RU2534836C1 - Aircraft retractable landing gear (versions) - Google Patents

Abstract

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

Description

The group of inventions relates to takeoff and landing devices of aircraft, in particular to the design features of retractable landing gear.

A retractable landing gear support of the aircraft (hereinafter referred to as LA) is known from the prior art, comprising a lever with a wheel pivotally mounted on the fuselage, a cleaning-release hydraulic cylinder with collet locks of the released and retracted positions, the cavities of which are connected to the aircraft hydraulic system by means of hydraulic locks, and a remote gas-hydraulic shock absorber . In the body of the shock absorber, one end of the rod is movably mounted. The other end of the piston rod is mounted in the cylinder body. The stem cavity is filled with gas and acts as a gas chamber of the shock absorber. The hydraulic cylinder is equipped with a plunger, one end of which is rigidly fixed in the housing, and the other, the free end by means of seals, is installed in the rod cavity with the ability to move and change the volume of the gas chamber of the shock absorber (RF patent No. 2183179, IPC V64C 25/10, V64C 25/58, publ. 10.06.2002).

This technical solution was adopted as a prototype for the claimed group of inventions.

In the known design, for cleaning the landing gear, a double-sided hydraulic cylinder is used, including a housing, a rod with a piston forming two hydraulic chambers connected to the aircraft hydraulic system through hydraulic locks and a plunger. In addition, the rod of the hydraulic cylinder is the rod of the shock absorber, therefore, it is subject to significant loads during the operation of the shock absorber, which necessitates the installation of collet locks in the hydraulic cylinder to prevent the rod from moving relative to the cylinder body during landing and run along the aircraft runway. This leads to an increase in weight, since it requires supporting the rod both in the shock absorber body and in the lift body, and the dimensions of the landing gear.

The basis of this group of inventions is the task - the creation of a combined unit that provides placement of retractable landing gear of the aircraft chassis in a minimum size.

The technical result achieved by the implementation of this group of inventions is to reduce the size of the retractable landing gear of the aircraft by combining a shock absorber and a lifting hydraulic cylinder into a single unit, in which the stroke is used for depreciation and for harvesting.

The task underlying the present invention is solved by the fact that in the retractable landing gear of the aircraft according to the first embodiment, comprising a lever with a wheel pivotally mounted on the fuselage, coaxially located cleaning-release hydraulic cylinder with locks of the released and retracted position, the cavities of which are connected with the hydraulic system of the aircraft, and the gas-hydraulic shock absorber, the latter made with the possibility of filling the cavity with working media through a common charging nozzle without separation and placed on the floor STI cylinder to form a pair of "tube in tube" and perform the functions of the hydraulic cylinder rod, wherein the cylinder is provided with a high pressure gas chamber, wherein the cavity formed by suspension rod piston mounted in said cavity communicating with the suspension rod, and an additional stationary axle box.

The task underlying the present invention is also solved by the fact that in the retractable landing gear of the aircraft according to the second embodiment, comprising a lever with a wheel pivotally mounted on the fuselage, coaxially arranged cleaning-release hydraulic cylinder with locks of the released and retracted position, the cavities of which connected with the hydraulic system of the aircraft, and a gas-hydraulic shock absorber, the latter is placed in the cavity of the hydraulic cylinder with the formation of a pair of "pipe in pipe" and the ability to perform the functions of the hydraulic stem ilindra, wherein the cylinder is provided with a high pressure gas chamber, wherein the cavity formed by the shock absorber rod, a piston mounted in the cavity, and an additional stationary axle box.

Additional significant differences of this group of inventions in two versions are that the cylinder body is pivotally connected to the lever, and the shock absorber rod is connected to the fuselage.

In addition, additional significant differences of the invention in the first embodiment are that the shock absorber rod is movable relative to the shock absorber housing when the latter is compressed, while a cavity is filled therein, filled with gas and liquid and communicating with throttling holes with a liquid cavity inside the shock absorber body, and an opening for a charging nipple for pouring liquid into the cavity of the shock absorber rod, and openings for flowing liquid into bone cavity when filling suspension, bypassing the throttle opening, and the rod mounted on spring-loaded valve.

