Patents Assigned to SAFRAN LANDING SYSTEMS
-
Patent number: 11649041Abstract: A method for extending a landing gear system for a vehicle is disclosed. The landing gear system includes a first landing gear assembly and a second landing gear assembly. The method includes the steps of sensing a first load on the first landing gear assembly after the first landing gear assembly has reached a wheels-on-ground state and comparing the first load to a first target value. The method further includes the step of controlling an extension speed of the first landing gear assembly according to a difference between the first load and the first target value.Type: GrantFiled: July 21, 2020Date of Patent: May 16, 2023Assignees: SAFRAN LANDING SYSTEMS, SAFRAN LANDING SYSTEMS CANADA INC.Inventors: Cole Tofflemire, Graeme Peter Arthur Klim, Thibaud Mazoue, Andrew Michael Ellis
-
Patent number: 11642707Abstract: A method of unclogging ducts in a part made by additive manufacturing, the ducts running from at least one well that opens out into the surface of the part, the method comprising the steps of: fabricating a guide with a body that is designed to fit in the well, the guide having internal channels that extend from a base of the guide that is accessible by a user to an outside wall of the body; cleaning the well and inserting the body of the guide in the well so that channels in the guide open out in register with inlets of ducts that are to be unclogged; and inserting a thin flexible tool, e.g. a metal cable, through the base of the guide into at least one channel therein and causing the tool to penetrate into the duct in register in the part so as to unclog it.Type: GrantFiled: August 29, 2018Date of Patent: May 9, 2023Assignee: SAFRAN LANDING SYSTEMSInventors: Olivier Rigo, Thomas Kairet, Denis Luttenbacher, Stéphane Lambre, Stefano Argentero, Gérard Balducci
-
Patent number: 11643192Abstract: A bogey undercarriage having at least two axles, each carrying at least two wheels, wherein at least one of the axles carries a wheel fitted with a rotary drive device and no brake device, while the other wheels are provided with brake devices and no movement devices is provided. A braking method applied to such an undercarriage is also provided.Type: GrantFiled: March 28, 2019Date of Patent: May 9, 2023Assignee: SAFRAN LANDING SYSTEMSInventors: Jérôme Gui, Jean-Yves Ravel, Christophe Devillers
-
Publication number: 20230134203Abstract: The invention relates to a method for controlling an aircraft taxi system, comprising the steps of: generating a traction command (Com) to control an electric motor of a wheel drive actuator; detecting whether or not an external brake command, intended to control braking of the wheel via the brake, is generated; if an external braking command is generated, producing a predetermined minimum command (Cmp) to control the electric motor so that the drive actuator applies a strictly positive predetermined minimum motor torque to the wheel during braking; detecting whether a speed of the aircraft becomes zero and, if so, inhibiting the predetermined minimum command (Cmp) so that the drive actuator applies zero torque to the wheel.Type: ApplicationFiled: February 11, 2021Publication date: May 4, 2023Applicant: SAFRAN LANDING SYSTEMSInventors: Pierre-Yves LIEGEOIS, Laurent BOISSARD, Djemouai HADJIDJ
-
Publication number: 20230124974Abstract: An aircraft landing gear assembly having a first landing gear element movably coupled relative to a second landing gear element to move between a first condition and a second condition. The aircraft landing gear assembly further comprises a fibre composite leaf spring formed from a plurality of composite layers and arranged between the first and second elements, the leaf spring being arranged to bend when the first element moves from the first condition to the second condition. The fibre composite leaf spring comprises a first region and a second region, wherein the number of composite layers in the first region is greater than the number of composite layers in the second region. The landing gear further comprises a mounting assembly arranged to engage the first region of the leaf spring to couple the leaf spring to the first landing gear element.Type: ApplicationFiled: February 26, 2021Publication date: April 20, 2023Applicants: SAFRAN LANDING SYSTEMS UK LTD, SAFRAN LANDING SYSTEMS CANADA INCInventors: Mark Bevan, Pierre-Etienne Dandaleix, Jorge Juesas Portoles, Robert Kyle Schmidt
-
