Safran Landing Systems UK Ltd

Messier-dowty Inc.

The Boeing Company

Safran Landing Systems

Messier-dowty Sa

Ian Robert Bennett

Robert Menezes

Richard Charles Lang

Robert Anthony Menezes

Harry C Ralph

Dominique Ducos

Yann Simonneaux

Matthew Hilliard

Matthew Sexton

Paul Shaw

David Smart

Jean-François Locufier

Yann Simmonneaux

Matthew Craig Sexton

An aircraft landing gear assembly including a first structural member; a second structural member pivotally coupled to the first structural member to be movable between a first angular condition and a second angular condition; a down-lock spring having a first end region pivotally coupled to a mounting structure under tension to bias the first and second structural members to assume the first angular condition; and a linkage assembly including an arm member pivotally coupled to one of the first and second structural members at an arm pivot point, the arm having an first end region pivotally coupled to a second end region of the down-lock spring; and a control link pivotally coupled to one of the first and second structural members at a first control link pivot point and pivotally coupled to the arm member at a second control link pivot point.

Aircraft landing gear assembly

An aircraft landing gear shock absorber strut including a damping pin and a flow restricting plate having an orifice through which the metering pin axially moves as the sliding tube moves between the extended and compressed positions, wherein the damping pin or the flow restricting plate is coupled to a separator piston so as to move with the separator piston.

Aircraft landing gear shock absorber strut with movable damping pin and flow restricting plate

An aircraft landing gear shock absorber strut including an outer cylinder having a bore defining an opening; an inner cylinder having a first end region movably coupled within the bore and a second end region which projects out of the opening. The inner cylinder being arranged to move along a longitudinal axis of the bore between a first condition and a second condition and is biased by a spring force to assume the second condition. A mechanical outstop is arranged to engage an abutment surface of the inner cylinder to limit extension of the shock absorber strut; and a rotatable member drives the out stop axially to move the inner cylinder from the second condition towards the first condition. The rotatable member is arranged such that the spring force cannot rotate the rotatable member to allow the shock absorber strut to extend.

Aircraft landing gear shock absorber strut

An attachment assembly for an aircraft strut mounting joint. The attachment assembly includes a tubular structure having a central axis and at least one open end. The attachment assembly further includes at least one mounting pin arranged at least partially within the at least one open end of the tubular structure and moveable along the central axis between a retracted position and an extended position. In the extended position, a portion of the at least one mounting pin protrudes for engagement with a lug and in the retracted position the at least one mounting pin is withdrawn for disengagement with the lug. The attachment assembly further includes a retraction mechanism arranged to convert a rotary input motion into linear motion of the at least one mounting pin along the central axis to drive the at least one mounting pin between the extended position and the retracted position.

Pintle pin assembly mechanism

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.

A bearing arrangement having: a first element having an inner race and a first bearing surface; a second element, pivotable relative to the first element about a first axis, and having an outer race and a second bearing surface that cooperates with the first bearing surface to form a plain bearing. The bearing arrangement also includes a roller element disposed between the inner and outer races to form a rolling bearing. The inner and outer races are arcuate and subtend an angle of less than 360&#xb0; about the first axis.

Bearing arrangement

A mechanical lock for a vehicle assembly such as an aircraft landing gear assembly. The lock is either pivotally mounted and substantially mass balanced, or part of an aircraft landing gear assembly and arranged to be mechanically operated from the ground by a mechanical actuation device.

Lock and aircraft landing gear assembly

An aircraft landing gear assembly having a bogie beam pivotally coupled to a support member, and a pitch trimmer assembly including a pitch trimmer actuator configured to exert a biasing force in a first direction and a bias force transmission assembly configured to receive the biasing force in the first direction and bias the bogie beam towards a predetermined neutral position relative to the support member irrespective of the initial position of the bogie beam.

Aircraft landing gear and pitch trimmer assembly

An aircraft landing gear assembly having a bogie beam, first and second wheel assemblies mounted on the bogie beam on longitudinally opposite sides of the bogie beam with respect to a bogie mounting bearing, a jacking dome mounted on the bogie beam to face a ground plane, and a guard that is distinct from the jacking dome and removably coupled to the bogie beam on an opposite side of the jacking dome with respect to the bogie mounting bearing. The jacking dome projects towards the ground plane by a first distance, and the guard extends from the bogie beam towards the ground plane by a second distance which is at least 0.9 times the first distance.

Landing gear assembly

An aircraft assembly having a bush mounted within a lug and a recess which extends along a portion of the lug-bush interface to create a relatively wide cavity for receiving sealant.

Aircraft assembly

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. The bearing surface defines a bore and is arranged to support the shaft when the shaft is movably housed within the bore in use. The bearing surface is defined by the lug or a coating applied to the lug.

Dynamic bearing

An aircraft landing gear assembly having a main strut and a bogie beam pivotally coupled to the main strut via a coupling assembly. The coupling assembly is arranged to define a bogie beam pivot axis which is spaced from the landing gear assembly. The coupling assembly includes an arcuate handle portion defined by a first one of the bogie beam and the main strut, and an arcuate passage defined by the other one of the bogie beam and main strut. The arcuate handle portion is slidably housed within the arcuate passage, and the arcuate handle portion and the arcuate passage each define a respective centre point, the respective centre points being coaxial to define the bogie beam pivot axis.

An aircraft landing gear having a shock absorbing strut and a shortening mechanism coupled between a walking beam and a shortening portion of a shock absorber. The shortening mechanism is arranged such that when the walking 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 walking 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.

Aircraft landing gear

A mechanical lock () for a vehicle assembly such as an aircraft landing gear assembly. The lock is either pivotally mounted and substantially mass balanced, or part of an aircraft landing gear assembly () and arranged to be mechanically operated from the ground by a mechanical actuation device.

Growing community of inventors

Gloucester, United Kingdom

Ian Robert Bennett