Abstract: A honeycomb structure including a first external side, a second external side, and an anti-friction agent buffer for receiving an anti-friction agent. An opening to an anti-friction agent inlet and an opening to an air outlet are present on the first external side. This honeycomb structure may be useful in an aircraft as part of a belly-landing system for the aircraft.

Abstract: A dynamically controlled cargo loading system for an aircraft includes electrical cargo conveying devices for conveying cargo items on a cargo loading deck; speed sensors, which are configured to capture current conveying speeds of the cargo conveying devices and/or the conveyed cargo items; electrical measuring devices, which are configured to capture current electrical parameters of the cargo conveying devices; and a control device which is configured to control the cargo conveying devices depending on the captured current conveying speeds and/or the recoded current electrical parameters such that at least one of the following variables is optimized: the electrical power consumption of the cargo conveying devices, the mechanical wear of the cargo conveying devices, the mechanical load action on the cargo items, the conveying time of the cargo items and the noise generation during the conveying of the cargo items.

Abstract: A fairing arrangement for an aircraft high-lift mechanism, the high-lift mechanism including a flap arranged at an aircraft wing trailing edge and a mounting and guiding mechanism for the flap. The fairing arrangement includes a flap side fairing unit and a wing side fairing unit. The flap side fairing unit includes a flap side fairing covering an aft part of the mounting and guiding mechanism and a flap side fairing mount mounting the flap side fairing to the flap. The wing side fairing unit includes a wing side fairing covering a forward part of the mounting and guiding mechanism and a wing side fairing mount mounting the wing side fairing to the wing. The wing side fairing mount is configured to connect the wing side fairing movably to the wing such that the wing side fairing is rotatable around an axis directed at least partially in a vertical direction.

Abstract: A simulation method of simulating correction parameters for aligning a first mating surface of a first section and a second mating surface of a second section of an apparatus or an aircraft airframe, with respect to each other, including obtaining design coordinates of a simulation set of measurement points on the first and second sections, measuring concrete coordinates of some of the measurement points when the first and second mating surfaces are arranged to face each other within a predefined distance range from each other, comparing the design coordinates to the concrete coordinates, and deriving at least one correction parameter from the comparison. An assembly method for assembling a first section and a second section of an apparatus, a corresponding assembly program, a computer-readable data carrier, a computing device and a respective assembly arrangement for assembling a first section and a second section of an apparatus are provided.

Abstract: A bipolar plate for a proton exchange membrane fuel cell includes a laminate of carbon fiber reinforced plastic (CFRP) with a first outer ply. The CFRP includes a resin and carbon fibers. The first outer ply is arranged at a first lateral surface of the laminate, wherein the laminate includes a first plurality of carbon nanotubes (CNTs). The first outer ply includes a first groove, wherein the first groove is configured to define a first gas diffusion channel. At least some of the first plurality of CNTs extend through the first outer ply in a direction transversely to the first lateral surface of the laminate.

Abstract: A wing assembly (5) including: a fixed wing portion (7), a first high-lift device (9), a first connecting assembly (19) which allows the first high-lift device (9) to move between a retracted position and an extended position, a second high-lift device (11), a second connecting assembly (21) which allows the second high-lift device (11) to move between a retracted position and an extended position, a drive unit (23) attached to the fixed wing portion (7), and a drive assembly (25) having a first portion (27) is attached to the drive unit (23) and a second portion (29) attached to the second high-lift device (11), wherein the drive unit (23) moves the second high-lift device (11) via the drive assembly (25) between the retracted position and the extended position.

Abstract: An extinguishing device for an electrical unit on an aircraft cabin monument or in an aircraft structure cavity, a combination of a holder and an extinguishing device and systems formed by extinguishing devices and a control unit and by combinations of an extinguishing device and a holder and a control unit. The extinguishing device has a base element for a holder. An extinguishing agent container has a casing and holds an extinguishing agent. A triggering device is connected to the extinguishing agent container to act in response to receiving a triggering signal wherein an extinguishing agent is released into the extinguishing device surrounding area. A data transmission device has a data store with an identifier unique to the extinguishing device and connected to the triggering device, the data transmission device for sending a warning signal via a network to a control unit in response to the triggering device receiving the triggering signal.

Abstract: An actuation system for a cargo door of an aircraft. The cargo door covers an opening into a cargo bay when it is in a closed position. The actuation system includes a first actuator configured to outwardly rotate the cargo door from the closed position to a first open position, and a second actuator configured to outwardly rotate the cargo door from the first open position to a second open position.

Abstract: A hatch locking device for an aircraft or spacecraft hatch, in particular for a cargo door, includes an actuation lever for actuating the hatch locking device which is rotatable about a pivot axis and includes a protruding section, a latch hinged rotatable about a hinge axis at a hatch frame and engageable with a corresponding latch counter part of a fuselage frame, and a connector mechanically connecting the protruding section and the latch so rotation of the actuation lever causes rotation of the latch. An aircraft or spacecraft hatch including such hatch locking device as well as an aircraft with such an aircraft or spacecraft hatch.

