Abstract: A method of servicing an aircraft cooling system comprises connecting a refilling container containing a two-phase refrigerant to a refrigerant connection provided in a cooling circuit of the cooling system, supplying refrigerant from the refilling container into the cooling circuit of the cooling system, and operating a condenser disposed in the cooling circuit so as to liquefy gaseous refrigerant flowing through the cooling circuit.
Abstract: A surface element, e.g. a wing, of an aircraft includes a leading edge, a high lift device arrangement positioned along the leading edge and at least one add-on body positioned in a leading edge region, wherein the high lift device arrangement is interrupted in the region of at least one add-on body for preventing collision with the add-on body and wherein the surface element includes an arrangement of openings in a region covering the add-on body, which openings are connected to an air conveying device for conveying air through the openings. Thereby an additional flap for harmonizing the flow above a pylon or other add-on body can be eliminated.
Abstract: A load introduction element for a movable surface of an aircraft comprises a load introduction body that is connectable with the surface. A fitting connected with the load introduction body with a first section and a second section. The first section comprises a first bearing means, the second section comprises a second bearing means, and the first or second section comprises a third bearing means. The fitting is pivotally connected with the load introduction body by way of the first bearing means. An adjustment unit connects the second bearing means with the load introduction body in a variable position and is positioned on a side of the load introduction body that is opposite the fitting. In this manner adjustment of a reference position of a surface takes place without the need for an access flap. By loosening the adjustment unit the movable surface is pivotable without moving a flap drive.
Abstract: According to an exemplary embodiment of the invention, pre-assembly and integration of part of an aircraft cabin takes place outside the aircraft structure by means of an assembly device. After pre-assembly, the part of the aircraft cabin is slid into the open section of the aircraft structure where it is installed.
Type:
Grant
Filed:
August 3, 2009
Date of Patent:
March 4, 2014
Assignee:
Airbus Operations GmbH
Inventors:
Christoph Blees, Niklas Halfmann, Dieter Krause, Marcus Gehm
Abstract: An area-expandable monument is provided for a cabin of a vehicle that includes, but is not limited to two housing parts that are displaceable relative to each other and can be fastened. A gap between the housing parts in an expanded state can be covered by a covering element. In the monument, a first sanitary fixture could be arranged whose position adapts to the spatial state of the monument. Optionally, there is also a pivotable second sanitary fixture that can be activated with the monument in its pushed-out state.
Type:
Grant
Filed:
January 23, 2012
Date of Patent:
March 4, 2014
Assignee:
Airbus Operations GmbH
Inventors:
Jürgen Tappe, Christian Holst, Ralph Sturm, Gregor Behlau, Michael Waller, Frank Trautmann, Arne Terstal
Abstract: An energy absorber for aircraft, which includes one or more energy absorber elements and a housing, whereby the energy absorber elements can absorb crash impulses by plastic deformation within the housing. Thus, the load on the primary structure and the respective inboard devices is limited, which can lead to an increased, passive safety of the passengers and a weight reduction.
Type:
Grant
Filed:
February 8, 2007
Date of Patent:
March 4, 2014
Assignee:
Airbus Operations GmbH
Inventors:
Dirk Humfeldt, Michael Harriehausen, Jan Schröder, Martin Sperber, Michael Demary
Abstract: The present invention provides a method for the production of a fiber-reinforced plastics material profiled part. The method comprises the supplying of a tubular fiber braid in which a polymer matrix is arranged by being distributed therein. A longitudinal portion of the fiber braid is enclosed in a molding press. The molding press is heated to cure the polymer matrix in the longitudinal portion. After the press is opened, the fiber braid is drawn through the open press in order to position a further longitudinal portion of the fiber braid in the molding press. The further longitudinal portion is enclosed in the press. Another aspect of the invention is the provision of a device for the production of a fiber-reinforced plastics material profiled part.
Abstract: Awing box of an aircraft with a stiffened shell structure, consisting of fiber reinforced material includes a skin for absorbing shear loads, and several stringers arranged on the inner side of the wing box for absorbing axial loads, in which at least 60% of the mass of the stiffened shell structure is concentrated in the stringers, wherein the stringers provide at least 80% of the axial stiffness of the stiffened shell structure. In the specific case of wing structure, this embodiment allows the use of unbalanced laminates for the skin to induce higher nose-down twist of the wing box without any loss in bending stiffness and so envisaging higher weight saving capability.
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, wherein the edge of the pressure bulkhead is circumferentially attached to the fuselage structure by fastening means, wherein the fastening means include a pair of ring-shaped attachment frames made of an open or hollow profile, which are disposed at each side of the pressure bulkhead respectively, in order to form a clamping connection for the pressure bulkhead towards the fuselage structure.
Abstract: The present invention provides a door frame construction in particular for an aircraft or spacecraft, including a former; a fibre metal laminate which is connected to the former; and an outer skin which is connected to the fibre metal laminate.
