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Safran Landing Systems patents


Recent patent applications related to Safran Landing Systems. Safran Landing Systems is listed as an Agent/Assignee. Note: Safran Landing Systems may have other listings under different names/spellings. We're not affiliated with Safran Landing Systems, we're just tracking patents.

ARCHIVE: New 2018 2017 2016 2015 2014 2013 2012 2011 2010 2009 | Company Directory "S" | Safran Landing Systems-related inventors


Aircraft landing gear

An aircraft undercarriage has an axle for carrying at least one wheel. The undercarriage further includes a magnetic measurement target and at least one magnetic movement sensor cooperating with the magnetic measurement target to measure bending of the axle. ... Safran Landing Systems

Magnetic measurement target

A magnetic measurement target is configured to be positioned inside a vehicle axle and to cooperate with at least two magnetic movement sensors to measure deformation of the axle. The magnetic measurement target includes a body with a fastener end for fastening to one end of the axle and a main portion. ... Safran Landing Systems

Hydraulic valve for dampening pressure spikes, and associated systems and methods

Hydraulic valves for dampening pressure spikes and associated methods are disclosed herein. In one embodiment, a hydraulic valve for dampening pressure spikes includes a valve body, a poppet at least partially inside the valve body, and a pilot piston at least partially inside the valve body and away from the poppet. ... Safran Landing Systems

Landing gear with threadless cardan joint

A retractable landing gear includes a main strut having an upper end that is configured to connect to aircraft primary structure and a lower end configured to connect to an axle or bogie truck. An articulated stay has a distal end configured to connect to the aircraft structure and a proximal end pivotally connected to a cardan pin member. ... Safran Landing Systems

Braking system architecture for aircraft

A braking system architecture for aircraft, the architecture comprising: a brake including friction members and electromechanical actuators for exerting a braking torque on the wheel; a computer situated in the fuselage of the aircraft and arranged to produce first control signals; and a junction box situated on the undercarriage, the junction box being connected to the computer and to the electromechanical actuators, the junction box being configured to receive the first control signals and to use the first control signals to produce second control signals for application to the electromechanical actuators in order to control the electromechanical actuators.. . ... Safran Landing Systems

Aircraft landing gear fitted with a braked wheel

An aircraft landing gear comprising at least an axle carried in the bottom portion of the landing gear, a wheel provided with a rim mounted on the axle of the landing gear via bearings in order to rotate about an axis of rotation, a brake threaded on the axle and including a torque tube extending around the axle, friction members mounted around the torque tube and extending between the torque tube and the rim of the wheel, and at least one brake actuator designed for selectively exerting a braking force on the friction members, the brake actuator being carried by an actuator carrier to which the torque tube is secured, and a rotary drive for driving the wheel in rotation comprising firstly an actuator for driving the wheel in rotation and secondly a transmission member for selectively transmitting movement in rotation from the rotation actuator to the rim of the wheel and extending between the axle and the torque tube. The actuator carrier is centered directly by the axle and the transmission member is carried by the brake and guided in rotation thereon by bearings.. ... Safran Landing Systems

Centre seeking actuator

A centre seeking actuator having an outer cylinder, a slave cylinder slidably disposed within the outer cylinder, and a rod assembly having a piston slidably disposed within the slave cylinder and a rod extending from the piston to a point outside the outer cylinder. One or more first dynamic seals are arranged to act on a side wall of the rod to inhibit working fluid leaking from the outer cylinder, and one or more second dynamic seals are arranged to act on a sidewall of the slave cylinder to inhibit working fluid leaking from the outer cylinder.. ... Safran Landing Systems

Aircraft assembly including deflection sensor

An aircraft assembly having a first region, a second region spaced from the first region by a flexible region, and a deflection sensor. The first region has greater positional stability than the second region such that the second region deflects further from its default position than the first region during in-use loads. ... Safran Landing Systems

