Patents Assigned to Safran Landing Systems UK LTD
-
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
-
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
-
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
-
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: 20230002038Abstract: 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. As such, the shock absorber may be pressurized to the correct level without applying an iterative approach, greatly reducing initialization time.Type: ApplicationFiled: September 7, 2022Publication date: January 5, 2023Applicant: Safran Landing Systems UK LTDInventors: Yann Simonneaux, Jon Smith
-
Publication number: 20220388638Abstract: A method of monitoring the condition of an aircraft landing gear shock absorber, the shock absorber including at least one spring chamber containing a gas, the method comprising taking a plurality of measurements of the gas pressure and temperature, each gas pressure and temperature measurement pair being taken of at the same instant relative to an operating cycle of the shock absorber; calculating, based on each pair of gas pressure and temperature measurements, a first value; storing the first value in a log; determining a value trend based on the log; and in response to determining that the value trend is outside a first range of values, generating a first notification signal.Type: ApplicationFiled: November 10, 2020Publication date: December 8, 2022Applicants: Safran Landing Systems UK LTD, Safran Landing SystemsInventors: Antoine Guidoux, Jon Smith, Jean-Yves Ravel, Yann Simmonneaux
-
Publication number: 20220297825Abstract: An aircraft comprising a fuselage, a pair of wings connected to an upper portion of the fuselage, and a pair of wing support struts, each wing support strut being connected between a lower portion of the fuselage and an underside of the adjacent wing, wherein at least one centre landing gear assembly is connected to the fuselage and is configured to be retractable within the fuselage, and a respective outrigger landing gear is connected to each wing support strut, each outrigger landing gear being configured to be retractable within the respective wing support strut.Type: ApplicationFiled: April 15, 2020Publication date: September 22, 2022Applicant: SAFRAN LANDING SYSTEMS UK LTDInventor: Yann Simonneaux
-
Publication number: 20220281589Abstract: An aircraft landing gear assembly having a reinstating geometry in which a lock link can be moved to assume a first locking condition to inhibit movement of a stay when a main strut is in a deployed condition and a second locking condition to inhibit movement of the main strut when in a stowed condition. An unlock actuator is coupled between a first element of the stay and the lock link such that the actuator can break the lock link from the first locking condition and force it to assume the second locking condition by operational force in a single direction.Type: ApplicationFiled: May 23, 2022Publication date: September 8, 2022Applicant: Safran Landing Systems UK LTDInventor: Ian Robert Bennett
-
Publication number: 20220127016Abstract: Techniques and methodologies for servicing a shock strut are provided that account for the variability in gas solubility of the shock strut while in-service. These examples incorporates knowledge of the shock strut's stoke history in order to estimate/predict the amount of gas in solution, its percentage saturation, etc. This may permit a more refined knowledge of the true servicing state of the shock strut.Type: ApplicationFiled: October 27, 2020Publication date: April 28, 2022Applicants: SAFRAN LANDING SYSTEMS CANADA INC, SAFRAN LANDING SYSTEMS UK LTDInventors: Robert Kyle Schmidt, Jon Smith
-
Publication number: 20220033069Abstract: An aircraft assembly having: a first part; a second part, the second part being movably mounted with respect to the first part; an electro-hydraulic actuator coupled between the second part and a first anchor point, the actuator comprising a cylinder defining a bore and a piston and rod assembly slidably mounted within the bore and an active chamber within which an increase in fluid pressure causes the actuator to change during a first phase between first and second extension states to move the second part relative to the first part. The electro-hydraulic actuator further includes a hydraulic fluid supply circuit comprising a piezo-electric pump operable to supply pressurised fluid to the active chamber to change the actuator between first and second extension states.Type: ApplicationFiled: October 18, 2021Publication date: February 3, 2022Applicant: SAFRAN LANDING SYSTEMS UK LTDInventors: Royston Alan Evans, Paul Shaw
-
Publication number: 20210347467Abstract: An aircraft landing gear assembly comprising: a ground contacting part, an aircraft attachment part, and a component comprising: 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 having 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: ApplicationFiled: July 25, 2019Publication date: November 11, 2021Applicant: Safran Landing Systems UK LTDInventor: Matthew Sexton
-
