Abstract: A cladding apparatus is provided for the interior of an aircraft that includes, but is not limited to at least one two-dimensional fabric sheet, at least one guide device, and at least one tensioning element. The guide device is configured to be attached in the interior along a direction of extension of the interior, and slidably guide the fabric sheet at least in a first section of the interior along the direction of extension. The tensioning element is, furthermore, configured to be attached in the interior, and by producing a tensile force that acts on the front edge and/or the rear edge of the fabric sheet to stretch taut the fabric sheet along the direction of extension of the interior.
Type:
Grant
Filed:
March 14, 2012
Date of Patent:
August 26, 2014
Assignee:
Airbus Operations GmbH
Inventors:
Ingo Wuggetzer, Stefan List, Nicolas Tschechne, Tobias Mayer
Abstract: A method for assisting the construction and validation of an avionics platform uses, on the one hand, a functional description of the platform using avionics functions, software modules suitable for executing these functions, and functional link occurrences between these modules and, on the other hand, a material description of this platform using calculation or communication items of equipment and physical links between these equipment. The method according to the invention enables to generate paths between the various items of equipment by using direct physical links and/or physical links belonging to one or more network(s), and subsequently to associate at least one such path to be each functional link occurrence. It also enables to associate to each software module an item of equipment adapted to host it.
Abstract: The invention relates to a radome (1) for an aircraft, and more specifically to a device for connecting said radome to the structure of said aircraft. The radome that is the subject of the invention comprises a plurality of locking units able to bring together the opposing surfaces of the aircraft's fuselage (10) and the radome (1), each unit comprising: locking means (20) able to exercise a traction force on the surface of the fuselage, substantially normal to the surface, via attachment means; centering means able to withstand the shear forces substantially tangential to the opposing surfaces of the fuselage and radome; the locking means (20) are placed such that they are located inside the cone of resulting forces on the centering means so as to minimize the bending stresses generated by the assembly in the radome (1).
Abstract: The dialog device includes a display screen, on which are displayed three graphic representations, which are respectively associated with the three control axes of the aircraft, each of said graphic representations comprising a plurality of portions, each of which is associated with a guidance mode of the associated control axis, so that all the possible guidance modes of the guidance system are thus represented, this representation highlighting the fact that the guidance modes are active exclusively on a given guidance axis.
Abstract: The aircraft passenger seat headrest (20) includes a carrier (21) and a helmet (22) for at least partially housing the head of the passenger. The helmet is attached to the carrier and is movably mounted in relation to the carrier (21). Said helmet includes a body and at least one portion (32, 34) that is movably mounted onto the body to extend the latter.
Abstract: A locking apparatus for an object that is lockable on a rail is provided such that the object may be undone in a single manual operating step. The apparatus may be used in a passenger aircraft in which it is necessary to slide seats or other built-in devices. The apparatus includes at least one first base body, at least one first locking body, and at least one first operating element. The at least one first base body is designed to be placed on top of the rail. The at least one first locking body is movably held to the at least one first base body, and is shaped to be placed into the rail. The at least one first operating element is connected to the at least one first locking body for moving the at least one first locking body in the direction of the interior of the rail.
Abstract: An interface system for use in an aircraft galley includes a first connection element. The first connection element can be connected via a first appliance connection apparatus to an internal electrical system, an internal fresh water supply system, and an internal wastewater disposal system of a first galley appliance, and can be connected via a second appliance connection apparatus to an internal electrical system, an internal fresh water supply system, and an internal wastewater disposal system of a second galley appliance. Further, the first connection element can be connected via an aircraft galley connection apparatus to a complementary aircraft galley connection apparatus of a second connection element of the interface system. The second connection element can be fixed in a compartment in the aircraft galley, so as to connect the first connection element to an electrical system, a freshwater supply system and a wastewater disposal system.