Abstract: A high lift component includes at least one intermediate seal on at least one lateral surface, wherein the intermediate seal includes at least one hollow body made of an elastic material, which hollow body includes a fluid inlet that is connectable to a fluid source. A gap between two high lift components, which gap is subjected to dynamic changes in geometry, can be flexibly sealed in this manner.
Abstract: A cabin segment for a vehicle includes two or more parking spaces, arranged side by side and separated from each other by at least one intermediate wall, for accommodating serving trolleys, and furthermore a vehicle attendant seat which on one side is held on one of the at least one intermediate walls so as to be pivotable on an axis. The vehicle attendant seat is pivotable to an in-use position and to an out-of-the-way position. The in-use position and the out-of-the-way position are situated apart by 90° or more relative to the pivoting of the vehicle attendant seat. This makes possible particularly efficient use of space without having to forego parking spaces or a vehicle attendant seat.
Abstract: A method for manufacturing a solid oxide fuel cell element by layer-wise buildup wherein at least one section of the element is built up by carrying out a step that at least includes the following at least once: applying a layer section of a particulate ceramic material with predefined dimensions onto a base layer in a predefined area and heating the layer section by means of a heat source such that the particles of the ceramic material connect to one another within the predefined dimensions. The solid oxide fuel cell element manufactured with the method is realized in one piece, as well as highly compact, and has a low weight.
Type:
Application
Filed:
October 21, 2013
Publication date:
February 20, 2014
Applicant:
AIRBUS OPERATIONS GMBH
Inventors:
Jürgen Steinwandel, Christian Wolff, Claus Hoffjann
Abstract: A drive unit includes a combustion chamber for combusting a fuel/air mixture, and a fuel cell device, wherein the fuel cell device includes at least one fuel cell, which in each case includes an anode that is couplable to a fuel line, a cathode that is couplable to an air source, and a fluid outlet and is arranged upstream of the combustion chamber. The combustion chamber further includes a combustion chamber inlet for supplying the fuel/air mixture, and a combustion chamber outlet for discharging exhaust gas, and the combustion chamber inlet is connected to the fluid outlet of the fuel cell device. In this way a hybrid drive unit can be provided which apart from mechanical power also generates electrical power at high efficiency.
Type:
Application
Filed:
October 21, 2013
Publication date:
February 20, 2014
Applicant:
AIRBUS OPERATIONS GMBH
Inventors:
Jürgen Steinwandel, Christian Wolff, Claus Hoffjann
Abstract: Structural component including at least one covering shell and a carrier structure, the covering shell designed in the form of a sandwich and formed by an inner skin section, an outer skin section and a shear-load absorbing core layer disposed between the two sections and connecting the inner and the outer skin sections to one another in a planar manner. The carrier structure is formed by at least one panel-shaped connecting part extending between and transversely to the inner and outer skin sections and connected along a reference longitudinal direction to the covering shell. The connecting part is located outside the carrier structure and fastened to the inner skin section resting thereon in a planar manner, wherein at least one profiled support extending along the reference longitudinal direction is provided in the covering shell in order to form a reinforcing section in the connecting region of the panel-shaped connecting part.
Abstract: A high lift system for an aircraft includes a basic body, a flap which is movably mounted on the basic body and has a flap edge, and a retaining element. The high lift system is set up to form a gap between the flap edge and the basic body. The retaining element is mounted on a region of the flap close to the flap edge and extends towards the basic body to restrict the distance between the flap edge and the basic body. The retaining element is preferably configured as a linear attachment means. Consequently, a gap dimension between a flap and a basic body can be influenced to restrict flexing effects during loading of the flap and of the basic body.
Abstract: A vacuum toilet unit having a urinal function with reduced noise emission, system design size and system weight, in which vacuum toilet unit a triggering device for triggering the vacuum valve is adapted in such a manner that the triggering unit may not be triggered when a sit-down toilet is in use as intended.
Abstract: An ice separator is provided that includes, but is not limited to at least one curved airflow deflection surface. The ice separator includes, but is not limited to an inflow aperture with a downstream trapping pocket at the airflow deflection surface, in which trapping pocket ice particles from an airflow flowing onto the ice separator are trapped due to their inertial forces. In this way with simple means an effective device for removing ice particles from airflow may be achieved.
Abstract: The present invention provides a fireproof bulkhead, having a highly porous structure with an intumescent coating, the highly porous structure being formed as a reticulated foam or as a highly porous pimple or nub structure.
Abstract: A fuselage section for the pressure fuselage of an aircraft which comprises a fuselage shell structure and at least one pressure bulkhead made of a fiber composite material, the pressure bulkhead being formed in one piece with the fuselage shell structure. A fuselage shell comprising at least one fuselage section of this type.