Aircraft assembly and method

An aircraft assembly having landing gear with a known deployment value, apparatus for permitting landing gear deployment, down-lock sensing apparatus, a navigation system, a landing gear control system, a flight control system, and a deployment controller. The deployment controller is configured to: calculate a touch down value using the aircraft position and speed information provided by the aircraft navigation system; command the landing gear control system to provide the deploy signal when the touch down value reaches a deployment threshold value which is greater than the landing gear deployment value; and command the flight control system to execute a landing abort sequence if the controller does not receive the down-lock signal from the landing gear sensing apparatus within a deployment value window which is greater than or equal to the known deployment value for the landing gear but less than the touch down value.. ... Safran Landing Systems

Method for generating a tooth profile of a wheel engaging with a roller pinion

Method for generating a tooth space profile (5) between two teeth (4) of a wheel (1) engaging with a roller (3) pinion (2) in a reference plane perpendicular to a central axis (x1) whose intersection with the reference plane defines a centre (c), comprising the step of defining a nominal tooth space with symmetrical first and second profiles so that the space is suitable for receiving a roller which comes into contact, without clearance, with the facing active portions of the first and second profiles at the level of a primitive diameter. The method of the invention comprises the steps of deforming the bottom portion (12) of the first profile so that the bottom point is brought nearer to the centre by an amount equal to a given radial clearance, and moving the first profile angularly through a given angular half-clearance around the centre to shift it away from the radial axis.. ... Safran Landing Systems

Aircraft wheel with a removable rim flange

An aircraft wheel rim includes a main portion and a removable portion. The main portion includes a hub and a disk extending between the hub and an annular outer portion that receives a tire and is shaped to form a rim one of its sides of the annular outer portion. ... Safran Landing Systems

Method of controlling an electrical taxiing system

A control method for controlling an electrical taxiing system adapted to moving an aircraft while it is taxiing, the method comprising the steps of: generating a ground speed setpoint for the aircraft; transforming the ground speed setpoint into an optimized speed setpoint presenting a curve as a function of time that has a predefined function comprising a plurality of linear portions, each having a slope that is a function of the ground speed setpoint; implementing a regulator loop having the optimized speed setpoint as its setpoint; and generating a command for the electrical taxiing system from an output of the regulator loop.. . ... Safran Landing Systems

Method for linking the shaft of a tachometer and an aircraft wheel

The invention relates to a method for linking an end (9) of a shaft (8) of a tachometer (7) positioned in a landing gear hub (1) and a wheel (2) mounted to rotate on said hub, the method comprising the step of equipping the wheel with a housing (14) suitable for receiving the end of the shaft of a tachometer and driving the shaft in rotation with the wheel, the housing comprising a bearing member (17) protruding inside the housing to be pushed back by the end of the shaft against an elastic member (18) to take up any play between the end of the shaft and the housing. The invention also relates to a bush ensuring application.. ... Safran Landing Systems

Aircraft undercarriage fitted with a shimmy-attenuator device

. . An aircraft undercarriage having a sliding rod slidably mounted in a strut-leg, and a scissors linkage (4) having one branch (4a) hinged to the strut-leg or to a turning element of a control for steering the sliding rod mounted to turn in the strut-leg, and one branch (4b) hinged to the sliding rod, the branches being hinged to each other by a pivot pin (12), the undercarriage being fitted with a shimmy-attenuator device (10a, 10b) placed on the pivot pin of the shimmy-attenuator, the attenuator device including threshold resilient return means generating a force returning the branches towards a rest position, and at least damping means generating a damping force when the branches move axially along the pivot pin. The attenuator device comprises two modules (10a, 10b) placed on either side of the scissors linkage in order to co-operate with the pivot pin, each of the modules performing at least one of the damping function and the threshold resilient return function.. ... Safran Landing Systems

03/01/18 / #20180058510

Method for connecting the rotor of an electric motor to an element that is to be driven

The invention relates to a method for connecting in rotation an output member (5) of an electric motor (1) and an element (2) that is to be driven in rotation, comprising the use of at least one fusible pin (11) that links the output member and the element that is to be driven, and that has at least one section that is prone to fail in shear when a torque transmitted by the fusible pin exceeds a predetermined threshold. The method comprises the step of interposing, between the pin and either the output member or the element that is to be driven, at least one elastic member (20) comprising a first travel with a first stiffness followed by a second travel with a second stiffness greater than the first stiffness.. ... Safran Landing Systems

