Abstract: An acoustic treatment panel in which each cell includes a plurality of conduits which extend from the porous acoustically resistive structure to the reflective layer of the acoustic treatment panel, each conduit including at least one opening set away from the porous acoustically resistive structure and configured to cause the inside and the outside of the conduit to communicate.
Type:
Grant
Filed:
April 24, 2018
Date of Patent:
March 9, 2021
Assignee:
Airbus Operations (S.A.S.)
Inventors:
Alain Porte, Jacques Lalane, Maud Lavieille
Abstract: An electrical link includes an electrical protection device. The electrical link, for linking an AC high-voltage generator to a user apparatus, includes an electrical conductor surrounded by a first inner insulating envelope. An electrical protection device includes a conductive sheath around the inner insulating envelope. A fixed DC current generator is connected to a current injection point of the conductive sheath. A circuit breaker that can be activated is on the electrical conductor and configured to break the electrical link when it is activated. A detection module is connected to a current tap-off point of the conductive sheath and to the circuit breaker, the detection module being configured to detect a break in the conductive sheath, a current leak out of the electrical conductor or a current leak out of the sheath and to activate the circuit breaker.
Abstract: A supporting structure of optimized volume includes at least two vertical structural elements having a front face and a rear face. Modules including electronic equipment items are fixed onto the front face of the vertical structural elements. Use in particular can be for the integration of avionics modules on aircraft.
Abstract: Method and device for controlling the path of a following aircraft with respect to a leading aircraft where the aircraft fly in formation. The device includes a data reception unit configured to receive an item of risk of collision information relating to the leading aircraft, a calculating unit configured to determine at least one what is termed safety position when an item of risk of collision information is received, the safety position corresponding to a position in which the following aircraft is not subjected to effects of vortices generated by the leading aircraft, and a control unit configured to bring the following aircraft into the safety position as soon as the calculating unit has determined the safety position.
Type:
Grant
Filed:
July 31, 2018
Date of Patent:
January 5, 2021
Assignee:
Airbus Operations (S.A.S.)
Inventors:
Jean-Luc Robin, José Torralba, Julie Lebas
Abstract: A method and device for assisting in piloting of an aircraft in approach to a landing runway with a view to a landing, including a module for determining current state of the aircraft, a module for determining distance between a target state and current state from an approach strategy and an ellipse formed by points determined such that a sum of a distance between the current position of the aircraft and the points of the ellipse and of a distance between the points of the ellipse and a projection of the target position on a horizontal plane of movement of the aircraft is equal to distance between target state and current state. The ellipse is displayed on a screen. The ellipse form gives indicates significance and variation of the energy surfeit of the aircraft. The pilot can decide on actions to maneuver the aircraft appropriately to dissipate the excess energy.
Abstract: A side console for an aircraft cockpit includes a structure for mounting of an item of aircraft equipment and a complementary structure. The mounting structure and the complementary structure are formed of single-piece components articulated about an axis of articulation between a storage position in which the single-piece components are more or less folded against one another, and a position of installation in which the single-piece components extend respectively in substantially mutually perpendicular planes.
Type:
Grant
Filed:
April 18, 2017
Date of Patent:
November 17, 2020
Assignee:
Airbus Operations S.A.S.
Inventors:
Bernard Guering, Matthieu De Kergommeaux
Abstract: An aircraft nacelle air intake structure including an air intake lip with a U-shaped section to ensure air is shared between an inner face and an outer face. An acoustic panel is on the intake lip rear on the side of the inner face level with a first assembly point. An outer panel is on the intake lip rear on the side of the outer face level with a second assembly point. A front reinforcing frame on the intake lip inside is fixed to the air intake lip on the side of the inner face level with a first fixing point and on the side of the outer face level with a second fixing point. The length of the chord between the stop point and each fixing point is between ? and ? of the total chord between the stop point and the assembly point.
Type:
Grant
Filed:
December 19, 2017
Date of Patent:
November 17, 2020
Assignees:
Airbus Operations (S.A.S.), Airbus (S.A.S.)
