Abstract: An air-conditioning system for an aircraft has a fresh air line, a recirculation device, an air-mixing device, an air distribution system with multiple cabin air outlets, and a control unit. The control unit is designed to determine or to receive flight-specific parameters characterizing the flight state of the aircraft, and to determine or to receive environment-specific parameters which characterize an air quality in the environment of the aircraft. A first operating state of the air-conditioning system is brought about in the case of a predefined limit value of at least one environment-specific parameter being exceeded, and a second operating state of said system is brought about during a second flight state, which is outside the first flight state. In the second operating state, the fresh air line is fluidically connected to the air-mixing device, and in the first operating state, the fresh air line is separated from the air-mixing device.

Abstract: A waste-gas line has a first pipe section connectable to a battery and having an inlet end and a first flange, a separate second pipe section having a second outlet end and a second flange, and an inner sleeve and an outer sleeve, both of a non-conductive material. The inner sleeve is positioned on an outer side of the first flange and of the second flange. The outer sleeve surrounds the first flange, the second flange and the inner sleeve. The first and the second flanges are fastened to one another in such a way that at least the second pipe section is electrically insulated by the inner and the outer sleeves and, by the combination of inner and outer sleeves, is heat-resistant up to a temperature of at least 1100° C. and pressure-resistant up to a pressure of at least 8 bar, for a duration of at least 120 seconds.

Abstract: A vehicle door unit comprises a rotating lever supported rotatably about a first shaft at a first end, a door mounting coupled rotatably about a second shaft to a second end of the rotating lever, a door attached to the door mounting and being configured to cover an opening in a vehicle and to close off a vehicle interior, and a drive unit configured to rotate the rotating lever about the first shaft between a closed position and an open position. The rotating lever is configured to move the second shaft, on a movement from the closed position to the open position, on a circular path, due to which the door mounting is first moved into the vehicle interior and, on further rotation of the rotating lever, out of the vehicle interior.

Abstract: This pertains to a method for connecting fiber-reinforced structural components. In a first step of the method, a first fiber-reinforced structural component and a second fiber-reinforced structural component are supplied. In another step, the first fiber-reinforced structural component and the second fiber-reinforced structural component are heated by means of a heating device. A penetration through the first fiber-reinforced structural component and the second fiber-reinforced structural component is produced in another step by means of a fastening device. In another step, the first fiber-reinforced structural component is connected to the second fiber-reinforced structural component by means of the fastening device. This furthermore pertains to a structural aircraft element.

Abstract: The invention relates to a control device for controlling a plurality of network nodes of a computer network, comprising a master computing means for controlling the network nodes in accordance with a program, which master computing means assigns at least one program to each network node, comprising a control logic which is configured to group the network nodes in accordance with the programs assigned to these network nodes in each case and to transmit the same program in parallel to those network nodes of the same group which have been assigned this same program by the master computing means. The invention further relates to a method for operating a computer network and to a computer network.

Abstract: An aircraft includes a fuselage, each wing with a movable flap element arranged on the wing, having a sensor element providing a sensor signal corresponding to vibrations on the flap element, and being movable between a retracted and an extended positions, drive means having a movable driven output connected by an actuation assembly with each of the flap element and configured such that a movement of the output effects a movement of each of the flap element between the extended and retracted positions. A control unit is adapted to compare for each sensor element during operation of an excitation means the amplitude of the vibrations in the frequency interval detected by that sensor element with a predetermined threshold of that sensor element and to provide a failure signal when for at least one sensor signal the amplitude is below the threshold of that at least one sensor signal.

Abstract: An oxygen supply device for an aircraft has a reaction tank for chemical oxygen generation and a pressurized tank filled with oxygen. The oxygen supply device also has an energy converter for converting thermal energy into electrical energy and also a control unit for setting a first amount of oxygen, provided by the reaction tank to a consumer unit, and a second amount of oxygen, provided by the pressurized tank to the consumer unit. The energy converter is designed to convert a thermal energy, generated by the chemical oxygen generation in the reaction tank, into electrical energy and to provide the electrical energy. The control unit is designed to set the second amount of oxygen, provided by the pressurized tank to the consumer unit, by using the electrical energy provided by the energy converter. The invention also relates to a method for supplying a passenger cabin of an aircraft with oxygen.

