Abstract: 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.

Abstract: 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. One of the first and second bearing surfaces includes a non-metallic material and the other of the first and second bearing surfaces includes cold worked titanium.

Abstract: A brake assembly for a vehicle comprising a wheel comprising a hollow section and a rim, the rim comprising a first portion comprising an electrically conductive material and a second portion adjacent to the first portion comprising a plurality of a permanent magnets and a stator comprising at least one electromagnetic coil arranged to be located within the hollow section of the wheel, wherein the stator is moveable between a first position in which the at least one electromagnetic coil is inductively coupled to the first portion of the rim when the wheel is rotating relative to the stator, and a second position in which the at least one electromagnetic coil is inductively coupled to the second portion of the rim.

Abstract: 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.

Abstract: A landing gear for an aircraft having a main fitting arranged to be coupled to the aircraft and arranged to move between a stowed condition and a deployed condition and a trailing arm movably coupled to the main fitting. A torsion spring is coupled to the trailing arm such that the movement of the trailing arm causes torsion loading of the torsion spring. A stay assembly is provided which comprises the torsion spring, the stay assembly having a first condition in which it is arranged to react axial loading thereof so as to maintain the main fitting in the deployed condition and a second condition in which it is arranged to permit the main fitting to move between the stowed condition and the deployed condition.

Abstract: A multifunction device for an undercarriage. The device comprises at least a first shaft rotatably mounted on the aircraft to rotate about an axis of rotation that is substantially parallel to a hinge axis hinging the undercarriage to the aircraft, and a telescopic second shaft rotatably mounted in the undercarriage and extending down along the undercarriage to the proximity of wheels carried thereby. A motor is adapted to cause the first shaft to rotate. The telescopic second shaft is a single shaft that extends inside the undercarriage to the proximity of an axle carrying the wheels of the undercarriage. The second shaft is connected to a differential connected to the wheels via drive shafts extending inside the axle.

Abstract: 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.

Abstract: 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 and a dynamic seal having a sealing face adjacent to the inner housing portion for confining shock absorber fluid to the chamber. The shock absorber fluid includes a colloidal suspension of inorganic particles in liquid, the colloidal suspension comprising 1-25% by weight inorganic particles.

Abstract: 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.

Abstract: 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.

Abstract: An aircraft landing gear assembly includes a fibre composite leaf spring arranged as a down lock spring to make the lock link.

Abstract: 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.

Abstract: 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.

Abstract: A brake rod assembly for an aircraft landing gear. The brake rod assembly includes a support member, a first brake rod having a first pivot point and a second pivot point, and a second brake rod. The support member is coupled to the first pivot point, the second brake rod is coupled to the second pivot point, and the first and second pivot points are longitudinally spaced apart along a first portion of the first brake rod.

Abstract: 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.

Abstract: 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.

Abstract: An aircraft landing gear having a strut having an upper portion for mechanically coupling to an aircraft and a lower portion movably mounted with respect to the upper portion. A bogie beam is pivotally coupled to the lower strut. A bogie control linkage is mechanically coupled to the bogie at a first connection point, and to the strut at a second connection point. The bogie control linkage has: an actuator including a locking system that inhibits actuation of the actuator; a sensor linkage mechanically coupled to the lower strut and arranged to change between first and second conditions in accordance with movement of the upper strut relative to the lower strut; and an actuator control linkage arranged to operate the locking system when the sensor linkage is in the first condition and arranged not to operate the locking system when the sensor linkage is in the second condition.

Abstract: A method of protecting an aircraft undercarriage (1) while it is being towed by means of a tow bar (13) hitched to a steerable bottom portion of the undercarriage, the method including the step of generating an alarm when a towing force imposed by the tow bar on the undercarriage reaches or exceeds a predetermined force threshold. The threshold is caused to vary as a function of an orientation of the steerable bottom portion of the undercarriage.

Abstract: A shock absorber assembly having a wheel assembly including first and second coupling points, and first and second shock absorber elements. Each shock absorber element includes a housing portion defining a bore, and a rod slidably coupled within the bore such that the shock absorber element has a variable length. Each rod is coupled to a respective coupling point of the wheel assembly. The shock absorber assembly is arranged to maintain the relative positions of the first and second housing portions such that the longitudinal axis of the first bore has a generally fixed relationship with respect to the longitudinal axis of the second bore.

Abstract: A landing gear for an aircraft having a main fitting arranged to be coupled to the aircraft and arranged to move between a stowed condition and a deployed condition and a trailing arm movably coupled to the main fitting. A torsion spring is coupled to the trailing arm such that the movement of the trailing arm causes torsion loading of the torsion spring. A stay assembly is provided which comprises the torsion spring, the stay assembly having a first condition in which it is arranged to react axial loading thereof so as to maintain the main fitting in the deployed condition and a second condition in which it is arranged to permit the main fitting to move between the stowed condition and the deployed condition.