In addition, additional significant differences of the invention according to the second embodiment are that the shock absorber rod is movable relative to the shock absorber body during compression of the latter, while a cavity filled with gas and liquid is made in it, with a separation piston and a diaphragm with a calibrated hole, which divides the fluid cavity of the shock absorber.

The implementation of the gas-hydraulic shock absorber according to the first embodiment, with the possibility of filling the cavity with working fluids through a common charging nozzle without separating them and placing it in the hydraulic cylinder cavity with the formation of a pipe-in-pipe pair and the possibility of performing the functions of the hydraulic cylinder rod, reduces the longitudinal dimensions of the shock absorber and the hydraulic lift cylinder due to parallel inclusion in the dimensional chain of the distance between the supports of the hydraulic cylinder-lift, while in a known design the specified distance in lyucheno in dimensional circuit sequentially.

The placement of the gas-hydraulic shock absorber according to the second embodiment in the cavity of the hydraulic cylinder with the formation of a pipe-in-pipe pair and the possibility of fulfilling the functions of the hydraulic cylinder rod also makes it possible to reduce the longitudinal dimensions of the shock absorber and the hydraulic lift cylinder due to the parallel inclusion of the distance between the supports of the hydraulic lift cylinder in the dimensional chain.

The supply of the hydraulic cylinder with a high-pressure gas chamber (unloading chamber) in two versions allows this design to perform a dual function - directly the unloading chamber, to reduce the force of breaking the rod, and the braking chamber of the hydraulic cylinder at the end of the exhaust stroke.

These signs are significant and interconnected with the formation of a stable set of essential features sufficient to obtain the specified technical result.

A comparative analysis of the proposed technical solution with identified analogues of the prior art, from which the invention does not explicitly follow for a specialist in the field of aircraft landing devices, showed that it is unknown, and given the possibility of industrial serial production of a retractable landing gear of the aircraft chassis, we can conclude about it eligibility criteria.

The present invention is illustrated by a specific example of the proposed retractable landing gear of the aircraft, which clearly demonstrates the possibility of obtaining the specified technical result. Various modifications and improvements are permitted without departing from the scope of the invention as defined by the appended claims.

Presented embodiments of the group of inventions are described below based on the drawings, where

figure 1 presents a diagram of a retractable landing gear LA, option 1;

figure 2 shows the retractable landing gear of the aircraft with uncompressed shock absorber-lift in the released position, option 1;

figure 3 is the same, with a shock absorber-lift in the released position, compressed on the course of unloading, option 1;

figure 4 is the same, with a shock absorber-lift in the released position, pressed out at full speed, option 1;

figure 5 is the same, with an unpressed shock absorber-lift when removing the released position from the lock, option 1;

figure 6 is the same with an unpressed shock absorber-lift, removed from the locks, in an intermediate position, option 1;

Fig.7 is the same, with an unpressed shock absorber-lift in the retracted position, option 1;

on Fig presents a diagram of a retractable landing gear aircraft, option 2;

figure 9 shows the retractable landing gear of the aircraft with an unpressed shock absorber-lift in the released position, option 2;

figure 10 presents a comparison of the layout schemes of the prototype and the claimed invention.

In graphic materials, the corresponding structural elements of the retractable landing gear of the aircraft chassis are indicated by the following positions:

1 - lever;

2 - wheel;

3 - shock absorber-lift;

4 - stock;

5 - housing cover;

6 - shock absorber cylinder;

7 - axle box movable;

8 - axle box;

9 - axle box;

10 - the housing of the hydraulic lift cylinder;

11 - axle box motionless;

12 - cavity release;

13 - cavity cleaning;

14 - fitting;

15 - fitting;

16 - a glass;

17 - calibrated holes;

18 - a liquid-gas cavity;

19 - liquid cavity;

20 - holes;

21 - spacer sleeve;

22 - spring-loaded valve;

23 - holes;

24 - charging connector;

25 - charging connector;

26 - discharge chamber (high pressure nitrogen chamber);

27 - the piston of the discharge chamber;

28 - collet of the released position lock;

29 - emphasis lock issued position;

30 - lock lock released position;

31 - spring lock released position;

32 - pusher lock released position;

33 - collet of the lock of the retracted position;

34 - emphasis of the lock of the retracted position;

35 - lock lock retracted position;

36 - lock spring retracted position;

37 - pusher lock retracted position;

38 - shock absorber-lift, option 2;

39 - stock, option 2;

40 - housing cover, option 2;

41 - shock absorber cylinder option 2;

42 - dividing piston;

43 - diaphragm with calibrated holes;

44 - nitrogen chamber of low pressure;

45 - liquid chamber;

46 - liquid cavity;

47 - a needle;

48 - charging connector;

49 - the body of the discharge chamber.

