Patents Assigned to Airbus
  • Method and a system for monitoring the reliability of at least one piece of electronic equipment installed in an aircraft
    Patent number: 10006954
    Abstract: A monitor system for monitoring the reliability of at least one piece of electronic equipment installed in an aircraft. In order to monitor each piece of electronic equipment, such a monitor system comprises: monitor means for measuring variations of at least one state parameter P as a function of time t; concatenation means for generating data groups (ti, Pi, Sj); transmission means for transmitting the data groups (ti, Pi, Sj) to a centralized unit; first computation means for determining an observed reliability Robs of the or each piece of electronic equipment; second computation means for determining an expected reliability Rexp of the or each piece of electronic equipment; comparator means for comparing the observed reliability Robs with the expected reliability Rexp of the or each piece of electronic equipment; and warning means.
    Type: Grant
    Filed: December 13, 2016
    Date of Patent: June 26, 2018
    Assignee: AIRBUS HELICOPTERS
    Inventors: Stephane Bailly, Vincent Schmidt
  • Conversion of geometric entities of 1D elements in a FEM from a source FEA tool format to a destination FEA tool format
    Patent number: 10007745
    Abstract: System and method of converting geometric entities of 1D elements in a finite element model (FEM) from a source finite element analysis (FEA) tool format to a destination FEA tool format is disclosed. In one embodiment, coordinates of all the geometric entities associated with each 1D element in the FEM are transformed from the source FEA tool format to a global coordinate system. The geometric entities of the ID elements in the FEM are then converted from the source FEA tool format to the destination FEA tool format using the transformed coordinates of all the geometric entities associated with each 1D element.
    Type: Grant
    Filed: May 27, 2013
    Date of Patent: June 26, 2018
    Assignee: AIRBUS GROUP INDIA PRIVATE LIMITED
    Inventors: Soham Narayan Patel, Amit Chaudhari, Abhishek Dwivedi, Jorge Gonzalez Rubio
  • Method for wireless energy transmission in closed spaces
    Patent number: 10008855
    Abstract: A method and device for the wireless transmission, in closed spaces, of energy emitted by at least one light source. The energy emitted by the light source is received by at least one solar cell module in the closed space and is converted into electricity. The method includes the steps of reflecting at least a part of the light energy emitted by the light source at a reflective surface inside the space, receiving the reflected light energy in the at least one solar cell module, and converting the reflected light energy into electricity. The device includes at least one solar cell module inside the closed space, configured to receive the light energy and convert the light energy into electricity. At least a portion of the space comprises a reflective inner surface comprising a multilayer insulation surface, at which the energy emitted by at least one light source is reflected.
    Type: Grant
    Filed: October 22, 2013
    Date of Patent: June 26, 2018
    Assignee: Airbus DS GmbH
    Inventors: Johannes Sebald, Hendra Kesuma
  • Compound aircraft having an additional anti-torque device
    Patent number: 10005550
    Abstract: A compound aircraft having a fuselage, a main rotor, a main anti-torque device and two wings positioned on either side of the fuselage. Each wing has at least one movable flap situated at its trailing edge. The flaps can be deflected asymmetrically relative to an air stream generated in reaction to the lift of the main rotor on either side of the fuselage so as to create longitudinal aerodynamic forces in opposite directions on either side of the fuselage and consequently create an additional torque that is added to the main torque from the main anti-torque device.
    Type: Grant
    Filed: July 12, 2016
    Date of Patent: June 26, 2018
    Assignee: AIRBUS HELICOPTERS
    Inventor: Francois Toulmay
  • MACHINE TOOL WITH AN ASSEMBLY CONFIGURATION WITH A CANTILEVERED TOOL
    Publication number: 20180169768
    Abstract: A machine tool for carrying out operations on a part includes a longitudinal rail, a transverse arm, a module for connection between the transverse arm and the longitudinal rail, the module being fitted in translation on the longitudinal rail, a tool which is supported by the transverse arm, and a retention unit which is arranged at one end of the transverse arm, and includes at least one sucker. The machine tool has an assembly configuration—in which the retention unit and the tool are positioned respectively on both sides of the longitudinal rail, such that the tool is fitted cantilevered relative to the longitudinal rail. This provides the machine tool with great polyvalence, in that it makes it possible to carry out operations in areas which in particular have significant curvatures, which are difficult to access, or which are unsuitable for securing of the sucker(s) of the retention unit.