Abstract: A method of opening a cargo door of an aircraft, the aircraft including a body with an opening into a cargo bay, and a cargo door which covers the opening when it is in a closed position. A cargo door is outwardly rotated with a first actuator from the closed position to a first open position. Then an actuator rod is installed by coupling a first end of an actuator rod to the body and coupling a second end of the actuator rod to the cargo door in the first open position. Then the cargo door is outwardly rotated with the actuator rod from the first open position to a second open position by increasing a distance between the first and second ends of the actuator rod.

Abstract: An aircraft wing, including a main wing and a trailing edge high lift assembly movably arranged at a main wing trailing edge, the high lift assembly including a flap and a connection assembly movably mounting the flap to the main wing, such that the flap is movable between retracted and extended positions. In the extended position, a gap is present between a main wing lower rear panel and a flap leading-edge section. In the retracted position, the gap is closed or minimized. The flap is movable between an extended position, a first retracted position, and a second retracted position where the flap is moved beyond the first retracted position in a forward direction, and the wing comprises a gap closing device configured to close or minimize the gap in both the first and second retracted positions of the flap, and to open the gap in the flap extended position.

Abstract: A actuator arrangement is disclosed in which the high-lift device support that supports and guides movement of a high-lift device, such as a flap, is in axial alignment with a control actuator assembly that controls one or more control surfaces. This allows a single support fairing to be sufficient for covering both the track member and the control actuator assembly and allowing for reduced drag and weight.

Abstract: A method for operating a water supply system for an aircraft, as well as a corresponding water supply system operating in accordance with the method and an aircraft having such water supply system. The method includes two operation sequences of a pump and a valve, each sequence including a time delay between operation of the pump and operation of the valve.

Abstract: A device for latching a door of an oxygen mask container in an aircraft cabin includes a door for an oxygen mask container having an inner side, outer side and hinge, a first latching device attached to the inner side, and a second latching device movable relative to the first latching device to selectively engage or disengage the second latching device. A retaining element is attachable to a structural part inside the oxygen mask container. A test control device on the inner side of the door includes a movable hook element and can move the hook element to a first or second position. The hook element can engage the retaining element in the first position to restrict an opening degree of the door. The hook element is placed in the second position such that when the door is opened, the hook element is moved past the retaining element.

Abstract: An unmanned ground-based transport vehicle, UGV, includes a housing, having a base plate and at least one housing side wall substantially perpendicular to the base plate. Arranged in the housing is at least one wheel drive, which is coupled to at least one wheel. The wheel is arranged in a recess in the base plate. The UGV further includes sensors for sensing the environment of the UGV, and a controller for autonomous location and navigation of the UGV on the basis of sensing parameters of the sensors. The UGV includes at least one load-receiving element coupled to the housing side wall and extending outwards from the housing side wall, wherein the load-receiving element includes a load support surface for supporting an item with respect to a vertical direction which extends transverse to the base plate.

Abstract: A wing for an aircraft includes a leading edge as a first chordwise edge, a trailing edge as a second chordwise edge, an upper skin extending between the leading edge and the trailing edge, a lower skin extending between the leading edge and the trailing edge, at least one spar extending between the upper skin and the lower skin in a spanwise direction to create wing box with the upper skin and the lower skin, and at least one of a fluid line, an electrical line, and a mechanical power transfer device attached inside or reaching into the wing box at least partially.

Abstract: An aircraft tank device for increasing a flight range and a wing area of an aircraft includes a fairing which is formed and configured to at least partly cover an aircraft wing-aircraft fuselage intersection, to store a fuel, and to provide a lifting function. An aircraft including such an aircraft tank device is also disclosed.

Abstract: An aircraft refrigeration system comprises an ambient air line, through which ambient air flows and which is connected to conduct ambient air to an aircraft, an ambient air compressor, arranged in the ambient air line, for compressing the ambient air in the ambient air line, a cabin exhaust air turbine, connected to a cabin exhaust air line and coupled to the ambient air compressor in the ambient air line and configured to expand cabin exhaust air flowing through the cabin exhaust air line and to drive the ambient air compressor, a transmission, configured to couple the cabin exhaust air turbine to the ambient air compressor and to set a speed of the ambient air compressor, and a motor, coupled to the transmission and configured to drive the ambient air compressor.

Abstract: An air distribution system for a cabin of an aircraft includes a supply air line with a supply air line connector, at least one air outlet with an air outlet connector, a riser line, which is connectable to the supply air line connector and the air outlet connector, and a trim element to be arranged on a primary structure of the aircraft inside the cabin. The riser line is flexible, wherein the trim element has an outer side which can be oriented relative to the primary structure and on which there is at least one retainer for retaining the riser line, and the at least one retainer is designed to be interlockingly connected to the riser line by being pressed against the latter, such that the riser line is fixed.

Abstract: An aircraft with an aircraft fuselage, and a passenger cabin and a cockpit, where the aircraft includes a center-forward attendant space between the passenger cabin and the cockpit. A cabin crew member of the aircraft can stand in the center-forward attendant space for monitoring progress of an emergency evacuation of the aircraft. The aircraft has one or more emergency exits for providing egress of passengers from the aircraft fuselage during the emergency evacuation. The aircraft also has a situational awareness monitoring (SAM) system for use in evacuating the passengers from the aircraft during the emergency evacuation. The SAM system includes one or more imaging devices and one or more display modules, each of which displays within the passenger cabin images captured by a corresponding one of the one or more imaging devices.