Aircraft retractable landing gear (versions) |
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IPC classes for russian patent Aircraft retractable landing gear (versions) (RU 2534836):
        
 Hydraulic shimmy damper for aircraft landing gear / 2527612
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.
 Bearing assy / 2526305
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").
 Charging valve (versions) and method of its modification / 2445543
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.
 Air hydraulic shock absorber / 2261381
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.
 Hydromechanical damper / 2258848
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.
 Aircraft undercarriage shock-absorber leg / 2247679
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.
 The shock absorber chassis of the aircraft / 2188143
The invention relates to mechanical engineering and aeronautical engineering and, in particular, can be used in the construction of the chassis of the aircraft
 The shock absorber landing gear of the aircraft / 2183180
The invention relates to aviation and for the creation of a landing aircraft devices
 The shock absorber / 2182876
The invention relates to the field of engineering to the field of cushioning protection, machines and other objects, allowing a limited degree of mechanical loads
 Device for landing gear unlocking in extended position and landing gear equipped with such device / 2523366
Aircraft (AC) landing gear contains leg pivotally mounted on AC, capable to rotate around retraction axis. The leg can be stabilised in extended position by means of brace containing two pivotally interconnected connecting rods and can be held in aligned position by stabilising element containing two pivotally interconnected links. One of the links is pivotally connected with brace, and the second link is pivotally connected with landing gear leg or with AC. The links are held in their aligned and locked position. The landing gear contains unlocking device. The unlocking device contains rotary drive, crank lever, lever pivotally mounted on the crank lever end and comprising recess, pin, returning device pressing lever to the pin. Drive axis is parallel to pivot of stabilising element links. The crank lever is connected with rotary drive shaft. The pin is rigidly fixed to one of stabilising element links and protrudes from this link. The crank lever is made capable to be shifted from the first angular position where the pin contacts with the lever being opposite the recess when links are in aligned position, to the second angular position to which the lever comes when lever recess thrusts away the pin thus bringing the stabilising element links out of aligned position.
 Undercarriage nlg (versions) / 2513347
Invention relates to aircraft undercarriage retractable NLG, particularly to three-wheel undercarriage. NLG comprises nacelle, leg and extension mechanism. In the case of tail-first configuration, NLG hinge makes the sleeve fitted on front horizontal fin axle. Undercarriage can have nacelle solely for NLG wheel. Note here that NLG is arranged inside the fuselage recess between NLG hinge and wheel nacelle. Besides, NLG can be arranged outside the fuselage, nearby it between NLG hinge and wheel nacelle. Every hinged flap of the wheel nacelle is articulated with the lever arranged said nacelle to contact with said wheel. Besides, every said articulated flap can be engaged with the lever fitted on the same hinge and engaged with said flap by contracting spring while stroke limiter is arranged between said flap and lever.
 Device to decrease aircraft undercarriage length / 2488523
Invention relates to aircraft engineering. Undercarriage comprises leg to be hinged to aircraft airframe and lower part with wheels mounted thereat. Lower part can move relative to said leg. Additionally, undercarriage comprises device decreasing undercarriage length between extended and retracted positions. Said device comprises interconnected first and second means. Said first means is engaged with undercarriage lower part or with moving element to displace together when lower part displaces relative to leg. Second means is articulated to airframe to allow it go to stop unless undercarriage is in retracted position.
 Aircraft landing gear with folding brace stabiliser release / 2453471
Aircraft landing gear comprises leg 1 pivoted to aircraft, folding brace 10 with two levers 11, 12, and brace stabiliser 20 in straight position. Said stabiliser 20 comprises two rods 21, 22 pivoted together and telescopic release 30 (release drive), for example, simple-action hydraulic cylinder. End 32 of release drive rod 31 is coupled with one of said rods 22. Rod 22 has arc-like slot 26 to receive rod 31. End of release drive rod 31 makes free moves in said arc-like slot without obstructing displacement of rod 22 outside of zigzag line position.
