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Aircraft retractable undercarriage strut Invention relates to aircraft (AC) alighting gears and concerns retractable undercarriage designs. Ac retractable undercarriage strut contains lever with wheel gimbal-mounted on fuselage, gear centring hydraulic cylinder with locks of extended and retracted position, where cylinder chambers are connected with AC hydraulic system, and gas-hydraulic shock-absorber one end of which is pivotally connected with the lever and the other - with fuselage. Hydraulic cylinder and shock-absorber are made articulated. Rods of hydraulic cylinder and shock-absorber are installed coaxially being capable to reciprocate relative to each other and to from cavities in one of which gas chamber is located and in the other liquid chamber is located. Hydraulic cylinder is provided with accumulating cavity with dividing piston and mechanical lock the elements of which are made capable to fix dividing piston in extended position and to contact with lock of retracted position. |
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Aircraft retractable landing gear (versions) Landing gear comprises lever with wheel articulated with fuselage, aligned hydraulic cylinder of landing gear in/out drive with locks of in/out positions, cylinder chambers being communicated with aircraft hydraulic system and has-hydraulic damper. The latter allows its chamber to be filled with working fluids via common charging union without their separation and is arranged in hydraulic cylinder chamber to make the pair “pipe-in-pipe” to act as hydraulic cylinder rod. Said hydraulic cylinder is equipped with high-pressure gas chamber composed by damper rod, piston fitted therein to interact with damper rod and extra fixed journal-box. |
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Hydraulic shimmy damper for aircraft landing gear Damper comprises hollow housing (10), cylinder piston (20) with the piston head, which forms two active hydraulic cameras, rod and deflecting units. A hydraulic compensator (40) is made with the internal volume of fluid medium, which is much greater than the volume of fluid medium removed from the housing. A hydraulic manifold (30) is located between the housing and hydraulic compensator. The control manifold is connected to the hydraulic compensator and establishes the passage between cameras. Manifold contains the interchangeable hydraulic valves (CV1, RV1; CV2, RV2) of the cartridge type for throttling of fluid medium flowing from cameras into the passage, allowing fluid medium to flow freely into cameras from the passage. |
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Invention refers to a bearing assy used as a support for a tubular element, in particular, to a lower bearing of the sliding tube of shock-absorber strut of the aircraft landing gear. Bearing (2') assy comprises body (3') supporting the first and the second annular supporting portions with the supporting surfaces, which contact with inner tubular element (1') in the areas distanced from each other in the axial direction. The annular supporting portions are represented either by separate supporting rings (4") installed in body element (3') with the supporting surfaces of different diameters, or by one supporting ring (4"), which can bend in the radial direction and is supported in such a way that the second annular supporting part can bend under effect of a load in the radial direction, while its supporting surface will occupy a position with a diameter bigger than the diameter of the supporting surface of the first annular supporting part (4"). Supporting ring (4") is installed in body (3') in seat (5") with shaped base (7") or conical base (9"). |
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Charging valve (versions) and method of its modification Charging valve comprises rod, pressure-sensitive device and intake section. Valve rod has first and second ends and channel extending there between. Pressure-sensitive device is located inside said channel on said first end and serves to measure pressure in pressurised tank. Intake section is arranged inside said channel between pressure-sensitive device and rid second end. Intake section is designed to rule out obstacles on fluid flow through the valve. Invention covers another design version of the valve and method of its modification. |
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The air hydraulic shock absorber consists of a cylinder, rod, plunger, movable and fixed axle boxes, hydraulic seals, gas and hydraulic chambers and a profiled needle. The shock absorber is equipped with an optimizing hydraulic double-stage regulator consisting of an internal bush with holes that is attached to the wall separating two spaces in the hydraulic chamber and linked with the plunger of the air hydraulic shock absorber fitted onto which is an external bush with holes with possibility of movement relative to the internal bush. Both bushes are interconnected by a multistart thread with a helix angle exceeding the friction angle, they are also connected by a flexible component. The profiled needle connected to the rod of the air hydraulic shock absorber enters the hole in the external bush of the optimizing hydraulic hydraulic double-stage regulator. |
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Hydromechanical damper comprises housing which receives pistons that are rigidly interconnected and held in the neutral position with a spring and lids with connecting pipes for connecting the above-piston spaces with hydraulic lines. The housing receives the additional sleeve covered with the lid. The sleeve receives orifice of constant flow section and adjustable orifice connected in series. The flow section of the adjustable orifice depends on the pressure drop at it. The orifices define the throttling device between the above-piston space and hydraulic line. The spring that holds the pistons in the neutral position are made of flexible members that can change the shape and volume. |
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Aircraft undercarriage shock-absorber leg Proposed shock-absorber leg includes cylinder, rod, piston, support and working member in form of system of rods made from monocrystals compressed to solid state between piston and support; generatrix of its surface corresponds to curve of diagram of operation of hydro-pneumatic shock absorber. |
Another patent 2551229.