The retractable landing gear of the aircraft chassis, according to the first embodiment, consists of a lever 1 pivotally suspended on the aircraft body (see Fig. 1) with a wheel 2 mounted on it, and a shock absorber-lift 3, an eye on the rod 4 pivotally mounted on the aircraft body, and an eye on the lid of the housing 5 is also pivotally connected to the lever 1.

The rod 4 (see figure 2) is installed in the cylinder 6 of the shock absorber-lift using a movable axle box 7 and axle box 8 located on the rod 4. The cylinder 6 of the shock absorber-lift is supported by the axle box 9, rigidly connected with it, on the inner surface of the housing 10 a hydraulic lift cylinder, and the rod 4 to a fixed axle box 11 installed in the housing 10 of the hydraulic lift cylinder. In this case, the cylinder 6 of the shock absorber-lift together with the rod 4 has the ability to move inside the housing 10 of the hydraulic cylinder-lift on the indicated supports when cleaning and releasing the landing gear, and the axle box 9 is the piston of the hydraulic cylinder. The exhaust cavity 12 and the cleaning cavity 13 of the hydraulic lift cylinder are connected to the aircraft hydraulic system (not shown) by means of fittings 14 and 15, respectively. A cup 16 with calibrated holes 17 is installed inside the stem 4, separating the cavity 18 filled with nitrogen and liquid from the fluid cavity 19 located inside the cylinder 6 of the shock absorber-lift. The cavity 18 also communicates with the fluid cavity 19 through the openings 20 in the stem 4, the openings in the spacer sleeve 21, the spring-loaded valve 22, and the openings 23 in the nozzle 16. In this case, the openings in the spacer sleeve 21 can be blocked by the spring-loaded valve 22. In the upper part, the cavity 18 connected to the charging nipple 24. The charging nipple 25 is connected to the high pressure nitrogen chamber 26 (discharge chamber). The piston 27 of the unloading chamber 26 through the movable axle box 7 has an emphasis on the rod 4. At the ends of the housing 10 of the hydraulic lift cylinder are located collet locks of the released and retracted positions. The lock of the released position consists of a collet 28, an abutment 29, rigidly connected with the cylinder 6 of the shock absorber-lift, a retainer 30, a spring 31 and a pusher 32. The lock of the retracted position consists of a collet 33, an emphasis 34, rigidly connected with the cylinder 6 of the shock absorber-lift, a clamp 35, springs 36 and pusher 37.