Publication number: 20230123036Abstract: An aircraft wheel includes a rim that is secured to a central hub defining an axis of rotation of the wheel. The wheel includes one or more driving pins that extend from the hub, projecting in a direction substantially parallel to the axis of rotation of the wheel so as to cooperate with a driving member for driving the wheel in rotation. The driving pin is distinct from bolts assembling together parts of the wheel.Type: ApplicationFiled: March 25, 2021Publication date: April 20, 2023Applicant: SAFRAN LANDING SYSTEMSInventors: Sylvain MOLINE, Yannick TARNOWSKI, Cédric ROULON
-
Patent number: 11619275Abstract: An aircraft braked wheel comprising a rim integral with a hub for rotationally mounting thereof on an axle of the aircraft along an axis of rotation, the wheel being equipped with a heat shield (11) extending opposite an inner face of the rim to protect the rim from the thermal radiation generated by a stack of discs extending inside the rim, characterized in that the heat shield has a face facing the discs (15) which has longitudinal ribs (16) extending in operation parallel to the axis of rotation of the wheel.Type: GrantFiled: November 4, 2019Date of Patent: April 4, 2023Assignee: SAFRAN LANDING SYSTEMSInventors: Maxime Brodard, Jean-Baptiste Robin
-
Patent number: 11618421Abstract: A method of controlling a braking device includes receiving a braking torque instruction, on the basis of the received braking torque instruction, setting a first braking torque set point for a first brake and a second braking torque set point for a second brake, measuring a first value of a first parameter representative of the first braking torque and modifying the first braking torque set point as a function of the first value with the aid of a first servocontrol loop, and measuring a second value of a second parameter representative of the second braking torque and modifying the second braking torque set point as a function of the second value with the aid of a second servocontrol loop.Type: GrantFiled: April 3, 2020Date of Patent: April 4, 2023Assignee: SAFRAN LANDING SYSTEMSInventors: Jean-Baptiste Lestage, Emmanuel Brun, Tiphaine Graillat
-
Patent number: 11613346Abstract: An aircraft landing gear assembly and method method of constructing an aircraft landing gear component. The assembly includes a ground contacting part, an aircraft attachment part, and a component. The component includes a first base member and a second base member separated along a first longitudinal axis, a plurality of first connecting points on the first base member arranged in a first regular polygon, a plurality of second connecting points on the second base member arranged in a second regular polygon. The second regular polygon has the same number of sides as the first regular polygon, and a plurality of first straight beams fixed to the first and second base members at the first and second connecting points and extending between the first and second base members, each beam aligned skew to the longitudinal axis.Type: GrantFiled: July 25, 2019Date of Patent: March 28, 2023Assignee: SAFRAN LANDING SYSTEMS UK LTDInventor: Matthew Sexton
-
Patent number: 11608039Abstract: A piece of electrical equipment for connecting both to at least one electromechanical braking actuator and also to at least one electromechanical drive actuator, the piece of electrical equipment (13a) comprising a housing (30), means for fastening the housing to the undercarriage, and inside the housing: a processor unit (32) arranged to generate a braking motor control signal and a drive motor control signal; a power supply unit (37) arranged to generate an equipment power supply voltage, a braking power supply voltage, and a drive power supply voltage; a power converter unit (40) arranged to generate a braking control voltage and a drive control voltage; and a distribution unit arranged to distribute the braking control voltage to the electromechanical braking actuator and the drive control voltage to the electromechanical drive actuator.Type: GrantFiled: October 29, 2018Date of Patent: March 21, 2023Assignee: SAFRAN LANDING SYSTEMSInventor: Brian Goyez
-
