Abstract: A composite material part and method for manufacturing the part. The part has a large variation in thickness between a first zone having a thickness E1 and a second zone having a thickness E2, which is made as a single part with a transition zone, external surfaces of which have gradients of magnitude, in which the structure of the stack includes; b1) a plurality of continuous plies that extend in the three zones; b2) a plurality of plies that extend in the first zone and in the transition zone, terminating in a stepped manner in the transition zone; b3) a plurality of plies that extend in the first zone and in the transition zone, terminating in a stepped manner in the transition zone.
Type:
Grant
Filed:
May 5, 2010
Date of Patent:
October 7, 2014
Assignee:
Airbus Operations, S. L.
Inventors:
Jose Luis Lozano Garcia, Jose Orencio Granado Macarrilla, Vicente Martinez Valdegrama
Abstract: An aircraft nacelle that makes it possible to channel a stream of air in a longitudinal direction and that includes at least two panels (50, 50?) placed end to end in the longitudinal direction, each including a so-called aerodynamic surface (52, 52?) that is in contact with the air stream and an edge (54, 54?) that is in contact with the edge of the other panel, characterized in that at least one of the panels includes—at its edge (54, 54?)—at least one partition (58) that projects relative to the edge that extends in the direction of the edge of the other panel, in a manner that is secant to the aerodynamic surface and in a plane that contains the longitudinal direction, so as to limit the circulation of air between the edges of the panels.
Type:
Grant
Filed:
October 11, 2011
Date of Patent:
October 7, 2014
Assignee:
Airbus Operations (S.A.S.)
Inventors:
Alain Porte, Jacques Lalane, Frederic Chelin, Thierry Surply
Abstract: A communication method on a communication link between an aircraft and a ground station, the communication capable of being configured according to a plurality of safety levels in which, when the aircraft sends a request to a ground station to modify the safety level of the communication from a previous safety level to a new safety level and the aircraft does not receive an acknowledgement of the request by the ground station, the aircraft still accepts messages from the ground station according to the new security level.
Abstract: A landing gear attachment apparatus (100) has a landing gear side bearing retention arrangement (104) connected to an aircraft side attachment apparatus (102), held together by a series of fuse pins. The interaction between a fuse pin carrier and a trunnion block varies the amount of load required to separate the landing gear from the fuselage depending on the direction of the load.
Type:
Grant
Filed:
August 8, 2012
Date of Patent:
October 7, 2014
Assignee:
Airbus Operations Limited
Inventors:
Andrija Ekmed{hacek over (z)}ić, Mario Straccia, Philip Jones
Abstract: A bonding lead comprising a core; and a sheath bonded to the core. The core comprises a substrate of fibers coated with nano-objects with at least one dimension between 1 nm and 200 nm. The nano-objects form a continuous electrically conductive network from one end of the bonding lead to the other with some of the nano-objects coating the fibers and others forming bridges between adjacent fibers. The nano-objects may be carbon nanotubes and the core may be woven or knitted. A conductive connector is provided at each end of the bonding lead, for instance a tab formed from an electrically conductive polymer. The lead can be used to dissipate static charge and/or lightning current between components, typically within an aircraft fuel tank.
Type:
Grant
Filed:
August 18, 2011
Date of Patent:
October 7, 2014
Assignee:
Airbus Operations Limited
Inventors:
Andrew Paul Limmack, David Alistair Sutton, Colin John West
Abstract: A process for manufacturing a piece made of composite material including a fiber preform that is embedded in a matrix, includes placing the preform in a first chamber that is delimited by a first semi-sealed wall, i.e., permeable to gas and impermeable to a product that is able to form the matrix, extracting the gases in a second chamber that is delimited by a second gas-tight wall and the first semi-sealed wall so as to obtain the diffusion of the product that is able to form the matrix in the preform, characterized in that it consists in using—as a first semi-sealed wall—at least one plate with a number of pipes of tapered shape that empty on either side of the at least one plate and at least one semi-sealed membrane that is superposed on the at least one plate.
Type:
Grant
Filed:
August 6, 2009
Date of Patent:
October 7, 2014
Assignee:
Airbus Operations SAS
Inventors:
Philippe Blot, Sébastien Gohier, Mathieu Lannuzel
Abstract: An onboard access control system to an information system onboard an aircraft, for communication from the open domain to the avionics domain, the open end avionics domains being connected to each other through a single-directional link from the avionics domain to the open domain. The system includes: a security device including: access switches controlling access to the avionics and open domains, a controller, a module for acquisition putting data into buffer memory and transmission to the avionics domain, a data control module, an acquisition module from the open domain and putting into buffer memory, and an operator's authentication mechanism.
Abstract: The aircraft includes: a fuel tank panel; a fuel pump bell, the bell being fastened to the panel; and a metal support arranged so that the bell is fastened to the panel entirely via the support.
Abstract: A method of removing a component from an aircraft includes attaching a device comprising a guide member to the aircraft; attaching the component (such as an actuator) to the guide member; detaching the component from the rest of the aircraft; and moving the guide member so that the component follows a predefined path of removal of the component. A device for use in such a method is also described.
Abstract: A monitor for monitoring the concentration of oxygen in a fuel or in an ullage over a fuel comprises (i) a sensing element comprising a luminescent substance comprising a luminophore and a support in which the luminophore is covalently bound to the support, (ii) a light source arranged to irradiate the sensing element with light, and (iii) a photosensor arranged to detect light emitted from the luminescent substance. The luminescent substance may be, for example, a platinum porphyrin covalently bound to silica.
