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: A freight container configured to fit in an aircraft cargo hold includes a floor element. First and second parallel side walls extend away from first and second opposite edges of the floor element base surface. A top wall, parallel to a floor element resting surface, extends between edges of the first and second side walls, which edges are remote from the first and second edges. A front wall extends between the first and second side walls from a base surface third edge to a top wall front edge. The front wall has a first front wall portion, extending from the base surface third edge at a first angle of at least 90° to the resting surface. The front wall has a second front wall portion, extending from the top wall front edge at a second angle of less than 180° and more than 90° to the top wall.

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: A floor system for a cabin of a vehicle is proposed, the floor system including a floor panel having a bottom layer, a top layer and a continuous stiffening structure having an alternating arrangement of elongated first depressions and elongated protrusions arranged between the bottom layer and the top layer, an elongated cover component, and at least one seat rail component. The cover component has an upper surface, a lower surface, and an elongated second depression reaching from the upper surface to the lower surface and having a shape that corresponds to the shape of the first depressions. The cover component is configured to be mounted inside a first depression that is accessible through an elongated cutout extending along a depression of the stiffening structure. The at least one seat rail component is attachable to the cover component to provide a seat rail along the floor panel.

Abstract: A primary structural assembly for an aircraft outside-skin heat exchanger, the assembly comprising an outer-skin portion which defines an outer shape of the aircraft and forms a portion of a hull of the aircraft, wherein the outer-skin portion comprises at least one recess, a thermal-transfer fluid connection which is designed to convey a thermal-transfer fluid into the recess, a component which closes the recess, and at least one retaining element which is arranged in or on the recess and is configured to hold the component closing the recess, in the recess. Further, an aircraft including such a primary structural assembly and a method for attaching the aircraft outside-skin heat exchanger are disclosed.

Abstract: In order to enlarge a tank volume of a hydrogen powered aircraft, an aircraft tank for storing cryogenic H2 is configured as a non-circular dorsal tank. The aircraft tank may be configured as a conformal fuel tank fitted to an outer contour of an aircraft fuselage. Further, an aircraft is provided with such an aircraft tank.

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.

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 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 aircraft cabin section with an aircraft door, a cabin floor, and at least one lining mounted to the aircraft door. The aircraft cabin section further comprises at least one seal that is mounted to the at least one lining and seals a space between the at least one lining and the cabin floor. This prevents a cold air draft from entering the aircraft cabin.

Abstract: A panel for covering a part of a structure in an interior space of an aircraft is disclosed including a main panel section having an interior side and an exterior side, and at least one attachment device coupled with the exterior side. The main panel section is exclusively made from a single thermoplastic material, and the at least one attachment device is adapted for attaching the panel to the respective interior structure.

Abstract: A sealing device for covering an aperture in a wing part of an aircraft is disclosed having an interface section for fixedly mounting the sealing device to a surface of the wing part adjacent the aperture, a connecting section, and a cover section for covering at least a part of the aperture. The connecting section is arranged between the interface section and the cover section and connects the interface section and the cover section. The connecting section is adapted to resiliently hold the cover section in a predetermined orientation relative to the interface section to cover at least a part of the aperture. The cover section comprises a contact portion for contacting a surface of an actuation element that protrudes through the aperture.

Abstract: A method and apparatus for cutting a Non-Crimp Fabric for improving edge stability and reducing stitch retraction is disclosed. The part of the NCF to be cut is treated with a binder and heated to activate the binder and therefore bind the tows and stitches together. By treating only the cutting path the drapability of the wider fabric is maintained. This may be achieved by heating only the part of the NCF to be cut, or applying binder to only the part of the NCF to be cut. The NCF may be compressed and cooled before cutting to improve binding action. A ply cutter may be adapted to carry out the invention by including a heat source and optionally a binder dispenser, compressor and cooler.

Abstract: An avionics network including a plurality of avionics components and a configuration monitoring device, which is connected by wire or wirelessly to the plurality of avionics components. The configuration monitoring device has at least one configuration data interface configured to receive a plurality of configuration parameters characterizing the operating status of the avionics components. The configuration monitoring device further includes a parameter filtering device connected to the configuration data interface and configured to filter a subset of the configuration parameters received.

Abstract: A method for producing an armored wall for an aircraft by determining an available thickness of the wall, an allowable areal mass of the wall, and an available space for a wall deformation due to ballistic impact. The method includes retrieving a parameterization of a plurality of armoring materials, which includes a parameter for each of a plurality of material characteristics for each of the plurality of armoring materials. The method also includes comparing the available wall thickness, the allowable areal mass, and the available deformation space with a corresponding parameter of the parameterization, selecting one armoring material for the wall from the plurality of armoring materials based on a result of comparing, and manufacturing a wall by supplementing the selected armoring material to a basic wall structure.

Abstract: A clamping apparatus connecting tube flanges, includes first and second bracing devices. The first bracing device connects first and second mounting devices and has a partially circular shape with a first inner and a first outer wall. The second bracing device connects first and second connecting devices. The first bracing device inner wall has a first recess. The first bracing device outer wall is configured to contact the second bracing device which is configured to contact the first bracing device outer wall to apply substantially radial force on that first outer wall. The first recess shape is configured to substantially convert the radial force applied to the first bracing device outer wall into an axial force inside the first inner wall. The first and second mounting devices each comprise at least two attachment devices connecting the first and second connecting devices of the second bracing device.

Abstract: A support for coaxial flanges of a double-coaxial coupling includes a circular support structure providing a primary mounting zone for attaching a primary flange for connecting a primary outer tube, and a secondary mounting zone for attaching a secondary flange for connecting a coaxial secondary inner tube. The primary and the secondary mounting zones are spaced apart from each other in a radial direction for centering the primary and the secondary flanges in a radially spaced coaxial manner. The primary mounting zone provides an outer circumferential connection region with at least three mounting points for attaching the primary flange. The secondary mounting zone provides an inner circumferential connection region with at least three mounting points for attaching the secondary flange. A thermal path within the circular support structure between the mounting points of the primary and secondary mounting zones is longer than the distance between the two points.

Abstract: An aircraft fuselage includes fore and aft sections, a barrier wall separating the sections and an opening therebetween, a rail attached to the barrier wall, a door moveable across the barrier wall between an open position offset from the opening and a closed position covering the opening, a first roller and a second roller rotatably fixed to the door and moveable on the rail along first and second paths to move the door, the rail including a first ramp engaging the first roller as it moves along the first path and to direct the first roller towards the barrier wall, and a second ramp engaging the second roller as it moves along the second path and to direct the second roller towards the barrier wall, the first roller configured to engage the first ramp as the second roller engages the second ramp to move the door towards the barrier wall.

Abstract: An actuator assembly for moving a movable aerodynamic surface of an aircraft is disclosed including an input section for introducing an externally provided rotary motion into the actuator assembly, and a geared rotary actuator having at least one actuator slice having a planetary gear with a sun gear couplable to the input section, a fixed gear attachable to a fixed component of the aircraft and an output gear couplable with the movable aerodynamic surface. At least one clutch is connected to the geared rotary actuator and is configured to couple the movable surface with the input section and to selectively decouple the movable surface from the input section, such that it is freely movable.