    Type: Application
    Filed: December 13, 2017
    Publication date: June 21, 2018
    Applicant: AIRBUS SAS
    Inventors: Fabien Albert, Eric Pospisil, Kyle Hollis, Jeff Nelson, Eric Davis
  • CONDUCTIVE SUPPORT, TOOL FOR FITTING SAID CONDUCTIVE SUPPORT, METHOD FOR FITTING SAID CONDUCTIVE SUPPORT ON AN AIRCRAFT STRUCTURE AND AIRCRAFT STRUCTURE PROVIDED WITH SAID CONDUCTIVE SUPPORT
    Publication number: 20180172047
    Abstract: A conductive support is disclosed which is configured to be fixed, thanks to an electrically conductive glue, on a surface of a metal structure and which includes an insert made from an electrical material which includes a first end face configured to be pressed against the surface of the structure and a second end face allowing the temporary fixing of an electrical element; and a body which includes a contact face coplanar with the first end face of the insert and which extends completely around the first end face of the insert.
    Type: Application
    Filed: December 14, 2017
    Publication date: June 21, 2018
    Applicant: AIRBUS OPERATIONS (S.A.S.)
    Inventors: Sebastien CLEMENTE, Yannick LABROUSSE, Didier SEKULA
  • A MEASURING APPARATUS FOR MEASURING PROPERTIES OF A SURFACE
    Publication number: 20180172435
    Abstract: The present invention provides a measuring apparatus (200) for measuring properties of a surface (101, 103), the apparatus (200) comprising a mounting structure (210) comprising a plurality of segments (211-216) moveably mounted (217) with respect to each other, an actuation mechanism to move the segments of the mounting structure with respect to each other, and a plurality of sensors (220), each sensor being mounted to a segment of the mounting structure (210). The invention also provides a method of measuring properties of a surface (101, 103). The surface (102, 103) to be measured may be an aerodynamic surface of an aircraft.
    Type: Application
    Filed: May 27, 2016
    Publication date: June 21, 2018
    Applicants: University College London, Airbus Operations Limited
    Inventors: Stuart Robson, Ben Sargeant, Abdul Rahman El-Nounu
  • ELECTRONIC DEVICE FOR DETECTING AN AIR FLOW
    Publication number: 20180172719
    Abstract: An electronic device for detecting an air flow includes at least one sensor having a pair of platelets, each platelet having an RTD and having one end fixed, the other end being free and overlapping the free end of the other platelet. A platelet is flexible so as to form a switch for an electrical circuit. An air flow with a speed higher than a predetermined speed makes the sensor go from a first state, corresponding to a closed switch, in which the free ends of the platelets are in contact, to a second state, corresponding to an open switch, in which said contact is broken. A detection module allows, for each sensor, a resistance of the electrical circuit to be measured, the resistance corresponding to the RTDs being connected in parallel when the switch is closed or to one of the RTDs when the switch is open.
    Type: Application
    Filed: November 30, 2017
    Publication date: June 21, 2018
    Applicant: Airbus Operations S.A.S.
    Inventor: Pierre Charon
  • FLIGHT CONTROL METHOD FOR ROTORCRAFT, AND A ROTORCRAFT
    Publication number: 20180170524
    Abstract: A method of controlling a path of a rotorcraft. The method comprises a step of generating a first path setpoint and a step of automatically generating a first autopilot command from the first path setpoint. The method comprises a step of generating a first pilot setpoint during which a movement of a control member is transformed into a first pilot setpoint, the first pilot setpoint and the first flight parameter being homogenous in that they are expressed in the same measurement unit. The method includes a step of generating a first human pilot command from the first pilot setpoint followed by a step of generating a path command by combining the first autopilot command and the human pilot command.
    Type: Application
    Filed: December 5, 2017
    Publication date: June 21, 2018
    Applicant: AIRBUS HELICOPTERS
    Inventors: Frederic BLANC, Serge MEZAN
  • AIR INPUT STRUCTURE FOR AN AIRCRAFT NACELLE
    Publication number: 20180170568
    Abstract: An air input structure includes an air input lip and a front reinforcement frame placed inside the air input lip. The front part of the air input lip has a plurality of segments distributed angularly along the leading edge of the air input lip, two adjacent segments being separated by an intermediate part having an excess thickness. Each segment has four edges, each having an excess thickness relative to the rest of the segment. Thus, the air input lip has a lighter structure.
    Type: Application
    Filed: December 7, 2017
    Publication date: June 21, 2018
    Applicants: Airbus Operations S.A.S., AIRBUS SAS
    Inventors: Alain Porte, Patrick Oberle, Gregory Albet
  • METHOD OF ANALYZING VARIATIONS OF AT LEAST ONE INDICATOR OF THE BEHAVIOR OF A MECHANISM FITTED TO AN AIRCRAFT
    Publication number: 20180174383
    Abstract: A method of analyzing variations of an indicator of the behavior of a mechanism fitted to an aircraft, the indicator being determined from measurements of a physical operating parameter of the mechanism during a mission of the aircraft. The Method includes a storage step of storing the measurements of the physical operating parameter in a storage unit; a first transmission step of transmitting the measurements of the physical operating parameter contained in the storage unit to a communication station; a second transmission step of transmitting the measurements of the physical operating parameter from the communication station to an analysis center; an indicator generation step of generating the indicator performed on the basis of the measurements of the physical operating parameter; and an analysis step of analyzing variations of the indicator.