Type:
Grant
Filed:
June 8, 2010
Date of Patent:
August 26, 2014
Assignee:
Airbus Operations GmbH
Inventors:
Stefan Koschberg, Marco Mundt, Detlef Eggers
Abstract: A detection device determines whether an uncontrolled movement of a control surface of an aircraft is occurring. The device includes means for calculating the difference between a theoretical command and an actual command in order to form a residual value, and means for detecting an uncontrolled movement of the control surface, if a comparison value depending on this residual value is greater than a threshold value If the comparison value is greater than the threshold value during a confirmation time, then the uncontrolled movement of the control surface of the aircraft is confirmed.
Type:
Grant
Filed:
July 18, 2012
Date of Patent:
August 26, 2014
Assignees:
Airbus Operations (SAS), Universite Bordeaux I, Centre National de la Recherche Scientifique
Inventors:
Philippe Goupil, Rémy Dayre, Hervé Le Berre, Anca Gheorghe, Ali Zolghadri, Jérôme Cieslak
Abstract: A cabin equipment component connection system for an aircraft comprises a plurality of connecting elements, which are adapted to be connected to a cabin equipment component in order to connect the cabin equipment component to a higher-level system of the aircraft. In at least one zone of the cabin equipment component connection system, a number and an arrangement of the connecting elements in the cabin of the aircraft are selected such that cabin equipment components that are provided in a first number and/or a first arrangement in the cabin of the aircraft are connectable to the connecting elements of the cabin equipment component connection system, and that cabin equipment components that are provided in a second number and/or a second arrangement in the cabin of the aircraft are connectable to the connecting elements of the cabin equipment component connection system.
Abstract: A fire fighting system for extinguishing a 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 fire source.
Type:
Grant
Filed:
November 9, 2006
Date of Patent:
August 26, 2014
Assignee:
Airbus Operations GmbH
Inventors:
Julika Bleil, Lars Frahm, Andreas Westenberger, Claus Hoffjann
Abstract: A device includes means for generating and applying to an aircraft protecting orders avoiding a flight with an excessive descent rate. More specifically, the device includes components configured to perform a series of operations including measuring the current vertical speed and the current height of the aircraft and comparing these flight parameters with a safety envelope defining couples of vertical speed and height that are indicative of an excessive descent rate. If the current vertical speed and height are located in the safety envelope, a protection is triggered by generating protecting orders to remove the aircraft from the safety envelope and applying those protecting orders to control surfaces of the aircraft.
Abstract: A force measuring system is provided for measuring forces on a rotating body that includes, but is not limited to a force measuring device, which is mounted on the rotating body, as well as a position sensing unit for detecting the rotation of the rotating body and an evaluation unit, which is connected to the force measuring device and the position sensing unit. The evaluation unit is configured for recording a force value measured by the force measuring device depending on the detected position of the rotating body. The force measuring system allows the forces and torques on a rotating body to be determined precisely and as flexibly as possible, independently of the prevailing rotation speed of the rotating body.
Type:
Grant
Filed:
February 28, 2012
Date of Patent:
August 26, 2014
Assignee:
Airbus Operations GmbH
Inventors:
Michael Huhnd, Erik Goldhahn, Stephan Zipp, Alberto Villa
Abstract: A method of controlling the center of gravity of an aircraft having a plurality of fuel tanks, the method comprising transferring fuel from one or more of the fuel tanks according to a predetermined sequence, the timing of the sequence being dependent on the decrease in gross weight of the aircraft.
Type:
Grant
Filed:
November 25, 2008
Date of Patent:
August 26, 2014
Assignee:
Airbus Operations Limited
Inventors:
Michael Spottiswoode, Antoine Burckhart, Petter Sjungargard
Abstract: The method of the invention comprises imparting to the flaps (6G, 6D) of said aircraft either a nose-up deflection (?F) corresponding to the maximum sharpness if the nose-up order is higher than a predetermined threshold, or a deflection (?0) corresponding to the minimum drag if the nose-up order is lower than said threshold.
Abstract: An aircraft wing comprising a main wing element with a spar and a leading edge rib which is supported by the spar and extends forward of the spar; a high lift device which is movably mounted to the main wing element; and an actuation mechanism comprising a drive shaft and a gear train. The gear train comprising a drive cog which is carried by the drive shaft, an actuator cog which is coupled to the high lift device, and one or more intermediate cogs which are mounted to the rib and coupled in series with the drive cog and the actuator cog so as to transmit torque from the drive cog to the actuator cog which moves the high lift device between a retracted position and an extended position in which the high lift device increases the camber of the wing. The sizes of the cogs in the gear train are selected so that the drive shaft rotates at a higher rate than the high lift device.