In the retractable landing gear of the aircraft, according to the second embodiment (Fig. 8), the lever 1 with the wheel 2 mounted on it is similarly to the structure in Fig. 1 pivotally suspended on the aircraft body. When this shock absorber-lift 38 is upside down. The eye on the rod 39, it is pivotally connected to the lever 1, and the eye on the cover of the housing 40 is pivotally mounted on the aircraft body. The shock absorber-lift 38 consists of a rod 39 (see Fig. 9) installed in the cylinder 41 of the shock absorber-lift using a movable axle box 7 and an axle box 8 located on the rod 39. The cylinder 41 of the shock absorber-lift 38 is supported by the axle box 9, rigidly with connected to the inner surface of the housing 10 of the hydraulic lift cylinder, and the rod 39 to a fixed axle box 11 installed in the housing 10 of the hydraulic lift cylinder. In this case, the cylinder 41 of the shock absorber-lift 38 together with the rod 39 has the ability to move inside the housing 10 of the hydraulic cylinder-lift on the indicated supports when cleaning and releasing the landing gear, and the axle box 9 is the piston of the hydraulic cylinder-lift. The exhaust cavity 12 and the cleaning cavity 13 of the hydraulic lift cylinder are connected to the aircraft hydraulic system (not shown) by means of fittings 14 and 15, respectively. Inside the rod 39 there is a movable separation piston 42 and a diaphragm with a calibrated hole 43. The separation piston 42 separates the low-pressure nitrogen chamber 44 from the liquid chamber 45 located in the rod 39. The diaphragm with a calibrated hole 43 separates the liquid chamber 45 from the cavity 46 connected by a needle 47 with a charging nipple 24. The charging nipple 48 is used to charge the low-pressure nitrogen chamber 44, and the charging nipple 25 is connected to the high-pressure nitrogen chamber 26 (discharge chamber). The piston of the unloading chamber 27 is moved in the housing 49 of the unloading chamber by means of a movable axle box 7 and has an emphasis on the rod 4. At the ends of the housing 10 of the hydraulic lift cylinder, collet locks of the released and retracted positions are located. The lock of the released position consists of a collet 28, an abutment 29, rigidly connected to the cylinder 38 of the shock absorber-lift, a retainer 30, a spring 31 and a pusher 32. The lock of the retracted position consists of a collet 33, a stop 34, rigidly connected to the cylinder 38 of the shock absorber-lift, a clamp 35, springs 36 and pusher 37.

Retractable landing gear aircraft operates as follows.

The filling of the shock absorber-lift, depicted in figure 2, the hydraulic fluid is as follows. Through the hole for the charging nipple 24, liquid is poured into the cavity 18. Since the calibrated holes 17 in the glass 16 are quite small, and the pressure of the liquid column in the chamber 18 is relatively small, the filling of the cavity 19 through them practically does not occur. The fluid enters the cavity 19 through the holes 20 in the stem 4, the holes in the spacer sleeve 21 and the valve 22, which is open under the action of the spring, and the holes 23 in the glass 16.

The shock absorber-lift 3 according to option 1 (see Fig. 1), as well as the shock absorber-lift 38 according to option 2 (see Fig. 8), is a combined unit and can operate in two modes. In the shock absorber mode, work is absorbed during landing, mileage and takeoff, and in the lift mode, the support is cleaned and released and held in the released and retracted positions using the appropriate locks.

The shock absorber-lift 3 (see figure 1) works as follows.

In the shock absorber mode, the cylinder 6 of the shock absorber-lift (see FIG. 2) is stationary relative to the housing 10 of the hydraulic lift cylinder, and the lock of the released position keeps it from moving. When the shock absorber is perceived, it is compressed, that is, the rod 4 moves relative to the cylinder 6 of the shock absorber-lift. In this case, the volume of the cavity 19 decreases, which leads to the flow of fluid with braking from the cavity 19 into the cavity above the axle box 8 through the holes in the latter, as well as into the cavity 18 through calibrated holes 17, and gas compression in the cavity 18. Through holes 20 in the rod 4 the fluid does not flow into the cavity 18, since the spring-loaded valve 22 blocks them. The impact energy is then accumulated in the compressed gas and partially dissipated when flowing through the holes. When compressing the shock absorber-lift to a stroke not exceeding the stroke of the piston of the unloading chamber 27 (see Fig. 3), the specified piston abuts through the movable axle box 7 into the rod 4 through the movable axle box 7, moving with it. 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 medium of the liquid cavity 19 and the cavity 18, but is smaller in magnitude, that is, it reduces the axial force on the rod 4 of the shock absorber-lift. Thus, the presence of a high-pressure nitrogen chamber 26 (unloading chamber) with a piston 27 of the unloading chamber can significantly reduce the pulling force of the rod 4 of the shock absorber-lift. When compressing the shock absorber-lift to a stroke exceeding the stroke of the piston 27 of the discharge chamber (see FIG. 4), only the rod 4 moves inside the cylinder 6 of the shock absorber-lift 4. The stroke of the axle box 7 and the piston 27 of the discharge chamber is limited by the stop in the cylinder 6 of the shock absorber, i.e. a decrease in force on the rod 4 from the nitrogen high-pressure chamber 26 does not occur. When working in the lift mode, the stem 4 (see Fig. 5) is stationary relative to the cylinder 6 of the shock absorber-lift and is in the released position on the stop. From moving inside the cylinder 6 of the shock absorber-lift it holds pressure in the cavities 18 and 19 of the shock absorber-lift. When cleaning or releasing the support, the cylinder 6 of the shock absorber-lift moves in the housing 10 of the hydraulic cylinder-lift to lock the retracted or released position.