Publication number: 20210269147Abstract: A center biased actuator having an outer cylinder, a slave cylinder linearly transposed within the outer cylinder, a rod assembly with a piston linearly transposed within the slave cylinder and a rod extending from the outer cylinder, one or more first dynamic seals arranged to act on a sidewall of the rod to inhibit hydraulic fluid leaking from the outer cylinder, one or more second dynamic seals arranged to act on a sidewall of the slave cylinder or an inner surface of the outer cylinder to inhibit hydraulic fluid leaking from the outer cylinder, and a gas chamber comprising a sealed expandable chamber containing gas. The expandable chamber is arranged to act on hydraulic fluid within the center biased actuator to bias the center biased actuator to assume an intermediate condition which lies between a compressed condition and an extended condition.Type: ApplicationFiled: May 17, 2021Publication date: September 2, 2021Applicant: SAFRAN LANDING SYSTEMS UK LTDInventor: Peter Sharpe
-
Publication number: 20210009258Abstract: An aircraft landing gear bogie beam including first and second ends and a mounting bearing for connection to an aircraft landing gear main strut between the ends. Each end has a respective axle, and each axle defines a wheel mounting portion on each side of the bogie beam. The bogie beam is arranged to enable the first and second axles to each pivot relative to the bearing about a respective longitudinal axis of the bogie beam by an amount that is sufficient to place a wheel rim of a wheel assembly in contact with the ground in the event of a tyre of the wheel assembly deflating.Type: ApplicationFiled: September 30, 2020Publication date: January 14, 2021Applicant: SAFRAN LANDING SYSTEMS UK LTDInventor: Robert Kyle Schmidt
-
Publication number: 20200392992Abstract: A bush assembly configured to be disposed between a first component and a second component movably coupled to the first component, the bush assembly comprising a first bush portion comprising a self-lubricating material; and a second bush portion, the second bush portion having greater electrical conductivity than the first bush portion, wherein the second bush portion provides a conductive path between the first component and the second component.Type: ApplicationFiled: June 11, 2020Publication date: December 17, 2020Applicant: SAFRAN LANDING SYSTEMS UK LTDInventors: Daniel Haikney, Neil Price
-
Publication number: 20200392991Abstract: A bearing having an electrically conductive sleeve and a self-lubricating liner wherein the electrically conductive sleeve comprises a first portion and a second portion, the first portion and the second portion having respectively an inner surface and an outer surface; the self-lubricating liner extends over the inner surface of the first portion of the electrically conductive sleeve to define a first tubular volume, the first tubular volume having a first diameter and a first longitudinal axis; and the inner surface of the second portion of the electrically conductive sleeve defines a second tubular volume, the second tubular volume having the same diameter and the same longitudinal axis as the first tubular volume.Type: ApplicationFiled: June 11, 2020Publication date: December 17, 2020Applicant: SAFRAN LANDING SYSTEMS UK LTDInventor: Ricky Peter Mansfield
-
Patent number: 10829209Abstract: An aircraft landing gear bogie beam including first and second ends and a mounting bearing for connection to an aircraft landing gear main strut between the ends. Each end has a respective axle, and each axle defines a wheel mounting portion on each side of the bogie beam. The bogie beam is arranged to enable the first and second axles to each pivot relative to the bearing about a respective longitudinal axis of the bogie beam by an amount that is sufficient to place a wheel rim of a wheel assembly in contact with the ground in the event of a tyre of the wheel assembly deflating.Type: GrantFiled: April 18, 2018Date of Patent: November 10, 2020Assignee: Safran Landing Systems UK LTDInventor: Robert Kyle Schmidt
-
Patent number: 10794407Abstract: 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.Type: GrantFiled: December 7, 2017Date of Patent: October 6, 2020Assignee: Safran Landing Systems UK LTDInventor: Yann Simonneaux
-
Patent number: 10759523Abstract: 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.Type: GrantFiled: December 7, 2017Date of Patent: September 1, 2020Assignee: Safran Landing Systems UK LTDInventor: Robert Kyle Schmidt
-
Publication number: 20200269972Abstract: 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.Type: ApplicationFiled: May 4, 2020Publication date: August 27, 2020Applicant: Safran Landing Systems UK LTDInventors: Nicholas Foster, Nikhil Sehgal, Daniel Mulley, Peter Scott
-
Publication number: 20200239132Abstract: An aircraft landing gear shock absorber assembly having: an outer cylinder having a bore which extends into the outer cylinder, the bore defining an opening in the outer cylinder; a sliding tube having a first end region slidably coupled within the bore and a second end region which projects out of opening; a ground fitting distinct from the sliding tube; and a mechanical fixing arranged to mechanically couple the ground fitting to the second end region of the sliding tube, wherein the sliding tube comprises a tubular body portion formed from a ceramic coated fibre composite tube.Type: ApplicationFiled: December 5, 2019Publication date: July 30, 2020Applicant: SAFRAN LANDING SYSTEMS UK LTDInventor: Ricky Peter Mansfield