 Aircraft landing gear with, at least, one noise killer / 2418716
Invention relates to aircraft engineering, particularly, to aircraft landing gear with noise killer and to aircraft equipped with said noise killer. Aircraft landing gear comprises noise killer 2, 3 linked with component 4 of said landing gear 1. Said noise killer 2, 3 incorporates separate circuit 5, 6 comprising geometrical cells 7. Note here that said circuit is arranged nearby component 4 so that one of its parts 8, 9 is, in fact, orthogonal with airflow E in final position of said component 4 with landing gear 1 in extended position.
 Aircraft retractable landing gear / 2415778
Invention relates to aircraft engineering, particularly, to retractable landing gear. Proposed landing gear comprises shock absorbing leg 1 with crosspiece 2 secured thereon and articulated with landing gear IN/OUT tie rod 5. Said tie rod 4 is articulated with IN/OUT drive and aircraft fuselage. Shock absorbing leg turn mechanism is made up of two tie rods 8 and 9 located on one plate and rocker 10 pivoted on aforesaid tie rod 5. First tie rod 8 has its one end secured to fuselage and its other end secured to first arm of rocker 10. Second tie rod 9 has its one end secured to shock absorbing leg 1 and its other end secured to second arm of rocker 10. To be locked in OUT position, shock absorbing leg 1 and crosspiece 2 are provided with detachable fasteners 7 that allow rigid attachment of shock absorbing leg 1 and crosspiece 2 to aircraft engine nacelle 6.
 Aircraft retractable landing gear / 2415777
Invention relates to aircraft engineering, particularly, to retractable landing gear. Proposed landing gear comprises leg 1 secured by suspension 2 to fuselage and articulated with folding brace 4 articulated with landing gear retraction drive 9, gear truck 3, damping cylinder 5, as well as gear truck turn mechanism with tie rod articulated with fuselage and damping cylinder 5. Said tie rod 6 is articulated with damping cylinder via ring 10 with lever 7 arranged on damping cylinder to rotate thereon and jointed with top link of splined hinge. Lever 7 is rigidly secured on ring 10 and has its free end pivoted to tie rod 6 of gear truck turn mechanism.
 Aircraft retractable landing gear / 2389650
Invention relates to aircraft engineering and aircraft retractable landing gear. Retractable landing gear consists of strut hinged to airframe, undercarriage, folding brace strut, retraction/extension drive, damper and undercarriage turning mechanism. Strut has hinged to be pivoted to folding brace strut, while folding brace strut other end is secured to airframe to revolve thereabout. Lever is arranged aligned with undercarriage wheels, oriented along flight direction and located in wheels rotational plane. Pivot is arranged on lever end for it to be jointed to said strut. Damper rod pivot joint is arranged between strut pivot joint and wheels axle on said lever. Dog is secured between aforesaid pivot joints in plane perpendicular to lever location plane. Proposed device comprises tie rod pivot-jointed to said dog and airframe. Said lever, dog and tie rod makes the wheels turning mechanism.
 Main landing gear of aircraft chassis / 2370413
Invention relates to aviation, namely to aircraft chassis gear. Walking-type chassis contains lifter and consists of shock-absorber hinge-connected to the aircraft framework. The shock-absorber is hinge-connected with brace coupled with carrier that actuates upper brace bearing hooking on a wing when the main landing gear is released. The carrier is provided with a tail, which is hinge-connected with a traction having hinged connection with framework. The brace is controlled by the lifter through the lever, which is hinge connected to the framework. Lifter and carrier are also in hinged connection with the lever. The lifter contains inner mechanical lock and is in hinge connection with the lever. One arm of the lever is hinge-fixed on lever framework, while the other arm is hinge connected with locking cylinder of emergency release of gear. The lock is represented with two jaws having grooves and latch, which are perpendicular to the released brace axis. Bushings of square external circuit are mounted on operating pins of the upper brace unit. Flat surfaces of bushings interact with hook grooves when main landing gear is released.
 Stand of aviation chassis / 2360835
Stand of aviation chassis comprises hydraulic cylinder, cross brace and cross beam. On cross beam contact platforms are arranged, which are inverted at the angle that provides for self-braking under action of landing loads, and carriage is fixed in central upper part of stand for trajectory of chassis pulling-in and extension.