Patent number: 11603189Abstract: A landing gear system includes a drive shaft extending through an axle. A wheel with a drive surface is rotatably coupled to the axle. A drive assembly, which has disengaged and engaged states, includes a drive element and an idler element. The drive element, which has an engagement feature, is coupled to the drive shaft for rotation about an axis. The engagement feature has first and second diameters when the drive assembly is in the disengaged and engaged states, respectively. The idler element is frictionally engaged with the engagement feature of the drive element to transfer rotation of the drive element to the wheel when the drive assembly is in the engaged state. The idler element is disengaged from at least one of the engagement feature of drive element and the wheel when the drive assembly is in the disengaged state.Type: GrantFiled: January 12, 2021Date of Patent: March 14, 2023Assignee: SAFRAN LANDING SYSTEMS CANADA INC.Inventor: Robert Kyle Schmidt
-
Patent number: 11603188Abstract: A landing gear system includes a wheel rotatably coupled to the axle about an axis. A motor is fixedly positioned relative to the axle with a clutch assembly operably coupled to an output shaft of the motor. The landing gear includes an actuator and a drive assembly. The actuator applies a braking force to the wheel. The drive assembly includes a pinion gear and a drive gear rotatably associated with the pinion gear. The drive gear is configured to transfer a rotational force to the wheel in order to provide autonomous taxiing capability. Both the brake assembly and the drive assembly are operably coupled to the clutch assembly so that the output shaft of the motor drives both the brake assembly and the drive assembly.Type: GrantFiled: May 6, 2020Date of Patent: March 14, 2023Assignee: SAFRAN LANDING SYSTEMS CANADA INC.Inventor: Robert Kyle Schmidt
-
Publication number: 20230071768Abstract: An aircraft landing gear assembly comprising: a structural pin defining a first bore having a longitudinal insertion axis; a cap for covering the bore, the cap comprising: a base portion; a head portion; a body portion positioned between the base portion and the head portion; and a bolt which extends between the head portion and the base portion and comprises a threaded portion so that engagement of either the head portion or the base portion with the threaded portion moves either the head portion or the base portion relative to the other, the body being formed of an elastically deformable material such that upon tightening of the bolt, the base portion moves towards the head portion and the elastically deformable material moves radially outwards such that a contact surface of the elastically deformable material engages with an inner surface of the first bore in order to retain the cap.Type: ApplicationFiled: February 15, 2021Publication date: March 9, 2023Applicant: SAFRAN LANDING SYSTEMS UK LTDInventors: Lee Williams, Doug Wight, Peter Millington, Steven Lawson
-
Publication number: 20230076329Abstract: An aircraft landing gear comprising: a first member, a second member pivotally coupled to the first member, and a spring coupled to the first and second members, the spring comprising a plurality of elastically deformable washers, the spring being arranged to generate a biasing force between the first and second members to bias the first member toward a predetermined orientation relative to the second member.Type: ApplicationFiled: February 4, 2021Publication date: March 9, 2023Applicant: SAFRAN LANDING SYSTEMS UK LTDInventors: Pierre-Etienne Dandaleix, Thibault Hernandez, Andrew Mills
-
Patent number: 11597244Abstract: Method for managing the energy in a system for verifying the inflation pressure of the tires of an aircraft, consisting in measuring, by a pressure sensor, at least one inflation pressure of each of the tires, obtaining a unique identification data relating to each of the tires, and sending via the wireless communication link the measurements and data thus collected to a processing unit disposed in or out of the aircraft for them to be available to a pilot or a maintenance operator, the step of sending the measurements and data being carried out in an acyclic manner as a function of a trigger signal given by a motion detector that detects the motion of the wheels of the aircraft as long as the speed is lower than a predetermined maximum speed.Type: GrantFiled: July 7, 2020Date of Patent: March 7, 2023Assignees: SAFRAN LANDING SYSTEMS, SAFRAN ELECTRONICS & DEFENSEInventors: Olivier Dages, Didier Levavasseur, Stéphanie Nocente
-