Abstract: A device and method for moving cargo above a floor inside an aircraft comprises a rigid under-floor. The device comprises a body part for supporting the weight of the cargo, lifting means and for lowering the body part from its lifted position into a retracted position, and a drive unit for moving the body part. The method comprises the steps of providing at least two devices in an aircraft, positioning the devices beneath the cargo, wherein the body parts of the devices are in their retracted positions. The body parts are lifted such that the weight of the cargo is supported by the body parts and the cargo is lifted above the floor. The cargo is then moved to a desired position and lowered into their retracted positions such that the cargo is lowered and the devices are moved away vertically from the cargo.

Abstract: An aircraft having at least one thrust providing jet engine and a fuselage with an integrated pressurized cabin includes an environmental control system having at least one pneumatic air cycle air conditioning unit, a bleed air port in the at least one thrust providing jet engine, a non thrust providing auxiliary supply unit configured to provide electricity and compressed air on ground and during flight, and at least one compressed air line. The at least one compressed air line is coupled with the bleed air port and the auxiliary supply unit. The environmental control system is coupled with the at least one compressed air line. Further, the auxiliary supply unit is dimensioned to exclusively operate the environmental control system by delivering compressed air, and bleed air from the bleed air port is selectively providable to the environmental control system for redundancy.

Abstract: A lift apparatus for transporting objects between compartments of an aircraft through an aperture in a floor structure separating the compartments and an aircraft in which such lift apparatus is mounted. The lift apparatus includes a conveyor with a retaining portion to selectively retain and release objects to be transported, a guide to which the conveyor is mounted to be linearly movable along a predetermined path of motion defined by the guide, and a moving mechanism for driving the conveyor to linearly move along the predetermined path of motion. The retaining portion and a closing portion of the conveyor are along the path of motion, and the lift apparatus mounts in an aircraft with the path of motion extending through the aperture. The conveyor is selectively movable along the predetermined path of motion between positions.

Abstract: The embodiments relate to a method for additive manufacturing of a component made from a metal matrix composite for a vehicle. In a step of the method, a plurality of elongated filaments is provided. In another step, metallic powder is provided. In a further step, the metal matrix composite component is additively manufactured by melting the metallic powder.

Abstract: Lavatories on-board a vehicle, and in particular to a lavatory unit for use by persons with reduced mobility on-board a vehicle are described. The lavatory unit includes a lavatory housing structure enclosing a lavatory interior space, a door opening in the lavatory housing structure, a toilet assembly inside the lavatory interior space, and a transition seating support for a user. The transition seating support provides a first transfer position and a second transfer position. In the first transfer position, in an open door state the transition seating support is directly accessible for a person sitting in a wheelchair that is located at least partly outside the lavatory unit such that the person can transfer to the transition seating support and vice versa, and in the second transfer position, a person sitting on the transition seating support can transfer to the toilet assembly and vice versa.

Abstract: A structural component includes a composite laminate built up of a plurality of layers of carbon fibers, wherein the layers of carbon fibers are oriented in different directions, wherein the carbon fibers are surrounded by a conductive polymer resin, wherein the carbon fibers of at least one of the layers comprise an electrically insulating coating, and wherein at least one of the coated carbon fibers extend through its respective layer to form an electrical connection between ends of the layer spaced apart from one another.

Abstract: A device for providing reinforcement strand loops for a multi-needle system for mechanically reinforcing a component made of a foamed plastics material, has a profile body, at least two clamps positioned on the periphery and/or end face of the profile body for fixing a reinforcement strand to the profile body, at least one slider which can be moved in parallel with a central longitudinal axis of the profile body to produce a reinforcement strand loop, at least two separators positioned in the periphery and/or end face of the profile body for separating the reinforcement strand loop from the reinforcement strand and a feeder for feeding the reinforcement strand loop. As a result, reinforcement strand loops can be produced with high precision and individually presented to the needles and/or grippers of a multi-needle system.