 Aircraft landing gear main leg / 2297366
Aircraft landing gear leg has lever 1 with wheel 2 articulated on fuselage, gas-and-hydraulic shock absorber 4 whose rod 5 is articulated with lever, down lock 9, up lock 11 mounted on fuselage, down lock shackle 10, up lock shackle 12 articulated on lever, leg retraction-extension hydraulic cylinder 13. In center part, shock absorber body is articulated to member 7 made in form of fork whose other end is articulated via ears to cardan 8 which is articulated on fuselage; down lock is mounted on the same member ; down lock shackle is articulated on upper part of shock absorber body.
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FIELD: aircraft engineering. SUBSTANCE: 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. EFFECT: decreased overall dimensions owing to integrated damper and lifting hydraulic cylinder. 6 cl, 10 dwg
Group of inventions relates to a landing device for aircraft, in particular to the design features retractable landing gear. The prior art retractable chassis support aircraft (hereafter LA) containing the lever with the wheel, hinged to the fuselage, cylinder cleaning-release collet locks released and retracted, the cavity of which is connected with the hydraulic system of the aircraft by means of hydraulic locks, and remote gatherplace the absorber. In the damper casing movably mounted one end of the rod. The other end of the rod with a piston is installed in the housing of the hydraulic cylinder. The stem cavity filled with gas and performs the function of the gas chamber of the shock absorber. The hydraulic cylinder equipped with a plunger, one end of which is rigidly fixed in the housing, and the other, free end through a seal is installed in the cavity of the piston rod can move and change the volume of the gas chamber of the shock absorber (patent RF №2183179, IPC VS 25/10, VS 25/58, publ. 10.06.2002). This technical solution is adopted as a prototype for the claimed group of inventions. In a known construction for cleaning-release chassis uses two-way hydraulic cylinder including a housing, the piston forming two hydraulic chambers associated with hidrosis the emnd LA through hidrotambo and the plunger. In addition, the piston rod of the hydraulic cylinder is a piston rod of the shock absorber, therefore, exposed to significant stress during operation of the shock absorber, which causes the need for installation in hydraulic collet locks, prevents movement of the rod relative to the housing cylinder during landing and landing runway of the aircraft. This leads to weight gain, as it requires software support shaft and in the housing of the shock absorber, and in the case of lift, and the dimensions of the landing gear. The basis of the present group of inventions is tasked to create a combined unit, providing accommodation retractable landing gear LA in minimum size. Technical result achieved in the implementation of the present group of inventions is to reduce the size retractable landing gear LA by combining shock absorber and hydraulic cylinder-lift in a single unit, in which the stroke is used for depreciation, and on the cleaning issue. The task underlying the present invention is solved in that in a retractable landing gear of the aircraft on the first version of the run containing the lever with the wheel, hinged to the fuselage, coaxially arranged cylinder housekeeping issue with the locks released and retracted position, the cavity is connected with the Hydra is a system of the aircraft, and gatherplace the absorber, the latter made with the possibility of filling the cavity of the working media through a common charging socket without their separation and placed in the cavity of cylinder pairing "pipe in pipe" and the ability to perform the functions of the rod of the hydraulic cylinder, the hydraulic cylinder is supplied with gas by high-pressure chamber, a cavity which is formed by a damper rod, a piston mounted in this cavity that communicates with the damper rod, and additional fixed panel Jack. The task underlying the present invention is solved in that in a retractable landing gear of the aircraft on the second version of the run containing the lever with the wheel, hinged to the fuselage, coaxially arranged cylinder housekeeping issue with the locks released and retracted, the cavity of which is connected with the hydraulic system of the aircraft, and gatherplace the absorber, the latter is placed in the cavity of cylinder pairing "pipe in pipe" and the ability to perform the functions of the rod of the hydraulic cylinder, the hydraulic cylinder is supplied with gas by high-pressure chamber, a cavity which is formed by a damper rod, piston, established in the cavity, and an additional fixed panel Jack. Additional significant differences between the present group of