03/01/18 / #20180057154

Aircraft landing gear shock absorber assembly

An aircraft landing gear shock absorber assembly having an outer casing having a bore which extends through the outer casing. The bore has a first opening and a second opening. ... Safran Landing Systems

03/01/18 / #20180057151

Aircraft wheel with a separable bearing box

The invention relates to an aircraft wheel comprising a hub (52) for mounting the wheel on a landing gear axle to enable the wheel to rotate about an axis of rotation, and a rim (55) with edge flanges for receiving a tire, the rim being secured to the hub by a web (56). The hub is adapted to receive releasably a bearing box (60) comprising two bearings (53, 54) each having an inner ring and an outer ring mounted between a bushing (61) for engaging on the axle with an outside wall shaped to receive the inner rings of the bearings, the bushing having one end (63) shaped as an abutment and another end shaped to receive a pre-loading nut (67); and a sleeve (62) extending around the bushing and having an inside wall presenting two shoulders to hold the outer rings of the bearings axially, the sleeve having an outer wall shaped to be received as a sliding fit in a bearing of the hub, with one end (68) shaped as an abutment and another end shaped to receive a stop nut (70).. ... Safran Landing Systems

02/08/18 / #20180037316

Aircraft landing gear assembly

. . An aircraft landing gear assembly having: a bogie beam coupled to a strut; a steerable axle mounted on the bogie beam, first and second wheel assemblies, mounted on the axle, each wheel assembly including a wheel and a brake disc attached to each wheel and arranged to rotate with the wheel; first and second brake plates mounted on the axle arranged to provide a braking force to the wheels upon contact with the first and second brake discs; a cross member coupled between the first and second brake plates; a brake rod, pivotally connected to the cross member at a first end and arranged to be attached to an anchor point on the aircraft landing gear at a second end; wherein the pivot axis of the axle and the pivot axis of the cross member are generally coaxial.. . ... Safran Landing Systems

02/01/18 / #20180031062

Heat screen with obstacles for a braked aircraft wheel

A method of reducing the cooling time of disks of a brake (5) of an aircraft wheel (1) fitted with a heat screen (10) extending between the wheel and the disks of the brake and mounted to rotate on an aircraft undercarriage about an axis of rotation, the method including making obstacles (11) on the heat screen, which obstacles project from a face of the heat screen that faces towards the brake disks.. . ... Safran Landing Systems

01/25/18 / #20180023647

Perforated heat screen for a braked aircraft wheel

The invention provides a method of reducing the cooling time for disks of a brake (5) of an aircraft wheel (1) fitted with a heat screen (10) extending between the wheel and the disks of the brake, and mounted to rotate on aircraft landing gear about an axis of rotation, the method comprising making perforations (11, 12, 13) through the heat screen to allow air heated by the disks to pass through the heat screen towards the wheel, the perforations being provided with obstacles to block any radiation from passing directly from the disks towards the wheel.. . ... Safran Landing Systems

01/25/18 / #20180022446

Aircraft braking system having a high level of availability

An aircraft braking system comprising: a first group (ga) of actuators and a second group (gb) of actuators. A first control module (105a) is adapted, in a nominal mode, to control the first group, and in a reconfigured mode, to control the first group and the second group. ... Safran Landing Systems

01/04/18 / #20180005744

Bistable linear electromagnet

A bistable linear electromagnet comprising a first housing (10) and a second housing (11) in alignment, a movable armature (18) comprising a rod (19) and a shuttle (20) that is slidably mounted, and a first coil (13) positioned in the first housing and a second coil (15) positioned in the second housing. A cavity (25) is made in a measurement wall (4) of one of the housings, and the electromagnet comprises a magnetic field sensor (26) positioned in the cavity and designed to measure a magnetic flux existing in a magnetic path formed by the walls of said housing and by the shuttle, in order to detect whether the shuttle has moved towards or away from the abutment wall of said first or second housing.. ... Safran Landing Systems