Type:
Application
Filed:
July 6, 2012
Publication date:
August 21, 2014
Applicant:
Airbus Operations Limited
Inventors:
Simon Topping, Christopher Payne, Llifon Williams, Martin Mayneord, David Belfourd, Xavier Hue
Abstract: A system for detecting jamming and/or uncontrolled movement of an aircraft control surface includes first means for estimating the value of at least one parameter of an equation simulating the feedback loop dynamic of the control surface, according to a recursive autoregressive method with exogenous variable of RARX type in a recursive least squares way, and second means for detecting jamming and/or uncontrolled movement of the control surface, according to the estimated parameter value by the application of a decision test in the parametric space.
Type:
Application
Filed:
February 21, 2014
Publication date:
August 21, 2014
Applicants:
Airbus Operations SAS, Universite de Bordeaux, Centre National de la Recherche Scientifique (CNRS), Institut Polytechnique de Bordeaux
Inventors:
Anca Gheorghe, Rémy Dayre, Philippe Goupil, Ali Zolghadri, Jérôme Cieslak, David Henry
Abstract: An engine simulator for wind tunnel models exhibits a turbine with an inlet for a pressurized fluid and an outlet for a relieved fluid, a flow-type body arranged downstream from the turbine, a jacket that at least partially envelops the flow-type body with the formation of a gap, and at least two electrodes. A downstream end of the flow-type body is provided with a heater coating comprised of a matrix material that contains a conductivity additive and is connected with the electrodes for applying an electrical voltage. This may make it possible to prevent ice formation on the trailing edge of the flow-type body.
Type:
Grant
Filed:
May 31, 2012
Date of Patent:
August 19, 2014
Assignee:
Airbus Operations GmbH
Inventors:
Michael Huhnd, Detlev Dau, Roman Melachrinos, Hans Perner, André Fueser
Abstract: An integration method and module aims at simplifying the electrical connections between equipment and an electrical power center to be supplied electricity, while enabling a good accessibility of each piece of equipment for easier maintenance. To do so, a particular integration of this equipment is carried out so as to be able to connect the equipment in a direct extension of the electrical power center. According to one embodiment, an integration module includes a frame and a cover, the frame having a substantially parallelepipedic shape adapted to be able to extend longitudinally along a main axis in parallel with a longitudinal main side of the electrical power center. Cells, which define a constant cross section and an adjustable width enabled by movable intermediary walls, extend perpendicularly to the main longitudinal axis. Such cells are adapted to receive formatted electrical equipment.
Abstract: A locking/unlocking device for electronic boards, the boards being configured to be inserted into an electronic cabinet with at least one slotted plate fit into the rack of the electronic cabinet, the device including a substantially rectangular frame supporting at least one locking slide that locks the electronic board onto the slotted plate through the action of a locking element. The device further includes an extracting lever that rotates between a rest and a locking position around a lateral Y1 axis, the extracting lever fitted so that exerting force is possible along the longitudinal X axis between the electronic board, or the frame and the rack, with the locking unit including an extension to be placed outside, opposite the extracting lever along the longitudinal axis X of the board when the two levers are engaged in the locking position.
Abstract: The invention relates to a method for joining cured stringers to at least one structural component of an aircraft or spacecraft, including placing the stringers onto the at least one structural component, depositing and pressing respective vacuum film strips such that each strip is attached to a pair of stringers and present between the pair of stringers with the use of vacuum sealing means in such a manner that a continuous vacuum arrangement, comprising the covering vacuum films and the vacuum film strips, is formed, and pressurized joining of the stringers to the at least one structural component by means of the continuous vacuum arrangement formed.
Type:
Grant
Filed:
July 19, 2011
Date of Patent:
August 19, 2014
Assignee:
Airbus Operations GmbH
Inventors:
Peter Sander, Hans Marquardt, Hauke Lengsfeld