Inventors:
Alain Porte, Eric Haramburu, Patrick Oberle, Grégory Albet, Vincent Billerot, Frédéric Piard, Franck Oundjian
Abstract: A method enabling two holes belonging to two parts to be aligned relies on use of a tool, comprising a body, having a first outer surface which gradually wanders from a longitudinal axis of the body as it extends from a first end of the body, and a hollow part having a second outer surface with a complementary section to the section of the holes. The hollow part comprises a hole through which it is removably mounted on the tool so that the second outer surface extends the first outer surface on an opposite side to the first end of the body. The method comprises inserting the first end of the body into the first hole, and then operating the tool to push the body and then the hollow part together into the holes. This method especially applies to the assembly of a floor module to an aircraft fuselage.
Abstract: An aircraft control comprises a mobile pedal and comprises a cylinder coupled to the pedal such that a displacement of the pedal according to at least a first direction reduces the volume of a first chamber of the cylinder. A control device comprises a fluid type bus system connecting two aircraft controls. Additionally, an aircraft is equipped with such a control device.
Abstract: An aircraft including at least one turbine engine and a monitoring device associated with the turbine engine, the turbine engine being linked firstly to circuits including fluid circuits and electric circuits, and secondly to sensors for monitoring the turbine engine and the circuits, the sensors including at least one fire sensor and sensors for monitoring the fluid circuits, sensors for monitoring the electric circuits and sensors for monitoring the operation of the turbine engine, the monitoring device being linked to the sensors and including a central processing unit to generate a signal indicating the occurrence of a fire on the turbine engine only if a fire sensor and a sensor for monitoring a fluid circuit or an electric circuit or the operation of the turbine engine transmit a signal indicating an anomaly.
Abstract: A holding tool for holding the first and second side panels of a primary structure of an aircraft pylon during assembly thereof includes: a first portion configured to be removably secured to the first side panel, at least one second portion including at least one pair of first and second parts, positioned on either side of the second side panel and attracting one another by virtue of a magnetic field so as to secure the second portion to the second side panel, and at least one connection element connecting the first and second portions. Thus, during assembly of the primary structure, the second portion of the holding tool may be secured to the second side panel without the need for through-holes. The primary structure thus assembled does not comprise any through-holes in the side panels.
Abstract: A method for assembling a primary structure of an aircraft pylon, includes a step of fixing an angle bracket to each of the first and second lateral panels such as to obtain an L form for each of the first and second lateral panels prior to a placement of said L forms each placed against two sides of each transverse frame. This assembly technique makes it possible to reduce the mounting clearances such that it is unnecessary to fit shims, resulting in a reduction of mounting time and manufacturing costs.
Type:
Grant
Filed:
October 2, 2018
Date of Patent:
October 13, 2020
Assignees:
Airbus Operations S.A.S., AIRBUS OPERATIONS LTD
Inventors:
Stéphane Dostes, Thierry Theron, Audrey Benaben, Thomas Deforet, Julien Moulis, Joel Dedieu, Robert Whiffen, François Martinel
Abstract: An interface manager device interconnects peripheral devices to a network of ACD type or of AISD type of an aircraft, and includes: a first data interface for connecting it to the network; a first electrical power supply interface for connecting it to a general electrical power source; second data interfaces and second electrical power supply interfaces, for connecting it to the peripheral devices, which are deactivated by default. The interface manager device is configurable via a configuration interface so as to selectively authorize connections between the second data interfaces and the first data interface, and to selectively authorize connections between the second electrical power supply interfaces which are associated with them and the first electrical power supply interface, and to activate the second interfaces concerned. The interface manager device propagates a received data packet when said data packet relate to an authorized connection and deletes said data packet otherwise.
Abstract: An estimation system includes a module for measuring a current angle of attack and current flight parameters of the aircraft, a module for estimating a current lift coefficient of the aircraft from the current flight parameters and from a mass of the aircraft, a module for estimating an angle of attack for a zero lift from the current angle of attack, from the current lift coefficient and from a slope of an affine part of at least one theoretical curve describing a lift coefficient of the aircraft as a function of an angle of attack, a module for estimating the current position of the flaps of the aircraft from the angle of attack for a zero lift and a module for sending the current position of the flaps to a user device.
Abstract: Prediction methods and systems including a central processing unit including a data acquisition unit configured to acquire experimental data of a parameter characterizing the time-dependent phenomenon, a data acquisition unit configured to acquire digital data of the parameter characterizing the phenomenon, and a data processing unit configured to combine the experimental data and the digital data, by using a proper orthogonal decomposition POD that makes it possible to obtain an effective prediction of the time-dependent phenomenon, combining the advantages of the experimental data (accuracy) and those of the digital data (spatial resolution).