    Type: Application
    Filed: December 6, 2017
    Publication date: June 21, 2018
    Applicant: AIRBUS HELICOPTERS
    Inventors: Alexandre DIAZ, Kishan MITHALAL, Pierre DOUSSE, Abdelhafid BOUTALEB, Romaric SIMONET, Didier ROCHEFORT
  • AIRCRAFT WITH AN AIRFRAME AND AT LEAST ONE ELECTRICALLY POWERED THRUST PRODUCING UNIT
    Publication number: 20180170509
    Abstract: An aircraft with an airframe and at least one thrust producing unit the at least one thrust producing unit being electrically powered by an associated electrical engine that is electrically connected to an electrical energy source via an electrical energy distribution system, wherein the airframe comprises at least one load carrying section and at least one propulsion system carrying section, wherein the at least one load carrying section and the at least one propulsion system carrying section are segregated from each other, wherein the at least one load carrying section is provided for transportation of passengers and/or cargo, and wherein the at least one propulsion system carrying section is provided for carrying at least essentially the electrical energy source and the electrical energy distribution system.
    Type: Application
    Filed: December 5, 2017
    Publication date: June 21, 2018
    Applicant: AIRBUS HELICOPTERS DEUTSCHLAND GMBH
    Inventors: Sebastian MORES, Martin BLACHA, Christian REICHENSPERGER, Klaus RITTEL, Marco SCHNEEBERGER, Michael GEISS, Markus PASCHEK, Marius BEBESEL
  • CONTROL DEVICE FOR A POLYPHASE MOTOR AND METHOD FOR DRIVING A POLYPHASE MOTOR
    Publication number: 20180175753
    Abstract: An actuating apparatus for a polyphase motor includes five phase terminals for connecting of in each case one phase of the polyphase motor, a high terminal for applying a supply voltage (UB), a low terminal for applying a reference potential of the supply voltage (UB), a control device, wherein the control device is adapted, in four of the five phase terminals, to impress a pulse-width-modulated voltage pattern by connecting the phase terminals to the high terminal or the low terminal so that in the first phase terminal, an evaluation signal which is dependent on the angle of rotation of the polyphase motor is produced, and wherein the control device is adapted to determine the angle of rotation and/or a commutation condition of the polyphase motor from the evaluation signal.
    Type: Application
    Filed: December 7, 2017
    Publication date: June 21, 2018
    Applicants: Airbus Defence and Space GmbH, Airbus Operations GmbH
    Inventors: Joerg Wangemann, Heiko Rothkranz, Jens Schult
  • TEMPERATURE DETECTION SYSTEM USING A RADIO-TAG COMPRISING A THERMISTOR
    Publication number: 20180174014
    Abstract: An onboard system for detecting a temperature of an element includes a radio-tag, the radio-tag being fixed onto the element and having an antenna, the antenna having a load, and a radio-tag reader. The radio-tag reader is designed to emit an interrogation signal and to receive in return a response signal coming from the radio-tag. The load includes a thermistor and the radio-tag reader is adapted for determining a gain and/or a phase-shift between the interrogation signal and the response signal and for deducing a temperature of the element therefrom.
    Type: Application
    Filed: November 29, 2017
    Publication date: June 21, 2018
    Applicant: Airbus Operations S.A.S.
    Inventor: Pierre Charon
  • GENERATIVE PRODUCTION DEVICE COMPRISING A MEASURING DEVICE
    Publication number: 20180169952
    Abstract: A device for the layer-wise additive production of a complex three-dimensional component has a measuring mechanism for continuously monitoring quality indicators during the production of the component, wherein the measuring mechanism and a bed with a material powder are surrounded, at least in regions, by a processing cell filled with a protective gas atmosphere and the material powder of an uppermost layer can be melted in a locally limited manner in a melting zone by means of at least one laser. The measuring mechanism has the at least one laser and at least one optical sensor for the priority detection of the quality indicators in the region of the melting zone, in particular by means of Raman spectroscopy. Consequently, any construction errors in the component can be recognised, evaluated and, if necessary, corrected in a resource-saving manner without delay.