The process of cleaning the support can be divided into three stages: removing the released position from the lock, moving the shock absorber-lift in the housing 10 of the hydraulic lift cylinder and locking the retracted position. It occurs as follows.

The fluid from the hydraulic system of the aircraft is fed into the cleaning cavity 13, and the exhaust cavity 12 communicates with a drain. In this case, the pusher 32 moves together with the latch 30, compressing the spring 31 and releasing the collet 28. The pressure of the hydraulic system in the cleaning cavity 13 also acts on the axle box 9 connected to the cylinder 6 of the shock absorber-lift, and at the same time moves it. When moving the cylinder 6 of the shock absorber-lift, the stop 29 unclenches the released collet 28, being released from the lock of the released position (see Fig. 6). Also, at the beginning of the cleaning stroke, a shock from the piston 27 of the unloading chamber acts on the shock absorber. The shock absorber is moved before locking the stowed position. At the end of the cleaning stroke, the emphasis 34 (see Fig. 7) of the shock absorber-cylinder 6 unclenches the petals of the collet 33 of the retracted position and engages with them, after which the lock is closed due to the force of the spring 36, pressing the latch 35, which holds the petals collets 33 from opening.

The release of the support occurs similarly to cleaning in three stages: removing the stowed position from the lock, moving the shock absorber-lift in the housing 10 of the hydraulic lift cylinder and locking the released position. In this case, the liquid is respectively supplied to the exhaust cavity 12, and the cleaning cavity 13 communicates with the drain. At the end of the course of the release on the shock absorber-lift acts on the side of the piston 27 of the discharge chamber (see Fig.6). In this case, the unloading chamber 26 acts as a braking chamber of the hydraulic cylinder.

The shock absorber-lift according to the second embodiment is as follows.

In the shock absorber-lift mode, the cylinder 41 (see Fig. 9) is stationary relative to the housing 10 of the hydraulic lift cylinder, and the lock of the released position keeps it from moving. With the perception of shock by the shock absorber-lift, it is compressed, that is, the rod 39 moves relative to the 41 cylinder of the shock absorber-lift. The volume of the cavity 46 is reduced, which leads to the flow of fluid with braking from the cavity 46 into the cavity under the axle box 8 through the holes in the latter, as well as through the calibrated opening of the diaphragm 43 into the liquid chamber 45. This in turn leads to the displacement of the separation piston 42 and gas compression in the cavity of the low-pressure nitrogen chamber 44. The impact energy is then accumulated in the compressed gas and partially dissipated when flowing through the holes.

When compressing the shock absorber-lift to a stroke not exceeding the stroke of the piston 27 of the unloading chamber 26, the specified piston abuts through the movable axle box 7 in the rod 39 under the action of compressed gas in the high pressure nitrogen chamber (unloading chamber 26), moving with it. The force on the rod 39 from the piston 27 of the unloading chamber 26 is opposite in direction to the force acting on the rod 39 from the medium of the cavities of the shock absorber-lift, but is smaller in magnitude, that is, it reduces the axial force on the rod 39 of the shock-absorber. Thus, the presence of a high-pressure nitrogen chamber (unloading chamber 26) with a piston 27 can significantly reduce the pulling force of the rod 39 of the shock absorber-lift.

When compressing the shock absorber-lift to a stroke exceeding the stroke of the piston 27 of the discharge chamber 26, only the rod 39 moves inside the cylinder 41 of the shock absorber-lift. The stroke of the axle box 7 and the piston 27 of the discharge chamber 26 is limited by the stop in the cylinder 41 of the shock absorber-lift, i.e. rod 39 does not occur from the high pressure nitrogen chamber 26.