01/04/18 / #20180001998

Aircraft landing gear

An aircraft landing gear having a shock absorbing strut and a shortening mechanism coupled between an elongate beam and a shortening portion of a shock absorber. The shortening mechanism is arranged such that when the elongate beam is at a first position due to a first extension state of the retraction actuator the shortening mechanism is in a locked condition in which it inhibits axial movement of the shortening portion within the strut element in the first direction axial direction, and as the retraction actuator changes in extension state from the first extension state towards a second extension state, the retraction actuator moves the elongate beam which in turn causes the shortening mechanism to move the shortening portion within the strut element in the first axial direction to shorten the shock absorbing strut.. ... Safran Landing Systems

01/04/18 / #20180001997

Aircraft undercarriage with a rotary drive actuator

The invention relates to an aircraft undercarriage having a leg (2) pivotally mounted on a structure of the aircraft to pivot about a pivot axis (x1) between a deployed position and a retracted position, the undercarriage including a foldable brace (3a, 3b) comprising two hinged-together elements, one of which is hinged to the leg and the other of which is hinged to the structure of the aircraft, in such a manner that when the leg is in the deployed position, the two brace elements are locked together in a substantially aligned position, the undercarriage also being provided with a rotary drive actuator (10) having an outlet shaft acting on one of the elements of the foldable brace in order to cause the leg to pivot between its two positions. The drive actuator is pivotally mounted on the structure of the aircraft to pivot about an axis of rotation (x3) of the outlet shaft, the drive actuator having a casing (12) connected by a reaction rod (13) to the leg in order to take up the torque developed by the drive actuator when driving the undercarriage.. ... Safran Landing Systems

12/07/17 / #20170349270

Landing gear storage and quick servicing solution

. . A method for pressurizing and depressurizing a shock absorber of an aircraft. More specifically, it relates to a method in which an aircraft weight and ambient temperature are used to calculate a required pressurization level of a shock absorber. ... Safran Landing Systems

11/16/17 / #20170326911

Aircraft wheel

An aircraft wheel including a rim (2) comprising two assembled-together rim halves (3a, 3b), each rim half (3a, 3b) having a bearing surface (7) extending in a plane perpendicular to an axis of rotation (x) of the aircraft wheel. The aircraft wheel further includes a spacer (9) situated between the two bearing surfaces (7) when the rim halves (3a, 3b) are assembled together.. ... Safran Landing Systems

10/12/17 / #20170293300

Method for controlling a taxiing system

A method for controlling an aircraft taxiing system, comprising the steps of: generating a nominal load command (comm_nom); generating an acceleration setpoint (cons_a); implementing, in parallel with the generation of the nominal load command, a processing chain (7) comprising a regulation loop (br), the regulation loop (br) having for its setpoint the acceleration setpoint (cons_a) and for its command an acceleration command (comm_a), the acceleration command being converted into an acceleration load (eff_a), a maximum load threshold being equal to the maximum of the acceleration load (eff_a) and a minimum load threshold (seuil_min); and generating an optimised load command (comm_opt) equal to the minimum of the nominal load command and the maximum load threshold.. . ... Safran Landing Systems

10/12/17 / #20170291695

Aircraft landing gear assembly

An aircraft landing gear assembly including structural members coupled via a coupling including a bearing. The bearing has a body defining a first bearing surface arranged to contact a first counter-face of the coupling. ... Safran Landing Systems

09/21/17 / #20170267335

Lockable wheel actuator disengagement system on an aircraft landing gear

. . A landing gear (0) for an aircraft comprising a wheel (r), a system (1) for rotationally driving the wheel that is mobile between a clutched position and a safety position by passing through a declutched position, and a manoeuvring system (3) to displace the driving system (1) between its declutched and clutched positions. The gear comprises an elastic return (4) for returning the driving system (1) to its safety position and first and second abutments (51a, 52a) that are separated as long as the driving system (1) is away from its safety position and in contact with one another when the driving system (1) is in safety position. ... Safran Landing Systems

09/07/17 / #20170253323

Aircraft landing gear assembly

An aircraft landing gear assembly comprising a first member coupled to a second member in parallel by a bolt. First and second mechanical fixings are mounted on the bolt and arranged to apply a clamping force to the members. ... Safran Landing Systems