inventions for two variants of execution are the body of the cylinder is pivotally connected to the lever and the damper rod with the fuselage. In addition, additional significant differences invention in the first embodiment, the execution consists in that the damper rod is arranged to move relative to the housing of the shock absorber during compression of the latter, it made a cavity filled with gas and liquid and soamsawali throttling holes with liquid cavity inside the absorber, and the hole for the charging nozzle for pouring liquid into the cavity of the damper rod and damper rod holes for flowing fluid in the fluid cavity of the shock absorber when it is filled, bypassing the throttling holes, and the rod has a spring-loaded valve. In addition, additional significant differences invention according to the second variant of implementation consists in that the damper rod is arranged to move relative to the housing of the shock absorber during compression of the latter, it made a cavity filled with gas and fluid, with a dividing piston and diaphragm with a calibrated orifice, which separates the liquid cavity absorber. Execution gothicrainbow shock absorber in the first embodiment, with the possibility of filling the cavity of the working media through General is ariadny fitting without their separation and its placement in the cavity of cylinder pairing "pipe in pipe" and the ability to perform the functions of the rod of the hydraulic cylinder allows to reduce the longitudinal dimensions of the shock absorber and cylinder-lift due to parallel inclusion in the dimension chain of the distance between the supports of the hydraulic cylinder-lift, while in the known construction the specified distance is included in the dimension chain sequence. Accommodation gothicrainbow shock absorber according to the second variant in the cavity of cylinder pairing "pipe in pipe" and the ability to perform the functions of the rod of the hydraulic cylinder also allows to reduce the longitudinal dimensions of the shock absorber and hydraulic cylinder-lift due to parallel inclusion in the dimension chain of the distance between the supports of the hydraulic cylinder-lift. The supply cylinder gas high-pressure chamber (discharge chamber) in two variants of execution allows this design to perform a dual function - directly Luggage unloading, to reduce the efforts of the moving rod, and the Cam brake cylinder at the end of the release. These characteristics are essential and interrelated with the formation of a stable set of essential features, sufficient to obtain the technical result. The comparative analysis of proposed technical solutions to identified analogues of the prior art from which the invention is not obvious to special the hundred in the field of landing device for aircraft, showed that it is unknown, and given opportunities for industrial mass production retractable landing gear LA can be concluded about its compliance with the criteria of patentability. The present invention is illustrated with a specific example of implementation of the proposed retractable landing gear for aircraft, which demonstrates the ability to obtain the technical result. Allowed various modifications and improvements that are not beyond the scope of the invention defined by the attached claims. Presents options group of the invention are described hereinafter based on the drawings, where in Fig.1 shows a retractable landing gear for aircraft, option 1; in Fig.2 shows a retractable chassis support with LA pobratim absorber-lift in a released position, option 1; in Fig.3 - the same, with shock absorber-lift in a released position, objitem on the course of unloading, option 1; in Fig.4 - the same, with shock absorber-lift in a released position, objitem at full speed, option 1; in Fig.5 - the same, with pobratim absorber-lift when removed from the lock released position, option 1; in Fig.6 - the same, with pobratim absorber-lift, taken from castles in the intermediate position, option 1; in Fig.7 - the same, with pobratim Amor is Isadora-lift in the retracted position, option 1; in Fig.8 presents a diagram of a retractable landing gear for aircraft, option 2; in Fig.9 shows a retractable chassis support with LA pobratim absorber-lift in a released position, option 2; in Fig.10 presents a comparison of the layout schemes of the prototype and of the claimed invention. Graphic materials relevant structural elements of a retractable landing gear LA is indicated by the following positions: 1 - the lever; 2 - wheel; 3 - shock absorber-lift; 4 - stock; 5 - cover; 6 - cylinder shock absorber; 7 - Bush of mobile; 8 - Buchs; 9 - Buchs; 10 - the case of the hydraulic cylinder-lift; 11 Bush motionless; 12 - cavity production; 13 - cavity cleaning; 14 - fitting; 15 - fitting; 16 - Cup, 17 - calibrated holes; 