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: An aircraft includes an insulation system for thermal and acoustic insulation. The insulation system includes a cabin, an outer skin, a sound insulating unit, and a heat insulating unit. The sound insulating unit is designed to acoustically insulate the aircraft. The heat insulating unit is designed to thermally insulate the aircraft. The sound insulating unit and the heat insulating unit are arranged between the cabin and the outer skin.

Abstract: Optimizing data updates in an operationally approved software application of aircraft, comprising a first software component using a second software component. Following the receipt of a software component comprising an update of said second software component, said received software component is analyzed and a class of the update of said second software component is determined. Depending on said class, the update of said second software component is transmitted to said first software component and/or to a central download system. If the update of said second software component is transmitted to said first software component, said second software component is updated and a configuration report showing said update is created.

Abstract: A security door comprises a frame structure, having a lateral surface in which a plurality of doorways are constructed. A first doorway has a first width along an inner circumference of the frame structure, and lateral surface portions delimiting the first doorway in a first direction and a second direction, opposing the first direction, along the inner circumference of the frame structure have a second width. A lock element is received in the frame structure and comprises a first segment, movable along the frame structure inner circumference relative to the frame structure, and a second segment, movable independently of the first segment along the inner circumference relative to the frame structure. The first segment is dimensioned so that, in a position in which it closes the first doorway, it also closes a second doorway adjacent to the first doorway in the first direction along the frame structure inner circumference.

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: The aerodyne, e.g. an airplane, includes: an auxiliary power unit suitable for producing electricity; a first electricity distributor connected to the unit; at least one flight propulsion engine including an electricity generator; at least one undercarriage motor, the motor enabling the aerodyne to taxi; and a second electricity distributor connected to the generator and to the undercarriage motor in order to transmit electricity from the generator to the motor independently of the first distributor.

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: 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: 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: 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 method for obtaining the inertial properties of a movable rotating around a hinge line in an aircraft control surface. The method includes the steps of removing the mechanical connections of the actuators from the movable, leaving the movable free to rotate around its hinge line, further balancing the movable and calculating in a first approach its coarse static moment. The method includes refining the coarse static moment and obtaining simultaneously a frictional moment of the movable; incorporating an elastic element on the control surface and configuring a second order mechanical system; inducing forced oscillations on the movable at a certain frequency, this frequency being increased until it is sensibly close to the resonance frequency of the movable to produce a wave response; calculating, from the wave response, the moment of inertia of the movable.

Abstract: A device for detecting the state of a switch. The device includes a detection circuit which delivers a signal of specified value (Vpullup) when the value of an electrical quantity (RSw) characterizing the state of the switch is less than a threshold called the lower threshold (Rclosed) and/or a signal of different value when the value of the electrical quantity is greater than a threshold different from the lower threshold, called the upper threshold (Ropen). The disclosed embodiments also concern flight control systems, in which the device is implemented, and the aircraft including the systems.

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: The automatic piloting system includes an element for automatically supplying a computation unit, when the aircraft is guided according to a descending corrected speed and a new corrected speed which is greater than the corrected speed used for guidance of the aircraft is input by the pilot, with a predetermined maximum Mach number which replaces the current Mach number and which is intended to form, together with the new input corrected speed, a pair of speeds which is taken into account by the computation unit for determining the guidance instructions for the aircraft.

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: An automatic landing method and device for an aircraft on a runway with strong slope. The device includes means to automatically transmit, a runway slope value to an automatic piloting system of the aircraft, and said automatic piloting system uses the slope value to automatically manage the flare phase upon landing.