Patents Assigned to Safran Landing Systems UK LTD
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Patent number: 10286995Abstract: An aircraft landing gear which includes a noise-inducing region and a cover. The cover comprises a cover portion arranged to enclose the noise-inducing region to inhibit an airflow negotiating the noise-inducing region when the landing gear is in use.Type: GrantFiled: March 21, 2013Date of Patent: May 14, 2019Assignee: SAFRAN LANDING SYSTEMS UK LTDInventors: Stuart Lacy, Geoff Cumner, Peter Michaelides
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Patent number: 10279896Abstract: An aircraft spring assembly having a spring, an end fitting including a spring engagement formation arranged to be mechanically coupled to an end region of the spring and a coupling formation for coupling the spring assembly to an aircraft anchor point. The coupling formation includes a load bearing surface via which loads from the anchor point can be transmitted into the spring assembly. The assembly further includes an integral damping member provided within the load path between the load bearing surface of the coupling formation and the end region of the spring.Type: GrantFiled: May 17, 2016Date of Patent: May 7, 2019Assignee: SAFRAN LANDING SYSTEMS UK LTDInventors: Andraz Vatovec, Paul Greenwood, Andrew Paddock
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Patent number: 10196132Abstract: An aircraft landing gear assembly having a main strut configured to move between a deployed condition and a stowed condition, a damping device to oppose movement of the main strut as it approaches the deployed condition, a retraction actuator and a mechanical retraction linkage coupled between the aircraft and the main strut, and a locking device. The locking device is operable to change the retraction linkage between a locking condition in which the retraction actuator can apply a stowing force to the main strut through the retraction linkage to move the main strut from the deployed condition to the stowed condition, and an extensible condition in which the retraction linkage permits the main strut to be deployed by way of gravity.Type: GrantFiled: August 17, 2016Date of Patent: February 5, 2019Assignee: SAFRAN LANDING SYSTEMS UK LTDInventor: Robert Kyle Schmidt
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Publication number: 20190016445Abstract: An aircraft assembly having: a first part; a second part, the first part being movably mounted relative to a second part; a dynamic conduit arranged such that movement of the first part relative to the second part causes the dynamic conduit to move through a movement volume from a first conduit position to a second conduit position; a first fastener arranged to couple a component to the aircraft assembly, at least some of the first fastener residing within the movement volume of the dynamic conduit; and a safety guide arranged to be coupled to the first fastener, the safety guide comprising a bridge portion which extends away from the first fastener within the movement volume of the dynamic conduit so as to support the dynamic conduit when the dynamic conduit is in the second conduit position.Type: ApplicationFiled: July 5, 2018Publication date: January 17, 2019Applicant: SAFRAN LANDING SYSTEMS UK LTDInventor: Ben Clark
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Patent number: 10112699Abstract: A method of preloading an aircraft assembly involving a step of operating an extendible preloading tool to move a landing gear strut to decrease the distance between first and second link attachment joints for attachment of a preloading linkage. A tool and aircraft assembly are also provided.Type: GrantFiled: June 23, 2016Date of Patent: October 30, 2018Assignee: Safran Landing Systems UK LTDInventors: Yann Simonneaux, Andrew Paddock
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Patent number: 10100848Abstract: A hydraulic actuator having a body defining a chamber, a piston rod including an annular groove and a piston head slidably housed within the chamber, the piston head having a number of segments each of which has a base portion mounted within the annular groove.Type: GrantFiled: April 14, 2016Date of Patent: October 16, 2018Assignee: SAFRAN LANDING SYSTEMS UK LTDInventors: Robert Kyle Schmidt, Matthew Hilliard
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Patent number: 10066694Abstract: 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. The insertion portion being installable within an annulus of a shock absorber to bridge a first shock absorber seal so as to place a portion of the annulus in fluid communication with an exterior of the hydraulic device via the one or more bridging channels.Type: GrantFiled: September 26, 2016Date of Patent: September 4, 2018Assignee: Safran Landing Systems UK LTDInventors: Daniel Charles Kendrick, Andraz Vatovec
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Patent number: 10024379Abstract: A hydraulic shock absorber having an inner housing portion slidably coupled to an outer housing portion to define a variable size chamber for containing shock absorber fluid. The region where the inner and outer housing portions overlap defines an annulus between adjacent surfaces of the inner and outer housing portions which varies in size in accordance with the extension state of the shock absorber. A dynamic seal is coupled to a surface of the shock absorber within the annulus for confining shock absorber fluid to the chamber. The shock absorber fluid is an electro-rheological or magneto-rheological fluid and the shock absorber includes a device for generating a magnetic or electric control field within the chamber at a region adjacent dynamic seal in order to increase the viscosity of the shock absorber fluid adjacent to the dynamic seal to inhibit passage of the shock absorber fluid beyond the dynamic seal.Type: GrantFiled: April 7, 2016Date of Patent: July 17, 2018Assignee: Safran Landing Systems UK LTDInventors: Robert Kyle Schmidt, Matthew Baxter
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Patent number: 10000282Abstract: An aircraft landing gear assembly includes a mechanical structural linkage having a shock absorber and a linkage abutment which are biased apart by a mechanical spring. The force required to deform the spring sufficiently to place the linkage abutment at a predefined distance with respect to the shock absorber abutment is less than the breakout force of the shock absorber.Type: GrantFiled: May 17, 2016Date of Patent: June 19, 2018Assignee: Safran Landing Systems UK LtdInventor: Robert Kyle Schmidt