Publication number: 20230059040Abstract: A method for the surface treatment of an aluminum or aluminum alloy part configured for use in the aviation sector, includes the steps of: i) subjecting said part to an anodization step; ii) treating the anodized part with a post-anodization sealing method according to the invention; and optionally iii) applying one or more layer(s) of paint; or optionally iv) applying a hard anodic oxidation treatment to at least some of the functional areas of the part. A part made of aluminum or aluminum alloy is treated with a post-anodization sealing method, optionally includes one or more layer(s) of paints or optionally having, on certain functional areas, a hard anodic oxidation treatment, wherein the part is configured for use in the aviation sector.Type: ApplicationFiled: January 21, 2021Publication date: February 23, 2023Applicants: SAFRAN AIRCRAFT ENGINES, SAFRAN LANDING SYSTEMSInventors: Virginie RELLAND, Myriam AUGROS, Philippe BAYARD, Benjamin MOULS, Aimé RAMAKISTIN
-
Publication number: 20230045934Abstract: An actuator includes a body and at least a first offset connection port that is connected to the body by a first duct projecting from the body. The first connection port is mechanically connected to the body at least by first and second struts. The first strut and the second strut extend from the first connection port, respectively, to a first segment of the body and to a second segment of the body that is axially spaced apart from the first segment. An undercarriage includes such an actuator as its locking or unlocking actuator.Type: ApplicationFiled: January 20, 2021Publication date: February 16, 2023Applicant: SAFRAN LANDING SYSTEMSInventors: Yves COURTOIS DE LOURMEL, Sébastien MESSE, Jean-Baptiste KAMIS, Arnaud LE BRETON, Nicolas NGUYEN
-
Publication number: 20230038683Abstract: An encapsulated shock absorber of an aircraft undercarriage includes a sliding rod slidably mounted in a leg strut of the undercarriage and an inner cylinder extending inside the strut. The inner cylinder is fastened to the strut via a top end, and the rod slides around the inner cylinder. The inner cylinder is terminated inside the sliding rod by a diaphragm that defines an oil chamber in the shock absorber and inside the sliding rod. A mixed oil/gas chamber is located in the inner cylinder, and an expansion chamber extends between the sliding rod and the inner cylinder. A hole being made in the inner cylinder in register with the expansion chamber is connected by a pipe to a pressure sensor situated outside the strut. The pipe extends inside the inner cylinder from the hole to the top end of the inner cylinder.Type: ApplicationFiled: February 26, 2021Publication date: February 9, 2023Applicant: SAFRAN LANDING SYSTEMSInventors: Philippe HENRION, Arnaud LAFITTE
-
Publication number: 20230031765Abstract: An aircraft landing gear includes a landing gear provided with a yoke supporting a spindle on which is mounted a capture pin to be hooked by a hook of a locking box to be mounted on a structure of an aircraft to immobilize the landing gear in a given position with respect to the structure. The capture pin includes a body provided with a longitudinal opening enabling the capture pin to be mounted on the spindle, and an outer surface of revolution having a central portion having a convex profile to cooperate with the hook. A central portion of the outer surface is formed on a central ring which is mounted so as to rotate freely on a central portion of the body.Type: ApplicationFiled: January 8, 2021Publication date: February 2, 2023Applicant: SAFRAN LANDING SYSTEMSInventor: Ludovic DUFAY
-
Patent number: 11565670Abstract: An electric braking system (1) for braking an aircraft, the system comprising: a brake (3) comprising an electromechanical actuator (5) designed so that when it applies a force to the friction members (4) that is less than or equal to a first maximum threshold, no degradation of the actuator occurs, and when it applies a force to the friction members (4) that is greater than the first maximum threshold, degradation is likely to occur; control means (7) configurable to occupy a first mode in which the controlled braking force cannot exceed the first maximum threshold, and to occupy a second mode in which the controlled braking force can reach the second maximum threshold; and configuration means (10) arranged to configure the control means (7) to occupy the second mode when in a situation preceding a potential interruption of takeoff (RTO) of the aircraft, and otherwise to occupy the first mode.Type: GrantFiled: April 1, 2020Date of Patent: January 31, 2023Assignee: SAFRAN LANDING SYSTEMSInventors: Nathanaël Richard, Romain Presle