Airbus Operations Patente

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An interior component (100) for an interior room of an aircraft is provided. The interior component comprises a body (103) having a first surface (106) and a second surface (108) and a multitude of functional modules (130A, 130B, 130C, 130D, 130E) which form a passenger service unit. The second surface (108) is arranged opposite to the first surface (106) and comprises a recess (110). The multitude of functional modules are arranged one after another in the recess in the longitudinal direction (301) of the interior component, such that a first front surface (147) of the functional module (130A) arranged frontally in the longitudinal direction (301) closes flush with a first front surface (114) of the body (103).

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A beam flange clamp (10) includes a clamp body (1) having a first vise jaw portion (3) with a first gripping surface (5) and a second vise jaw portion (2) with a second gripping surface (4). The first gripping surface (5) and the second gripping surface (4) are oriented parallel to each other, are facing the same direction and are offset in height by a predetermined clamping distance. The at least one bolting hole (6) is formed through the first vise jaw portion (3) perpendicularly to the first gripping surface (5).

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The present disclosure pertains to a safeguarding arrangement (10) for restricting the movability of at least one transport container (17) storable or stored in a reception (16) of a support structure (14). The mentioned transport container (17) may be used for the transport of goods, for example, in an aircraft, and may be stowed in the area of the aircraft's galley as a so-called trolley (18, 19). The safeguarding arrangement (10) has a first safeguarding installation (11) with at least one first safeguarding means (12). The at least one first safeguarding means (12) allows a the supply or the retraction of the at least one transport container (17) into the reception or from the reception, respectively, in its open position via an opening (15). At this the safeguarding means (12) overlaps a clean measure of the opening (15) of the reception (16) at least zonally in a hold position, in which the at least one transport container (17) is held against retraction from the reception (16). Further, the first safeguarding means (12) is formed variably with regard to its engagement depth into the reception (16).

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Described and illustrated is a floor panel (1) for an aircraft, said floor panel (1) comprising a panel structure (3) for transmitting forces applied to the floor panel (1), wherein the panel structure (3) includes an upper cover layer (7), a lower cover layer (9), and a core assembly (11) sandwiched between the upper and lower cover layers (7, 9), and a heater layer (5) for heating the floor panel (1), wherein the heater layer (5) is provided between the upper and lower cover layers (7, 9). The object of the present invention, to provide a possibly simple heated floor panel for an aircraft, wherein the risk of overheating and at the same time the risk of local hot spots at the heater layer is reduced, is achieved in that the heater layer (5) is formed as a PTC-layer having a plurality of electric conductor paths (27) interconnected to one another by a plurality of PTC-resistor paths (29) comprising a PTC-material, wherein the electric resistance of said PTC-Material increases with increasing temperature.

The invention relates to a panel structure (1) for a vehicle, and especially for an aircraft (A) or spacecraft, comprising: an area member (2), especially a skin member, that defines an areal expanse with a first surface (3) and an opposite second surface (4) and having a thickness (5) between the first and second surfaces (3, 4); and a plurality of elongate stiffener members (6) which are attached to the area member (2) and extend over at least one of the first and second surfaces (3, 4); wherein at least one of the stiffener members (6) is bifurcated at a bifurcation point (P) into two or more branch stiffener members (6'). The invention also provides a method of producing such a panel structure (1).

A fixed wing aircraft has a wing with an aerofoil cross-section defining an upper geometric surface and a lower geometric surface which meet at a geometric leading edge of the wing at the intersection with the aerofoil geometric chord. The wing is configured to define an upper aerodynamic surface and a lower aerodynamic surface when the wing is moved through air. The upper aerodynamic surface and the lower aerodynamic surface meet at an aerodynamic leading edge of the wing at the intersection with an attachment line dividing the air that passes over the upper aerodynamic surface from the air that passes over the lower aerodynamic surface. The lower geometric surface adjacent the geometric leading edge has a roughness strip with a step height of at least 50 microns over the lower geometric surface. The roughness strip is located on the lower aerodynamic surface of the wing when the aircraft is flown at a load factor -the ratio of the lift of the aircraft to its weight - of 1g, and the roughness strip is located on the upper aerodynamic surface when the aircraft is flown at a load factor of 1.2g or more.

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A smoke detection system (10) comprises at least one smoke detector (12) which is installed in a first partial region (110) of a region (100) to be monitored by means of the smoke detection system (10). The smoke detection system (10) further comprises at least one fluid injection device (14) which is configured to inject a fluid into the region (100) to be monitored by means of the smoke detection system (10) in a direction of at least one smoke detector (12) such that in an emergency case, when smoke (116) is present in a second partial region (112) of the region (100) to be monitored the smoke (116) is transported to the at least one smoke detector (12).

A flow body (34) of an aircraft comprises a flow surface (46) exposed to an airstream during flight of the aircraft, at least one structural component (38) attached to an interior of the flow surface (46), at least one perforated area (12) comprising a plurality of openings extending through the flow surface (46), a manifold (36) positioned interior to the flow surface (46) in fluid communication with the openings and upstream of the at least one structural component (38), and at least one suction duct having a first end and a second end, the first end being in fluid communication with the manifold and the second end placed exterior to the flow surface (46) downstream of the at least one structural component (38). The at least one suction duct (42, 44) comprises a suction opening (56, 58) facing away from the first end. Further, the suction opening is adapted for inducing a suction force into the at least one suction duct (42, 44) when the flow surface (46) is exposed to an airstream during flight, thereby inducing a flow of air from through the openings to the suction opening (56, 58).

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