    Type: Application
    Filed: May 23, 2016
    Publication date: June 21, 2018
    Applicant: Airbus Defence and Space GmbH
    Inventors: Franz Engel, Andreas Nick, Wolfgang Rehm, Christian Weimer
  • AIRCRAFT WITH AN AIRFRAME THAT COMPRISES A LOAD CARRYING FRAMEWORK
    Publication number: 20180170511
    Abstract: An aircraft with a modular airframe. The modular airframe has a load carrying framework and at least one exchangeable covering item that exhibits a first predetermined shaping. The at least one exchangeable covering item is detachably mounted to the load carrying framework. The modular airframe is customizable by exchanging the at least one exchangeable covering item with a substitute exchangeable covering item that exhibits a second predetermined shaping.
    Type: Application
    Filed: December 5, 2017
    Publication date: June 21, 2018
    Applicant: AIRBUS HELICOPTERS DEUTSCHLAND GMBH
    Inventors: Sebastian MORES, Martin BLACHA, Christian REICHENSPERGER, Klaus RITTEL, Marco SCHNEEBERGER, Michael GEISS, Markus PASCHEK, Marius BEBESEL
  • Aircraft turbine engine comprising an air intake housing with a variable aerodynamic profile
    Patent number: 10001062
    Abstract: An aircraft turbine engine includes a fan duct having a wall; an air passage arranged in the wall and including an air inlet opening at the wall, the air passage being designed to receive part of the flow of air from the fan duct across the opening; an air intake housing located above the air inlet opening and fixed to the wall, the housing being arranged to intercept part of the air flow in the fan duct, and successively including, in the air flow direction, an upstream wall then a downstream wall, an upstream opening and a downstream opening arranged on the upstream wall and the downstream wall, respectively, the inside of the housing being in fluidic connection to the air inlet opening, and a movable sealing means between an “open” position; and a “closed” position relative to the downstream opening and the air inlet opening.
    Type: Grant
    Filed: October 30, 2015
    Date of Patent: June 19, 2018
    Assignee: Airbus Operations S.A.S.
    Inventor: Stephane Warnet
  • Device for holding and aligning a useful component, in particular a space travel component
    Patent number: 10000300
    Abstract: A device for holding and aligning a component includes a first and a second housing part and a tilting device. The first housing part is arranged on a first end for stationary arrangement on a carrier and the second housing part is arranged on a second end for connection to the useful component. The first end and the second end are on opposite sides of the device in relation to a longitudinal axis. The tilting device mechanically connects the first and the second housing parts to one another and enables a defined alignment and holding of the relative position of the second housing part in relation to the first housing part. The actuator of the tilting device is a number of wires made of a shape-memory alloy. A length of each of the number of wires is individually adjustable by a respective determination of the resistance, which can be processed as a control variable in a control loop.
    Type: Grant
    Filed: March 2, 2015
    Date of Patent: June 19, 2018
    Assignee: Airbus DS GmbH
    Inventor: Matti Haeberlein
  • Toilet system for a lavatory of a vehicle, lavatory of a vehicle, and aircraft with such a lavatory
    Patent number: 10000918
    Abstract: A toilet system for a lavatory of a vehicle comprises a toilet bowl, a cladding assembly for cladding the toilet bowl, forming a hollow space between the toilet bowl and cladding assembly, and a ventilation device with at least one suction line for extracting air. The cladding assembly extends from an exterior side of the toilet bowl over an edge of the toilet bowl, and thereby partially encases the edge. At least one of the at least one suction lines is fluidically connected with the hollow space.
    Type: Grant
    Filed: November 19, 2015
    Date of Patent: June 19, 2018
    Assignee: AIRBUS OPERATIONS GMBH
    Inventors: Christian Seibt, Joerg Cremers, Jens Wiebalck
  • Pushing device, moving mechanism and aircraft
    Patent number: 10000276
    Abstract: The present application relates to a pushing device, a moving mechanism and an aircraft. According to an aspect of the present application, a pushing device for a moving mechanism of an aircraft is provided, the moving mechanism including a primary moving device and an auxiliary moving device assisting the primary moving device, the pushing device including a support member and a pushing assembly supported by the support member, and the pushing assembly including a pushing element and an energy storage element. The pushing element is adapted to push a broken part of the auxiliary moving device to an offset position from a normal working position by means of energy from the energy storage element when the auxiliary moving device breaks. According to the present application, it is possible to provide an effective fault protection to the moving mechanism of the aircraft.
    Type: Grant
    Filed: April 21, 2016
    Date of Patent: June 19, 2018
    Assignee: AIRBUS (BEIJING) ENGINEERING CENTRE COMPANY LIMITED
    Inventors: Ming Li, Yumin Sun