Type:
Grant
Filed:
July 14, 2009
Date of Patent:
October 7, 2014
Assignee:
Airbus Operations Ltd
Inventors:
Joseph K-W Lam, David Osborne, Norman Mark Ratcliffe
Abstract: A fuselage segment of an aircraft fuselage is provided with an outer skin and an inner skin that are spaced apart from one another by a core, wherein conduits for system installations are integrated into the core, as well as a method for manufacturing such a fuselage segment.
Abstract: The present invention relates to the use of connecting elements for fastening CFK components and metal components in an aircraft or spacecraft, wherein a CFK component and a metal component can be connected to each other via at least one connecting element. The connecting element in this case is produced from an electrically non-conducting material, or has a shank and is produced from an electrically conducting or non-conducting material, wherein the shank is provided with a sleeve consisting of an electrically non-conducting material.
Abstract: A method for estimating aircraft airspeed by a processor and an airspeed estimation device, which includes the calculation of a value for aircraft aerodynamic speed (Vcaero), by an aerodynamic calculator, based on aircraft aerodynamic parameters and the calculation of a value for current aircraft speed (Vc) by an anemobarometric unit. An estimated airspeed (Vcest) is determined by adding, by an adding unit, a corrective value, determined by an airspeed integrating unit, to the value for Vcaero. The corrective value is determined, by the airspeed integrating unit, according to a comparison between: a residual speed value (VR), determined by a residual speed determination unit, with the value VR determined by correcting the value for Vcaero to a value that converges toward the value for Vc, and a predetermined threshold value (?).
Abstract: An air conditioning system in an aircraft is provided. The system comprises at least one air cycle air-conditioning pack with a compressor comprising a bleed air outlet and with a compressed-air line connected to the bleed air connection, which compressed-air line is connectable to a starter turbine for a main engine. With the use of air from a compressor of an air conditioning pack it is not necessary to switch off the air conditioning pack; bleed air removal from the auxiliary power units becomes obsolete; and, since there is no unnecessary discharge of compressed air from a bleed air system, noise pollution on the ground is reduced.
Abstract: A routing clip for securing a line to a structure comprising: a base for attaching the clip to a structure; and a clamp comprising: a first flexible strap which extends from the base and has one or more projections extending from its side; and a second flexible strap which extends from the base and has a passageway for receiving the first flexible strap and a locking surface which is arranged to engage one of the projections on the first flexible strap to prevent the first flexible strap from being withdrawn from the passageway. At least part of the clip is made from an elastomeric material.
Abstract: A method for manufacturing a fiber composite component having an integral structural design includes positioning a sheet-like fibrous semi-finished product in a mold that defines an outer contour of the fiber composite component. Dimensionally stable fibrous semi-finished products, each having dimensions corresponding to a respective portion of the manufactured fiber composite component, are arranged on the sheet-like fibrous semi-finished product. The dimensionally stable fibrous semi-finished products are stabilized and fixed in place using mold cores. The semi-finished products are resin infiltrated using one of a first or a second gating process so as to form a construct. The first gating process includes gating via the mold cores at a head of each dimensionally stable fibrous semi-finished product and performing extraction in an area of the mold.
Type:
Grant
Filed:
December 28, 2010
Date of Patent:
September 30, 2014
Assignee:
Airbus Operations GmbH
Inventors:
Georg Lonsdorfer, Hauke Seegel, Klaus Rode, Andreas Pau
Abstract: This invention relates to an aft pylon fairing for the suspension system of an aircraft engine, comprising a main structure extending along a longitudinal direction of said fairing and integrating two side panels connected to each other, the fairing also comprising a heat protection deck mounted on said main structure through connection means comprising tabs designed to deform to accompany displacement of the deck relative to the main structure, if there is differential thermal expansion between these two entities.
Abstract: An aircraft turbomachine propeller including multiple blades assembled on a hub rotating around an axis of rotation of the propeller, that can reduce risks of loss of the blade following impact of a foreign body. At least one blade includes a recess opening radially towards the inside in the area of the base of this blade. A retaining device includes a moving retaining mechanism positioned in the recess and configured to be moved from a retracted position to a deployed blade-retaining position, and vice versa.
Abstract: An arrangement for verifying a real model by using a virtual model is provided. The arrangement comprises a real model which has a real coordinate system, a virtual model which has a virtual coordinate system, a first position determination element, which is applied in/on the real model in a defined manner, and a real tool element, which is arranged in the real model. A position and/or orientation of the real tool element in the real model can be determined relative to the first position determination element. An operation of the real tool element can be triggered in the real model, and the operation of the real tool element can be imaged in the virtual model. The operation of the real tool element in the real model and the imaged operation in the virtual model can be logically or functionally assigned to one another.
Type:
Grant
Filed:
June 18, 2012
Date of Patent:
September 30, 2014
Assignee:
Airbus Operations GmbH
Inventors:
Benjamin Becker, Holger Schmidt, Ilke Oencue Calis
Abstract: Device for mechanically decoupled retention of components perfused by hot gas in an aircraft, with a coupling member for coupling to a component emitting hot gas and to a component accepting hot gas, with a holder, with a flange, and with a bellows, the holder being fittable to a housing or frame connected to the component emitting hot gas, the bellows being fastened by one end to the flange and by the other end to the holder, and the coupling member being fastened to the flange. By virtue of the device, both an angular misalignment and radial and axial positional misalignment can be equalized.