18 - cavity liquid-gas; 19 - cavity liquid; 20 - holes; 21 - bushing spacer; 22 is spring-loaded valve; 23 - holes; 24 - socket charger; 25 - socket charger; 26 - unloading chamber (nitrogen high-pressure chamber); 27 - piston discharge chamber; 28 - collet lock released position; 29 - emphasis of the lock released position; 30 - retainer lock released position; 31 - spring lock released position; 32 - plunger lock released state is; 33 - collet lock the retracted; 34 - emphasis castle retracted position; 35 - retainer lock the retracted; 36 - spring lock retracted position; 37 - plunger lock the retracted; 38 - absorber-lift, version 2; 39 stock, option 2; 40 - cover, option 2; 41 - cylinder shock absorber option 2; 42 is a piston dividing; 43 - aperture with calibrated holes; 44 - nitrogen low-pressure chamber; 45 - Luggage liquid; 46 - cavity liquid; 47 - needle; 48 - fitting charger; 49 - case handling of the camera. Retractable bearing chassis LA, in the first embodiment, the execution is suspended from the hinge on the body LA of the lever 1 (see Fig.1) with a fixed wheel 2 and the damper-lift 3, the eyelet on the rod 4 pivotally mounted on the body of the aircraft, and a lug on the housing cover 5 is also pivotally connected with the lever 1. The shaft 4 (see Fig.2) installed in the cylinder 6 of the shock absorber lift using movable journal-boxes 7 and overlays 8, located on the rod 4. 6-cylinder shock absorber-lift is backed by pan 9, rigidly related to it, on the inner surface of the housing 10 of the hydraulic cylinder-lift, and the stem 4 on the stationary buxu 11 installed in the housing 10 of the hydraulic cylinder-lift. When the cylinder 6 of the shock absorber is under the of amnike together with the rod 4 is able to move inside the housing 10 of the hydraulic cylinder-lift on these supports when harvesting and production of landing gear, and the Bush 9 is a piston cylinder. The cavity 12 and cavity cleaning 13 of the hydraulic cylinder-lift is connected to the hydraulic system of the AIRCRAFT (not shown) by means of the fittings 14 and 15, respectively. Inside the rod 4 is mounted glass 16 with calibrated holes 17, which separates the cavity 18 is filled with nitrogen and the liquid from the liquid cavity 19 that is located inside the cylinder 6 of the shock absorber-lift. The cavity 18 also communicates with the fluid cavity 19 through the holes 20 in the stem 4, the holes in the spacer sleeve 21, the spring loaded valve 22 and openings 23 in the Cup 16. While the holes in the spacer sleeve 21 can be blocked by a spring-loaded valve 22. In the upper part of the cavity 18 is connected with the charging socket 24. Charging fitting 25 is connected to a nitrogen high-pressure chamber 26 (discharge chamber). The piston 27 of the discharge chamber 26 through the movable buxu 7 has an emphasis in the stem 4. In the enclosure 10 of the hydraulic cylinder-lift located collet locks released and retracted. Lock released position consists of collet 28, the stop 29, rigidly connected to the cylinder 6 of the shock absorber-lift latch 30, a spring 31 and the plunger 32. Lock the retracted consists of the collet 33, the stop 34, rigidly connected to the cylinder 6 of the shock absorber-lift latch 35, the spring 36 and the pusher 37. In a retractable landing gear for aircraft,according to the second variant of execution (Fig.8), the lever 1 with a fixed wheel 2 is similar to the design in Fig.1 pivotally suspended on the body of the aircraft. When this shock-lift 38 is inverted. The eyelet on the rod 39 he is pivotally connected with the lever 1, and a lug on the housing cover 40 is hinged to the body of the aircraft. Shock-lift 38 consists of a rod 39 (see Fig.9) mounted in the cylinder 41 of the damper lift using movable journal-boxes 7 and overlays 8, located on the rod 39. The cylinder 41 of the damper lift 38 is backed by pan 9, rigidly related to it, on the inner surface of the housing 10 of the hydraulic cylinder-lift, and the rod 39 on the fixed buxu 11 installed in the housing 10 of the hydraulic cylinder-lift. When the cylinder 41 of the damper lift 38 together with the rod 39 has the ability to move inside the housing 10 of the hydraulic cylinder-lift on these supports when harvesting and production of landing gear, and the Bush 9 is a piston of the hydraulic cylinder-lift. The cavity 12 and cavity cleaning 13 of the hydraulic cylinder-lift is connected to the hydraulic system of the AIRCRAFT (not shown) by means of the fittings 14 and 15, respectively. Inside the rod 39 has a movable separating piston 42 and aperture with a calibrated orifice 43. The separating piston 42 separates nitrogen the low-pressure chamber 44 from the liquid chamber 45 located in the stem 39. Aperture with kalibawang the m hole 43 separates the liquid chamber 45 from the