplastic components. A multiply perforated metallic sheet entity configured as a bonding agent is disposed on each side of the at least one reactive sheet entity, at least in some regions of the mating zone. The at least one reactive sheet entity is activated so as thermally join the two thermoplastic components in the regions of the mating zone.

Abstract: A monument is provided for an aircraft. The monument includes, but is not limited to several system components with identical, substantially identical or similar functions that can be connected by way of a single system connection arrangement to the supply in the aircraft. Distribution of the supply media, received by the aircraft, to the individual system components takes place within the monument. The system connections can thus be identical to the system connections of a single monument.

Abstract: A fixed wing of an aircraft, having a main wing extending over a half-span with a wing box including spars extending along the spanwise direction of the main wing, ribs arranged one in back of the other viewed in the spanwise direction, and an outer skin. The wing box includes a wing box base section (K10) and a wing box adapter section, that forms the outer end area of the wing box, as viewed from the wing root, and is designed to secure a wing tip device. In its nominal state of construction, the dihedral angle of the wing box adapter section referring to the respective local spanwise direction continuously increases by at most 60 degrees from the outer rib of the wing box base section (K10) up to the outermost rib of the wing box adapter section.

Abstract: A cooling system of a vehicle with a fuel cell includes an absorbent circuit with an absorber tank, a regenerator tank, an absorbent pump and a first pressure reduction means and a coolant circuit with a condenser connected to a steam outlet of the regenerator tank, a second pressure reduction means and an evaporator arranged between a steam inlet of the absorber tank and the second pressure reduction means. The regenerator tank is designed to desorb the coolant in solution in the absorbent by absorbing a first quantity of heat and to introduce it in a vaporous state into the condenser. The evaporator is designed to evaporate the coolant while absorbing a second quantity of heat and to introduce it in the vaporous state into the absorber tank. At least one of the first and of the second quantity of heat could be provided by the fuel cell.

Abstract: A sealing system (38) for use in an aircraft facility to be sealed from the environment comprises a closing element (40) which can be connected to a housing (42) of the aircraft facility in order to seal an opening (44) formed in the housing (42) of the aircraft facility. Furthermore, the sealing system (38) comprises a receiving device (46), and a sealing element (48) received in the receiving device (46). A transfer device (54) is adapted to transfer the sealing element (48) between an inactive state, in which the sealing element (48) is shaped and/or positioned such that it cannot be brought into sealing contact with a sealing surface (64), and an active state, in which the sealing element (48) is shaped and/or positioned such that it can be brought into sealing contact with the sealing surface (64).

Abstract: A measurement device for measurement of forces in structural components, having a measurement sensor, which is embodied such that it is connected with the structural component in a force-fit and/or form-fit manner, and generates measurement signals as a function of force transfers in the structural component, the measurement device having a measurement casing upon the measurement sensor. Processing of received measurement signals can occur, and the measurement casing has connecting means, for placing in position and releasable attachment of the measurement casing on the structural component, and the contacting means of the measurement casing can establish contact with the measurement sensor for the reception of the measurement signals.

Abstract: An earth connection for electrically and mechanically connecting a plurality of earth wires to a structure, in particular to an aircraft structure, comprising an angled element which element is formed in one piece and is made of electrically conductive material, which comprises a first and a second fastening portion. The first fastening portion is fastened to the structure and the second fastening portion comprises a plurality of electrical connections for connecting the earth wires. The electrical connections comprise socket contact elements which are formed so as to receive pin contact elements of the earth wires.