Abstract: A die tool for forming a C-section component having radiused shoulders has first and second outer dies, each outer die having a truncated conical portion connected to a flange portion by a radiused portion and being symmetrically disposed to one another along a common axis such that each flange portion is outermost, and a cylindrical outer support die located between the first and second outer dies.
Abstract: A method of curing a composite material. A tool is heated using microwaves. At least a part of the composite material is shielded by reflecting microwaves away from the composite material with a shield. Heat is transferred from the tool through the shield to the composite material. The tool comprises a material which is sensitive to microwaves so that, when microwaves are incident upon the tool, some of the microwaves are absorbed by the microwave-sensitive material, thereby heating the tool.
Abstract: A guiding mechanism is disclosed for moving a cargo door into extended cargo door positions to open and into a retracted cargo door position to close at least one section of an opening of a loading hatch on a fuselage of an aircraft. A first structural component in the form of the cargo door is pivotably supported on a second structural component on a front lateral edge by a pivot joint arranged in a pivoting axis in order to assume the extended cargo door positions on the loading hatch. The guiding mechanism features at least one actuator for moving the cargo door, a supporting device arranged on an actuating element, and a spring mechanism on the actuator for exerting a compressive force.
Abstract: The invention discloses a method for prevention of porosity in composite material parts (1), which is applied when the curing stage of the part (1) is being carried out on a female tool (2). In the curing stage, an adhesive (4) is placed on at least one of the areas of the radii (5) of the composite material part (1), so that the possible subsequent appearance of porosity in said areas of the composite material part (1) is prevented. Thus, the adhesive (4) acquires the fluidization temperature before the resin of the composite material and it is displaced filling the holes generated during the placement of the part (1) on the female tool (2), in the area of the radii (5) of the part (1), during the coupling between the part (1) and the female tool (2).
Type:
Application
Filed:
April 26, 2013
Publication date:
October 31, 2013
Applicant:
Airbus Operations, S.L.
Inventors:
Jose David CANO CEDIEL, Pedro Nogueroles Vines
Abstract: A noise reduction unit for inserting in a vacuum suction drain is adapted to be flown through by a material to be conveyed through the vacuum suction drain and comprises an inlet section with a first diameter, a middle section with a second diameter and an outlet section with a third diameter. The middle section is adapted to affect a flow velocity reduction of the material to be conveyed such that the noise level arising during the conveying process is being reduced.
Abstract: A system for the contactless transfer of energy and data includes a transfer path with a primary coil and with a secondary coil. The primary control unit is designed to lead data-modulated first alternating-voltage signals of a first frequency range into the primary coil. The secondary control unit is designed to receive the first alternating-voltage signals of the first frequency range from the secondary coil, and to demodulate the modulated-on data. The system further includes a feed-in line for feeding a second alternating-voltage signal of a second frequency range to a primary line leading to a primary coil and an activation line that is connected to a secondary line that is connected to the secondary coil. A first filter filters the second alternating-voltage signal from the secondary line and provides the signal to an activation connection.
Abstract: A passenger service system includes an individual ventilation arrangement and/or a lighting arrangement, wherein at least one air nozzle of the individual ventilation arrangement and/or at least one reading lamp of the lighting arrangement is/are disposed in the region of a service surface of the passenger service system, The service surface of the passenger service system includes a substantially flat portion as well as a buckled portion, which is curved convexly relative to the substantially flat portion and extends along a longitudinal axis (LP) of the passenger service system.
Abstract: A machining method for machining a superficial portion of a laminate using machine tool having a depth limiter which restricts a maximum depth of the machine tool. A guide frame having an inner guide contour restricts a maximum dimension of the superficial portion, and is secured over the superficial portion. The superficial portion is machined while the machine tool is guided by the guide contour. From another point of view, a machining apparatus for machining a superficial portion of a material is provided. The machining apparatus comprises a guide frame, an inner guide contour for guiding a machine tool, an attachment member for securing the guide frame to an attachment member, adjacent to the superficial portion, of the material.
Abstract: An energy supply system for an aircraft comprises at least one fuel cell and at least one energy storage device, wherein the fuel cell, of which there is at least one, is coupled to the energy storage device, of which there is at least one, such that the energy storage device can be charged by means of the fuel cell.
Abstract: The invention concerns a pressurized flooring for aircraft, provided with beams (1) including an upper sole (2), a vertical web plate (3), and a lower sole (4), the lower sole being provided with two oblique feet (7, 8) arranged on both sides of the vertical web plate and presenting a support surface (14, 15) provided for supporting pressurized curved membranes (9), characterized in that the lower sole includes a linking element (10) connecting the two oblique feet, so that said lower sole presents an enclosed section. Such a structure can be advantageously realized in composite material.