cavity 46, connected by means of a needle 47 with charging socket 24. Charger socket 48 is used for charging nitrogen chamber low pressure 44 and the charging nozzle 25 is connected to a nitrogen high-pressure chamber 26 (discharge chamber). The piston of the discharge chamber 27 is moved in the housing 49 of the discharge chamber through the movable journal-boxes 7 and has an emphasis in the stem 4. In the enclosure 10 of the hydraulic cylinder-lift located collet locks released and retracted. Lock released position consists of collet 28, the stop 29, rigidly connected to the cylinder 38 of the shock absorber-lift latch 30, a spring 31 and the plunger 32. Lock the retracted consists of the collet 33, the stop 34, rigidly connected to the cylinder 38 of the shock absorber-lift latch 35, the spring 36 and the pusher 37. Retractable chassis support aircraft operates as follows. Fill shock absorber-lift, shown in Fig.2, hydraulic fluid is as follows. Through the hole for the charging nozzle 24 is filled with fluid in the cavity 18. As an orifice 17 in the Cup 16 are small enough, and the pressure of the liquid column in the chamber 18 is relatively small, the filling of the cavity 19 through which virtually does not occur. The liquid flows into the cavity 19 through the holes 20 in the stem 4, the holes in the spacer sleeve 21 and the valve 22, which is of Tcrit under the action of the spring, and the holes 23 in the Cup 16. Shock-lift 3 to option 1 (see Fig.1), as well as shock-lift 38 option 2 (see Fig.8), is a combined unit and can operate in two modes. In the mode of the shock absorber is provided by the absorption of the work during the landing ground roll and run LA, and lift the harvesting and production support and holding it in released and retracted positions by means of respective locks. Shock-Elevator 3 (see Fig.1) works as follows. In the mode of the shock absorber the shock absorber cylinder 6-lift (see Fig 2) stationary relative to the housing 10 of the hydraulic cylinder-lift, move it holds the lock released position. When the perception of the shock absorber is its compression, that is, the moving rod 4 relative to the cylinder 6 of the shock absorber-lift. The volume of the cavity 19 decreases, which leads to the flow of fluid from the braking of the cavity 19 in the cavity above the panel Jack 8 through the openings in the latter and into the cavity 18 through an orifice 17, and compression of the gas in the cavity 18. Through the holes 20 in stock 4 fluid in the cavity 18 does not flow as a spring-loaded valve 22 their overlaps. The impact energy is thus stored in the compressed gas and partially consumed when the flow through the holes. When the compression of the shock absorber lift n the move, not exceeding the stroke of the discharge chamber 27 (see Fig.3) specified the piston under the action of compressed gas in nitrogen high pressure chamber 26 abuts via mobile buxu 7 in stock 4, moving with him. The force on the rod 4 from the piston 27 of the discharge chamber is opposite in direction to the force acting on the rod 4 from the liquid environment of the cavity 19 and the cavity 18, but less than its size, that is, it reduces the axial force on the rod 4 shock absorber-lift. Thus, the presence of nitrogen in the high pressure chamber 26 (discharge chamber) with the piston 27 of the discharge chamber can significantly reduce the force of the moving rod 4 shock absorber-lift. When the compression of the shock absorber-lift to move greater than the stroke of the piston 27 of the discharge chamber (see Fig.4), within the cylinder 6 of the shock absorber lift moves the rod 4. Move pan 7 and the piston 27 of the discharge chamber is limited by a stop in the cylinder 6 of the shock absorber, i.e. reduction efforts on the rod 4 from nitrogen high-pressure chamber 26 does not occur. When the operation of the lift rod 4 (see Fig.5) fixed with respect to the cylinder 6 of the shock absorber-lift and is in a released position on the fence. From moving inside the cylinder 6 of the shock absorber lift it holds the pressure in the cavities 18 and 19 of the shock absorber-lift. When cleaning or release supports qi is indr 6 shock absorber-lift moves in the housing 10 of the hydraulic cylinder-lift to the setting of the castle retracted or released position. The cleaning process of the support can be divided into three stages: the removal of the lock released position, moving the damper lift in the housing 10 of the hydraulic cylinder-lift and the setting of the castle retracted position. It is as follows. Fluid from the hydraulic system LA is fed into the cavity of the cleaning 13, and the cavity 12 is communicated with the drain. This moves the plunger 32 with the retainer 30, compressing the spring 31 and releasing the collet 28. The hydraulic pressure