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Patent number: 9994306Abstract: An aircraft landing gear assembly stop member is arranged to be coupled to a first part of an aircraft landing gear assembly and includes a pair of projections which control movement of a second part of the landing gear assembly.Type: GrantFiled: January 12, 2016Date of Patent: June 12, 2018Assignee: Safran Landing Systems UK LtdInventors: Lee Williams, Peter Millington, Anthony Foy, Richard Tutton
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Patent number: 9994309Abstract: A pitch trimmer assembly for an aircraft landing gear having a damping element arranged to be connected between a first and a second element of an aircraft landing gear and arranged to exert a first damping force when in a first state and a second damping force in a second state, the damping element being switchable between the first and second states in dependence on the relative positions of the first and second landing gear elements.Type: GrantFiled: February 4, 2014Date of Patent: June 12, 2018Assignee: Safran Landing Systems UK Ltd.Inventors: Ben Hodgkinson, R. Kyle Schmidt, David Smart
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Patent number: 9968978Abstract: Apparatus configured to deform a tubular work piece having a longitudinal axis, the apparatus comprising a support for supporting a tubular work piece to be deformed; rotation means for rotating the tubular work piece about its longitudinal axis; a nozzle for directing a stream of pressurized fluid at the tubular work piece in a direction transverse to the longitudinal axis of the tubular work piece; and means for moving one or both of the tubular work piece and the nozzle relative to one another such that the stream of pressurized fluid can be aimed at a plurality of locations along the tubular work piece; wherein the pressure of the fluid directed at the tubular work piece is great enough to cause deformation of the tubular work piece, but not so great that cutting of the tubular work piece can occur.Type: GrantFiled: March 10, 2014Date of Patent: May 15, 2018Assignee: Safran Landing Systems UK Ltd.Inventors: Jean-Philippe Villain-Chastre, Germain Forgeoux, Przemyslaw Grochola
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Patent number: 9926072Abstract: A method of forming an aerospace component, the method including: forming a first subcomponent by an additive layer manufacturing (ALM) process, the first subcomponent having an inner surface defining an inner space; performing a non-ALM machining process to modify a portion of the inner surface of the first subcomponent; and forming a second subcomponent by an ALM process, the second subcomponent being arranged to close the inner space to complete the component.Type: GrantFiled: September 29, 2015Date of Patent: March 27, 2018Assignee: SAFRAN LANDING SYSTEMS UK LTDInventors: Mark Collins, Marcin Chilik
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Patent number: 9919793Abstract: An aircraft landing gear assembly having a main strut and an axle on which wheel and brake assemblies are mounted. An adaptor member is mounted on a mounting pin and arranged to define a brake rod anchor point. The adaptor member is coupled to a part of the landing gear assembly so as to react brake torque and can be formed from a different material than a portion of the main strut.Type: GrantFiled: October 14, 2015Date of Patent: March 20, 2018Assignee: SAFRAN LANDING SYSTEMS UK LTDInventors: Matthew Sexton, Robert Kyle Schmidt
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Patent number: 9914532Abstract: An aircraft landing gear shock absorber having an inner housing portion slidably coupled within an outer housing portion, and a chamber which defines a sealed fluid volume for containing shock absorber fluid within the shock absorber. The chamber includes a moveable wall portion arranged to move between a first position and a second position, and in the second position the effective volume of the chamber is decreased such that the shock absorber fluid pressure increases, to provide a bump to the shock absorber.Type: GrantFiled: March 2, 2016Date of Patent: March 13, 2018Assignee: SAFRAN LANDING SYSTEMS UK LTDInventor: Robert Kyle Schmidt
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Patent number: 9879701Abstract: An actuator arranged to be movable between an extended condition and a compressed condition and being biased to an intermediate condition between and distinct from the extended condition and the compressed condition. The actuator includes a damping device arranged to define the damping coefficient of the actuator.Type: GrantFiled: April 24, 2014Date of Patent: January 30, 2018Assignee: Safran Landing Systems UK LTDInventors: Christopher Green, Robert Kyle Schmidt, David Smart
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Patent number: 9878780Abstract: An aircraft landing gear assembly includes a bi-stable, split line tube biased to assume a tubular condition to serve in place of a lock link or side stay and an actuator configured to radially enlarge the tube at a region for folding.Type: GrantFiled: March 17, 2016Date of Patent: January 30, 2018Assignee: Safran Landing Systems UK LTDInventor: Robert Kyle Schmidt
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Patent number: 9862483Abstract: An aircraft landing gear assembly includes a fibre composite leaf spring arranged as a down lock spring to make the lock link.Type: GrantFiled: March 17, 2016Date of Patent: January 9, 2018Assignee: Safran Landing Systems UK LTDInventor: Robert Kyle Schmidt
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Patent number: 9863455Abstract: A pin joint assembly for an aircraft landing gear having an elongate joint pin; at least one first lug through which the joint pin passes; and at least one second lug through which the joint pin passes. The joint pin assembly includes first and second retaining elements located at opposite ends of the joint pin and arranged to maintain the location of the joint pin relative to the first and second lugs. At least portion of the pin joint assembly is elastically deformable.Type: GrantFiled: January 13, 2014Date of Patent: January 9, 2018Assignee: Safran Landing Systems UK LTDInventor: Chris Green
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Patent number: 9816806Abstract: A tool for detecting deformation of a nominally straight element includes a first body element having first straight edge, means for biasing the first straight edge against the straight element, and a light source arranged to illuminate any space present between the straight element and the first straight edge of the first body element.Type: GrantFiled: February 4, 2014Date of Patent: November 14, 2017Assignee: Safran Landing Systems UK LTDInventors: Chris Green, Kay Green