Abstract: A method of forming a rib-spar joint during assembly of an aircraft wing, the method comprising: providing a spar with a fixedly attached rib post, the rib post having a first coordination feature; providing a rib having a web with a first tooling feature; providing a tooling component having a second tooling feature for cooperating with the first tooling feature, a second coordination feature for cooperating with the first coordination feature, and a plurality of drill bushings; fixedly attaching the tooling component to the rib web by aligning the first and second tooling features; aligning the rib with the spar by aligning the first and second coordination features; drilling fastener holes in the rib and the rib post off the drill bushings of the tooling component; removing the tooling component from the rib web; and fastening the rib to the rib post using the fastener holes to form a rib-spar joint. The method may be applied to form front and/or rear rib-spar joints.
Abstract: A seat rail for attaching seats in aircraft is provided. The seat rail includes a profile element for attaching the seats, and a support element for attaching the seat rail in an aircraft. At least the support element is manufactured from aluminum or an aluminum alloy. The surface of the aluminum or the aluminum alloy includes, an oxide layer, and the oxide layer has been manufactured by means of hard anodic oxidation.
Type:
Grant
Filed:
August 31, 2010
Date of Patent:
October 29, 2013
Assignee:
Airbus Operations GmbH
Inventors:
Thorsten Roming, Gastao De Freitas, Daniel Heydorn
Abstract: A method for transmitting data, a receiving method, related devices, and an aircraft equipped with the devices. The method includes determining an authentication word of the data; processing the data to obtain processed data; and transmitting the processed data on a transmission channel.
Abstract: The invention relates to a cover panel for an aircraft, comprising a decompression opening that can be closed by a decompression flap that comprises a membrane, and a ventilation opening that is provided separately in the cover panel and that is permanently open. Furthermore, the invention relates to an aircraft fuselage comprising such a cover panel.
Abstract: The object of the invention is an aircraft nacelle that comprises at least one part, called a door (14), that moves relative to a stationary part (20) and a connecting device that makes it possible to limit the offset between said door and said stationary part in a direction that corresponds to the primary direction of the flow of air outside of the nacelle during flight, whereby said device comprises, on the one hand, an indexer (40) that is connected to the door (14) that comprises an attachment surface (63) and at least one attachment element (66), and, on the other hand, at least one stop (58) that is connected to the stationary part (20) against which said indexer (40) can rest in such a way as to limit its movement in said direction, characterized in that said at least one attachment element (66), oriented in the radial direction, is arranged upstream from the stop (58) in said direction, said at least one stop (58) comprising a surface relative to the door arranged essentially at the attachment surface
Type:
Grant
Filed:
January 18, 2011
Date of Patent:
October 29, 2013
Assignee:
Airbus Operations SAS
Inventors:
Alain Porte, Jacques Lalane, Franck Alvarez
Abstract: The invention relates to a section of fuselage for an aircraft, including frames and bays for receiving cabin windows. According the disclosed embodiments, at least some of the frames include at least one frame segment that surrounds at least one bay, the frame segment having two branches that are disposed to the side of the bay. The ends of the branches are attached to each of the ends of the frame segment such as to form a Y.
Type:
Grant
Filed:
January 3, 2008
Date of Patent:
October 29, 2013
Assignee:
Airbus Operations (S.A.S.)
Inventors:
Guillaume Gallant, Damien Aguera, Philippe Bernadet
Abstract: A trailing edge flap arrangement for an aircraft wing, comprising an array of flap elements each discretely moveable between a retracted and an extended position by a respective actuator, wherein the flap elements are arranged to be deployed so as to open up a through slot between an adjacent pair of the flap elements only when the aerodynamic leading element of the pair has reached its extended position. Also, a method of operating the trailing edge flap arrangement.
Abstract: A fire protection system for reducing the danger of fire, which has a fuel cell for producing a nitrogen-enriched cathode exhaust air. The fuel cell is supplied with air and a fuel. Within the fuel cell, the air is then reduced to a determined oxygen content. The exhaust air is supplied to the room to be protected.
Type:
Grant
Filed:
July 30, 2012
Date of Patent:
October 29, 2013
Assignee:
Airbus Operations GmbH
Inventors:
Julika Bleil, Lars Frahm, Andreas Westenberger, Claus Hoffjann
Abstract: The invention relates to a flight control system for an aircraft comprising control surfaces and actuators associated with the control surfaces to control flight functions, including roll, yaw, pitching, and aerodynamic braking of the aircraft. The actuators associated with the control surfaces that control at least one of the flight control functions are electromechanical actuators. A part of the control surfaces associated with the electromechanical actuators is divided, where each of the divided control surfaces is comprised of at least two independent surfaces.
Type:
Grant
Filed:
January 4, 2011
Date of Patent:
October 29, 2013
Assignee:
Airbus Operations S.A.S.
Inventors:
Marc Fervel, Arnaud Lecanu, Antoine Maussion, Laurent Andrieu
Abstract: The invention relates to a mixing system for inerting a gas volume. A first exhaust gas that is provided by a fuel cell, and a second exhaust gas that is provided by a hydrogen reformer, can be mixed to form an inert gas mixture. The mixture can be fed into the gas volume for inerting.
Type:
Grant
Filed:
March 3, 2009
Date of Patent:
October 29, 2013
Assignee:
Airbus Operations GmbH
Inventors:
Heinz-Detlef Naeve, Juergen Friedrich Haastert, Lars Frahm