in the cavity cleaning 13 also acts on buxu 9 associated with 6 cylinder shock absorber-lifts, and moves it. When moving cylinder 6 shock absorber lift the stop 29 pushes the released the collet 28, leaving the lock released position (see Fig.6). Also early in the course of cleaning the absorber-lift force acts from the side of the piston 27 of the discharge chamber. The movement of the shock absorber lift occurs before the setting of the castle retracted position. At the end of the cleaning stop 34 (see Fig.7) of the cylinder 6 of the shock absorber lift pushes the petals of the collet 33 is retracted and included them in the engagement, after the closure of the castle due to the force of the spring 36 which presses the latch 35, which holds the petals of the collet 33 from the opening. The release bearing is similar to cleaning in three stages: the descent from the castle retracted state is, the movement of the shock absorber lift in the housing 10 of the hydraulic cylinder-lift and putting on the lock released position. When this fluid is respectively fed into the cavity 12, and a cavity cleaning 13 is communicated with the drain. At the end of output to a shock absorber is the lift force acts from the side of the piston 27 of the discharge chamber (see Fig.6). In this case, the unloading chamber 26 operates as Luggage brake cylinder. The shock absorber is the lift on the second version execution works as follows. In the mode of the shock absorber lift cylinder 41 (see Fig.9) fixed relative to the housing 10 of the hydraulic cylinder-lift, move it holds the lock released position. When the perception of the shock absorber-lift is the compression, that is, the moving rod 41 39 on the cylinder of the shock absorber-lift. The volume of the cavity 46 decreases, which leads to the flow of fluid from the braking of the cavity 46 in the cavity behind the panel Jack 8 through the openings in the latter, and through a calibrated aperture 43 in the liquid chamber 45. This in turn leads to the displacement of the separating piston 42 and the compression of the gas in the cavity nitric camera low pressure 44. The impact energy is thus stored in the compressed gas and partially consumed when the flow through the holes. When about is gatii shock absorber-lift to move not exceeding the stroke of the piston 27 and the discharge chamber 26, the said piston under the action of compressed gas in the nitrogen chamber high-pressure discharge chamber 26) rests via mobile buxu 7 in the rod 39, moving with him. The force on the rod 39 from the piston 27 and the discharge chamber 26 is opposite in direction to the force acting on the rod 39 from the environment cavities shock absorber-lift, but less than its size, that is, it reduces the axial force on the rod 39 shock absorber-lift. Thus, the presence of nitrogen high-pressure chamber (discharge chamber 26 with the piston 27 can significantly reduce the effort of moving the rod 39 shock absorber-lift. When the compression of the shock absorber-lift to move greater than the stroke of the piston 27 and the discharge chamber 26, the inside of the cylinder 41 of the damper lift moves the rod 39. Move pan 7 and the piston 27 and the discharge chamber 26 is limited by a stop in the cylinder 41 of the damper lift, i.e. reduction efforts on the rod 39 from nitrogen high-pressure chamber 26 does not occur. When the operation of the lift rod 39 fixed with respect to the cylinder 41 of the damper lift and is in a released position on the fence. From moving inside the cylinder 41 of the damper lift it holds the pressure in the cavities of the shock absorber. When cleaning or release bearing cylinder 41 is of amortizatory-lift moves in the housing 10 of the hydraulic cylinder-lift to the setting of the castle retracted or released position. The cleaning process of the support can be divided into three stages: the removal of the lock released position, moving the damper lift in the housing 10 of the hydraulic cylinder-lift and the setting of the castle retracted position. It is as follows. Fluid from the hydraulic system LA is fed into the cavity of the cleaning 13, and the cavity 12 is communicated with the drain. This moves the plunger 32 with the retainer 30, compressing the spring 31 and releasing the collet 28. The hydraulic pressure in the cavity cleaning 13 also acts on buxu 9 associated with the cylinder 41 of the damper lift, and when it moves it. When moving cylinder 41, the stop 29 pushes the released the collet 28, leaving the lock released position. Also early in the course of cleaning the absorber-lift force acts from the side of the piston 27 and the discharge chamber 26. The movement of the shock absorber lift occurs before the setting of the castle retracted position. At the end of the cleaning stop 34 of the cylinder of the shock