Gloucester, United States
Gloucester, United States

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Patent
Messier Dowty Ltd | Date: 2016-08-17

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.


Patent
Messier Dowty Ltd | Date: 2017-01-18

A magnetic shock absorber (11) comprising a first body (12) slidably coupled to a second body (14) via a first bearing (24a) arranged to move in sliding engagement with a first counter-face portion (26a). A first array of magnets (18) associated with the first body is arranged to magnetically interact with a second array of magnets (22) is associated with the second body to absorb compression or extension loads applied to the shock absorber. The first bearing and the first counter-face portion each have a non-circular cross section profile (27) to inhibit axial relative rotation between the bodies.


Patent
Messier Dowty Ltd | Date: 2016-05-17

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.


Patent
Messier Dowty Ltd | Date: 2016-07-06

An aircraft spring assembly (10) includes a helical spring (12) having a hollow core (12c). A polymer damping member (16) is confined within the core (12c) and is narrower than the internal spring diameter so as to be free to move along the core (12c).


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.


Patent
Messier Dowty Ltd | Date: 2016-05-17

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.


Patent
Messier Dowty Ltd | Date: 2016-10-12

A hydraulic shock absorber (10) comprising an inner housing portion (12) slidably coupled to an outer housing portion (14) to define a variable size chamber for containing shock absorber fluid. The region where the inner and outer housing portions overlap defines an annulus (A) 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 (24) 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 electrorheological or magneto-rheological fluid and the shock absorber includes a device (28) for generating a magnetic or electric control field within the chamber at a region (R) adjacent to the 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.


Patent
Messier Dowty Ltd | Date: 2016-04-20

An aircraft landing gear assembly (10) includes a main strut and an axle (18b) on which wheel and brake assemblies (20b, 22b) are mounted. An adaptor member (30) is mounted on a mounting pin and arranged to define a brake rod anchor point (28). 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.


Patent
Messier Dowty Ltd | Date: 2016-12-07

An aircraft landing gear assembly (10) includes a mechanical structural linkage (12) comprising a conventional shock absorber (18) and a linkage abutment (20) which are biased apart by a mechanical spring (22).


Patent
Messier Dowty Ltd | Date: 2016-07-13

An aircraft landing gear assembly stop member (10) is arranged to be coupled to a first part (102) of an aircraft landing gear assembly (100) and includes a pair of projections (24, 26) which control movement of a second part (104) of the landing gear assembly to inhibit damage during installation.

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