Abstract: A seat arrangement includes a first group of seats having first and second passenger seats, a second group of seats having third and fourth passenger seats, a first aisle parallel to a longitudinal axis, and a second aisle parallel to the longitudinal axis. The first passenger seat is situated next to the first aisle with a seat direction parallel thereto, and the fourth passenger seat is situated next to the second aisle with a seat direction parallel thereto. The seat direction of the second passenger seat is angled by at least 2° relative to the seat direction of the first passenger seat. The seat direction of the third passenger seat is angled by at least 2° relative to the seat direction of the fourth passenger seat. The first and second groups are next to each other, and have a longitudinal offset relative to each other along the longitudinal axis.

Abstract: In a method for detecting damage to a component of an aircraft, having an unpressurized first area and a pressurized second area, at least one theoretical pressure parameter, characteristic of a theoretical pressure in the unpressurized first area, a theoretical pressure in the pressurized second area or a theoretical pressure difference between the unpressurized first area and the pressurized second area, is determined. At least one actual pressure parameter, characteristic of an actual pressure in the unpressurized first area, an actual pressure in the pressurized second area or an actual pressure difference between the unpressurized first area and the pressurized second area, is recorded. The theoretical pressure parameter is compared with the actual pressure parameter. Damage to a component of the aircraft causing a compression of the unpressurized first area is detected when a difference between the theoretical pressure parameter and the actual pressure parameter exceeds a threshold value.

Abstract: A reinforcing arrangement for an opening in an aircraft fuselage structure has a fuselage skin having an inner side, an outer side and a first opening with a first opening contour, and a one-piece reinforcing structure having a thickening section and at least one projecting profile. The first opening contour is surrounded on the inner side of the fuselage skin by an opening edge surface having a thickness corresponding to a thickness of the fuselage skin surrounding the opening edge surface. The thickening section has a bearing surface matched to the opening edge surface and has a receiving section facing away from the bearing surface and surrounding a second opening. The bearing surface is in surface contact with the opening edge surface, and the reinforcing structure is connected to the fuselage skin, with the result that the first opening and the second opening lie one above the other.

Abstract: A seat belt arrangement for a seat assembly of an aircraft for securing a passenger in a seat during travel. The seat belt arrangement comprises: a seat belt including at least a first belt portion to extend across a body part of the passenger seated on the seat; and a fastener member provided on the first belt portion, especially at a first end region of the first belt portion, for operation by the passenger to fasten and to release the seat belt across the body part of the passenger. A second end region of the first belt portion is anchored at a footing of the seat assembly or at a floor structure of the aircraft directly.

Abstract: A wireless aircraft network includes a plurality of aircrafts having transceiver devices for transceiving wireless communication, a plurality of ground-based network stations having transceiver devices for transceiving wireless communication, and a network operator station configured to store location data regarding the current geographical location of the plurality of aircrafts in a location data table of the network operator station and to determine a most efficient network path for each of the plurality of aircrafts to one of a plurality of ground-based network stations depending on the current geographical location of the plurality of aircrafts and the geographical location of the plurality of ground-based network stations.

Abstract: A vortex generator arrangement for an aircraft comprising a surface section forming a flow surface interacting with a flow surrounding the aircraft in operation, wherein the surface section comprises an opening, a vortex generator movable between a retracted position and an extended position, a retainer for holding the vortex generator in the retracted position, a biasing structure for biasing the vortex generator towards the extended position and a release for releasing the vortex generator from the retainer such that the vortex generator can be moved towards the extended position. Further, a sealing membrane is provided completely sealing the opening when the vortex generator is in the retracted position. The vortex generator is movable through the membrane from the retracted position to the extended position. Furthermore, a flow control system, an aircraft and a method of controlling flow are described and claimed.