absorber 6 he opens the petals of the collet 33 is retracted and included them in the engagement, after the closure of the castle due to the force of the spring 36 which presses the latch 35, which holds the petals of the collet 33 from the opening. The release bearing is similar to cleaning in three stages: the descent from the castle retracted position, movement of the damper lift in the housing 10 g is of drollinger-lift and putting on the lock released position. When this fluid is respectively fed into the cavity 12, and a cavity cleaning 13 is communicated with the drain. At the end of output to a shock absorber is the lift force acts from the side of the piston 27 and the discharge chamber 26. In this case, the unloading chamber 26 operates as Luggage brake cylinder. The main distinctive feature of the invention is the arrangement of the joint Assembly, shock absorber-lift. In the prototype this unit arranged in series, and in both embodiments of the invention the absorber-lift is inside the cylinder, is moved inside for cleaning and release and can say that is the rod of the hydraulic cylinder. If we consider the schematic of which is mainly formed of the longitudinal dimensions of both units (see Fig.10), we can see that: L=S+b1+S+b2+S L=S+b2+S+S where L - lengthwise dimension of the prototype; S - harvesting process of hydraulic cylinder-lift; b1 is the distance between the values of the hydraulic cylinder-lift; b2 is the distance between the values of the absorber-lift; L - lengthwise dimension of the proposed design. That is, the reduction in the longitudinal dimension is due to the parallel connection in the dimension chain distances between values of hydraulic cylinder-lift. brezec offer retractable landing gear LA was developed on the basis of a detailed experimental investigation of the design and process of its work. Manufacturer offer retractable landing gear LA does not require the development of new equipment and retrofitting of existing facilities, and the used tools are widely used in the aviation industry, which confirms the possibility of practical implementation and achievement of the technical result. 1. Retractable bearing chassis of the aircraft, containing the lever with the wheel, hinged to the fuselage, coaxially arranged cylinder housekeeping issue with the locks released and retracted, the cavity of which is connected with the hydraulic system of the aircraft, and gatherplace the shock absorber, characterized in that last made with the possibility of filling the cavity of the working media through a common charging socket without their separation and placed in the cavity of cylinder pairing "pipe in pipe" and the ability to perform the functions of the rod of the hydraulic cylinder, the hydraulic cylinder is supplied with gas by high-pressure chamber, a cavity which is formed by a damper rod, piston, mounted in this cavity that communicates with the damper rod, and additional fixed panel Jack. 2. Reliance on p. 1, characterized in that the damper rod is arranged to move relative to the housing of the shock absorber during compression of the latter, when it is done is in the cavity, filled with gas and liquid and soamsawali throttling holes with liquid cavity inside the absorber, and the hole for the charging nozzle for pouring liquid into the cavity of the damper rod and damper rod holes for flowing fluid in the fluid cavity of the shock absorber when it is filled, bypassing the throttling holes, and the rod has a spring-loaded valve. 3. Reliance on p. 1, characterized in that the housing of the hydraulic cylinder pivotally connected to the lever and the damper rod with the fuselage. 4. Retractable bearing chassis of the aircraft, containing the lever with the wheel, hinged to the fuselage, coaxially arranged cylinder housekeeping issue with the locks released and retracted, the cavity of which is connected with the hydraulic system of the aircraft, and gatherplace the shock absorber, characterized in that the latter is placed in the cavity of cylinder pairing "pipe in pipe" and the ability to perform the functions of the rod of the hydraulic cylinder, the hydraulic cylinder is supplied with gas by high-pressure chamber, a cavity which is formed by a damper rod, a piston mounted in the cavity, and an additional fixed panel Jack. 5. Reliance on p. 4, characterized in that the damper rod is arranged to move relative to the pus of the shock absorber during compression of the latter, it made a cavity filled with gas and fluid, with a dividing piston and diaphragm with a calibrated orifice, which separates the liquid cavity absorber. 6. Reliance on p. 4, characterized in that the damper rod pivotally connected to the lever and the housing of the hydraulic cylinder with the fuselage.
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