Type:
Grant
Filed:
March 17, 2016
Date of Patent:
September 8, 2020
Assignees:
Airbus Operations (S.A.S.), Airbus Group India Private Limited, Airbus Operations GmbH
Inventors:
Marcus Barth, Lars Hansen, Mathieu Berthomet, Saravanan Rajan
Abstract: A rear engine attachment includes a beam attached to the reactor strut, a rudder mounted by a pivot connection on the beam about a main rotational axis, and two thrust rods each exhibiting a first end attached to the rudder and a second end attached to a front section of an engine, the two thrust rods and the rudder attached to the beam together defining a primary thrust path between the engine and the reactor strut to bear the engine thrust. For each thrust rod, the rear engine attachment exhibits a waiting fail-safe system activated in the event of a failure of the primary thrust path. The rear engine attachment includes, for each thrust rod, a break detector integral with the rudder which is provided to come into contact with the beam in the event of a failure of the primary thrust path. The attachment allows a quick inspection to be made to determine whether there has been a failure of the primary thrust path.
Type:
Grant
Filed:
November 1, 2017
Date of Patent:
September 1, 2020
Assignee:
Airbus Operations (S.A.S.)
Inventors:
Jean Pierre Couffignal, Jérôme Cassagne, Didier Rovatti, Thomas Deforet, Benoit Orteu, Michael Belin, Miren Egana-Abarrategui
Abstract: A mobile machine includes a fuselage having at least one door, inside which is located a unit for processing measurements taken by at least one measurement device installed outside said fuselage. The system for communication between the processing unit and the measurement device includes a flex circuit that is affixed at least partially flat in the door corner between the door and the rim of the opening formed in the fuselage with which the door is associated and one of the ends, the internal end, of which is located inside the fuselage and the other, external, end of which is located outside. Since the flex circuit makes it possible to pass through the wall of the fuselage via the opening for doors, the need to make substantial modifications to the aircraft is avoided.
Abstract: A nacelle includes a fixed structure supporting a fixed cowl and a movable cowl, the movable cowl being movable translationally between a closing position and an opening position. A blocker door is movably mounted rotationally on the nacelle between a closed position and an open position. The nacelle includes a drive mechanism of the blocker door and of the movable cowl between the closed/closing position and the open/opening position of the blocker door/movable cowl, respectively, and vice versa, the drive mechanism includes at least one actuator fixed, to the fixed structure of the nacelle and, to a fitting fixed to the movable cowl. The drive mechanism includes, for each actuator, a flexible member having a first end fixed to the fixed structure of the nacelle and a second end fixed to the fitting.
Type:
Grant
Filed:
February 6, 2018
Date of Patent:
August 25, 2020
Assignees:
Airbus Operations (S.A.S.), Airbus (S.A.S.)
Inventors:
Eric Haramburu, Patrick Oberle, Eric Masson
Abstract: A heat exchange device to be positioned in an aircraft pylon and including a heat exchanger and an obturator to adopt a closed state where it prevents flow of air from flowing through the heat exchanger, and more- or less-permissive states where it allows flow of air to flow with a higher or lower flow rate. The obturator includes slats each including a pivot axis, the pivot axes of the various slats being mutually parallel and intersecting the direction of the flow of air, the slats being simultaneously mobile in rotation about their pivot axis between a closed position in which the slats are contiguous, which corresponds to the closed state of the obturator, and an open position in which the slats are spread apart, which corresponds to the permissive state of the obturator.
Type:
Grant
Filed:
September 12, 2018
Date of Patent:
August 18, 2020
Assignee:
Airbus Operations (S.A.S.)
Inventors:
Stéphane Combes, Jean Geliot, Thomas Deforet, Adeline Soulie, Benoit Orteu
Abstract: A thrust reverser system includes a thrust reversal cascade and a reverser door which are accommodated in a housing situated outside a secondary flow duct. The system also includes connection parts the presence of which combined with the action of the actuator gives rise simultaneously to: displacement rearwards of the cascade in the direction of a nacelle opening, cleared by a nacelle cowling entrained rearwards together with the cascade; and a combined movement of the reverser door relative to the cascade, leading to displacement of the front end of the door rearwards along the cascade, and to pivoting of this door, such as to give rise to plunging of its rear end into the secondary flow duct.