08/10/17 / #20170227051

Dynamic bearing

A dynamic bearing for an aircraft landing gear. The bearing comprises a lug, a shaft comprising a first material, and a bearing surface comprising a second material that is softer than the first material. ... Safran Landing Systems

07/20/17 / #20170204931

Shock strut

A shock strut for a landing gear assembly that includes a hollow cylinder having a first bearing surface and a piston having a second bearing surface. The piston is configured to move within the hollow cylinder such that the second bearing surface slides relative to the first bearing surface. ... Safran Landing Systems

07/20/17 / #20170203833

Aircraft landing gear assembly

An aircraft landing gear assembly includes a structural member coupled to another part by a joint including engagement formations or a relatively high friction coating arranged such that the joint inhibits pivotal movement of the structural member when the structural member is compressively loaded in an axial manner.. . ... Safran Landing Systems

06/08/17 / #20170158316

Fully electric speed-proportional nose wheel steering system for an aircraft

An aircraft drive system having a fully electric speed-proportional control and drive system for the nose wheel of an aircraft in which variable steering authority is accomplished by monitoring of the signal from a tiller and rudder pedals by a nose wheel controller in conjunction with the speed of the aircraft, in order to command and power an electromechanical steering, actuator to achieve speed-proportional variable steering authority. This provides a system with a quicker response time than current hydraulic-based systems which can help reduce nose wheel shimmy, eliminate certain nose wheel steering failure modes associated with hydraulic systems, and reduce weight when used in small-to-medium sized aircraft.. ... Safran Landing Systems

06/01/17 / #20170152886

Pivot link assembly

. . The invention relates to a pivot connection type assembly comprising a shaft and first and second connection parts, each receiving the shaft so as to enable them to pivot relative to each other, the first connection part being arranged axially between a first end of the shaft and a radial plane, while the second connection part is arranged axially between said radial plane and the other end of the shaft. The shaft is hollow and includes an inside section that presents a radial dimension at least in a first axial plane and over a first segment of the shaft extending axially between the first end and the radial plane , which radial dimension varies, decreasing on axially approaching the radial plane. ... Safran Landing Systems

05/11/17 / #20170130297

Method for producing a low-alloy steel ingot

A method of fabricating a low alloy steel ingot, the method including a) melting all or part of an electrode by a vacuum arc remelting method, the electrode, before melting, including iron and carbon, the melted portion of the electrode being collected in a crucible, thus forming a melt pool within the crucible; and b) solidifying the melt pool by heat exchange between the melt pool and a cooling fluid, the heat exchange applied serving to impose a mean solidification speed during step b) that is less than or equal to 45 μm/s and to obtain an ingot of low alloy steel.. . ... Safran Landing Systems

04/27/17 / #20170115253

Aircraft health and usage monitoring system and triggering method

An aircraft health and usage monitoring system (hums) having one or more monitoring sensors arranged to be coupled to an aircraft subassembly to monitor the health of one or more parts of the subassembly and a trigger subsystem. The trigger subsystem includes a sound transducer and a processor, the processor being coupled to the sound transducer to receive and process sound signals from the sound transducer to extract sound information and being coupled to the monitoring sensors to provide control commands to the monitoring sensors. ... Safran Landing Systems

04/27/17 / #20170113811

Aircraft landing gear assembly including a health and usage monitoring system (hums) and method

A health and monitoring system or “hums” mounted within a hollow structural subassembly of an aircraft landing gear assembly, the subassembly having an access port for access to the hums without requiring disassembly of the structural subassembly so as to require jacking up the aircraft.. . ... Safran Landing Systems

04/06/17 / #20170098976

Electric motor

Electric motor comprising a rotor and a stator (2), the stator comprising a body (3) forming a frame and a windings assembly (4, 5) housed in slots of the body. The electric motor comprises at least one rod (16, 23) used to connect, to one another, at least two fixed assembled parts of the electric motor, the rod extending into a housing (9) formed in the body over the entire length thereof in order to emerge on each side of the body.. ... Safran Landing Systems

04/06/17 / #20170096215

Aircraft assembly

An aircraft assembly having a first body connected to a second body via a flexible coupling arranged to limit separation of the bearing faces while permitting relative rotational movement between the bodies in a movement plane so as to define a joint between the bodies.. . ... Safran Landing Systems

03/30/17 / #20170089418

Assembly, bridging tool for an assembly and method of forming an assembly

A tool for bridging an outer dynamic seal in a shock absorber to enable fluid leakage to be more readily determined. The tool having an insertion portion including one or more bridging channels, and a body portion that is thicker than the insertion portion. ... Safran Landing Systems

03/02/17 / #20170059603

Method for measuring the rotation speed of a vehicle wheel

. . A method for measuring the rotation speed of a wheel including the steps of: acquiring an analogue measurement signal (sma) generated by a magnetic tachometer and containing a useful signal the frequency of which is representative of the rotation speed of the wheel; digitizing in real-time the analogue measurement signal (sma) in order to obtain a time-dependent digital measurement signal (smnt); calculating a fourier transform of the time-dependent digital measurement signal (smnt) in order to obtain a frequency-dependent digital measurement signal (smnf); and carrying out a frequency analysis in order to identify by a search for peaks a useful spectral line (16) so as to obtain the frequency of the useful signal and therefore the rotation speed of the wheel.. . ... Safran Landing Systems

03/02/17 / #20170058981

Method for ventilating brake discs of an aircraft wheel

A method for ventilating discs (11) of a brake (10) fitted to an aircraft wheel (1) having a rim (2) mounted so as to rotate on an axle (4) of a landing gear of the aircraft. The brake discs are threaded onto a torsion tube (12) of the brake which extends around the axle. ... Safran Landing Systems

02/23/17 / #20170051427

Device intended for implementing an anodization treatment and anodization treatment

A device for performing anodizing treatment on a part, the device including a treatment chamber including a part for anodizing together with a counter-electrode situated facing the part to be treated, the part to be treated constituting a first wall of the treatment chamber; a generator, a first terminal of the generator being electrically connected to the part to be treated and a second terminal of the generator being electrically connected to the counter-electrode; and a system for storing and circulating an electrolyte, the system including a storage vessel, different from the treatment chamber, for containing the electrolyte; and a circuit for circulating the electrolyte in order to enable the electrolyte to flow between the storage vessel and the treatment chamber.. . ... Safran Landing Systems

02/16/17 / #20170043865

Device aircraft undercarriage leg including rack-and -pinion type means for controlling the orientation of the wheels of the undercarriage leg

An aircraft undercarriage leg having an orientation control for wheels that causes a sliding rod to pivot. The orientation control has a rotating member mounted on the strut assembly having a toothed sector forming a pinion and is rotationally coupled to the sliding rod, and a rack mounted to slide on the strut assembly along a sliding axis perpendicular to the pivot axis to mesh with the pinion, the rack being moved by drive means. ... Safran Landing Systems

02/09/17 / #20170036756

Landing gear for an aircraft comprising an obstacle detector

The invention relates to a landing gear (1) of an aircraft (5), comprising: a strut assembly (10) including a first end (10a) designed to be mounted on the aircraft (5) and a second end (10b) opposite the first end (10a); a rod (14) slidably mounted on the second end (10b) of the strut assembly (10), said rod (14) being translationally movable in relation to the strut assembly (10); and at least one obstacle detector (2) secured to the landing gear (1), the landing gear (1) being characterised in that the obstacle detector (2) is secured in a zone adjacent to the second end (10b) of the strut assembly (10).. . ... Safran Landing Systems

01/12/17 / #20170008617

Device for measuring a relative rotation speed and/or a relative angular position between a first rotating element and a second rotating element mounted to rotate relative to a static part

A device for measuring a relative rotation speed and/or a relative angular position between a first rotating element (2) and a second rotating element (3). The device includes a structure for generating a magnetic field rotating at a magnetic rotation speed representing a rotation speed of the first rotating element and a sensor (5) mounted to rotate and adapted to produce from the rotating magnetic field a measurement signal representing the relative rotation speed and/or the relative angular position. ... Safran Landing Systems








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