When working in the lift mode, the rod 39 is stationary relative to the cylinder 41 of the shock absorber-lift and is in the released position on the stop. From moving inside the cylinder 41 of the shock absorber-lift it holds pressure in the cavities of the shock absorber. When cleaning or releasing the support, the cylinder 41 of the shock absorber-lift moves in the housing 10 of the hydraulic cylinder-lift to lock the retracted or released position.

The process of cleaning the support can be divided into three stages: removing the released position from the lock, moving the shock absorber-lift in the housing 10 of the hydraulic lift cylinder and locking the retracted position. It occurs as follows.

The fluid from the hydraulic system of the aircraft is fed into the cleaning cavity 13, and the exhaust cavity 12 communicates with a drain. In this case, the pusher 32 moves together with the latch 30, compressing the spring 31 and releasing the collet 28. The pressure of the hydraulic system in the cleaning cavity 13 also acts on the axle box 9 connected to the cylinder 41 of the shock absorber-lift, and at the same time moves it. When moving the cylinder 41, the stop 29 unclenches the released collet 28, being released from the lock of the released position. Also, at the beginning of the cleaning stroke, the shock absorber-lift acts on the side of the piston 27 of the unloading chamber 26. The shock absorber-lift moves before the locked position is locked. At the end of the cleaning stroke, the emphasis 34 of the shock absorber cylinder 6 unclenches the petals of the collet 33 of the retracted position and engages with them, after which the lock is closed due to the force of the spring 36, pressing the latch 35, which holds the petals of the collet 33 from opening.

The release of the support occurs similarly to cleaning in three stages: removing the stowed position from the lock, moving the shock absorber-lift in the housing 10 of the hydraulic lift cylinder and locking the released position. In this case, the liquid is respectively supplied to the exhaust cavity 12, and the cleaning cavity 13 communicates with the drain. At the end of the exhaust stroke, the shock absorber-lift acts on the side of the piston 27 of the discharge chamber 26. In this case, the discharge chamber 26 acts as a braking chamber for the hydraulic cylinder.

The main distinguishing feature of the invention is the layout of the combined unit, shock absorber-lift. In the prototype, this unit is arranged sequentially, and in both versions of the invention, the shock absorber is located inside the hydraulic cylinder, moves inside it during cleaning and release, and, it can be said, is the rod of the hydraulic cylinder.

If we consider schematically from what the longitudinal dimensions of both units mainly form (see Fig. 10), then we can see that:

Lprot = Sub + b1 + Sub + b2 + S

L image = Sub + b2 + Sam + Sub

Where

Lprot is the longitudinal dimension of the prototype;

Sub - the course of cleaning the hydraulic lift cylinder;

b1 is the distance between the axle boxes of the hydraulic lift cylinder;

b2 is the distance between the axle boxes of the shock absorber-lift;

Lizob - longitudinal dimension of the proposed design.

That is, the reduction of the longitudinal dimension occurs due to the parallel inclusion in the dimensional chain of the distance between the axle boxes of the hydraulic lift cylinder.

A sample of the proposed retractable landing gear of the aircraft was developed on the basis of detailed experimental studies of the design parameters and the process of its operation.

The manufacture of the proposed retractable landing gear for the aircraft does not require the development of new equipment and the re-equipment of existing facilities, and the tools used are widely used in the aviation industry, which confirms the possibility of practical implementation and achievement of the technical result.

Claims (6)

1. A retractable landing gear support of the aircraft, comprising a lever with a wheel pivotally mounted on the fuselage, coaxially arranged cleaning-release cylinder with locks of the released and retracted positions, the cavities of which are connected to the aircraft hydraulic system, and a gas-hydraulic shock absorber, characterized in that the latter is made with the ability to fill the cavity with working media through a common charging connector without separating them and placed in the cavity of the hydraulic cylinder with the formation of a pair of "pipe in pipe" and the possibility is made I functions cylinder rod, wherein the cylinder is provided with a high pressure gas chamber, wherein the cavity formed by suspension rod piston mounted in said cavity communicating with the suspension rod, and an additional stationary axle box. 2. The support according to claim 1, characterized in that the shock absorber rod is movable relative to the shock absorber body during compression of the latter, while it has a cavity filled with gas and liquid and communicating with throttling holes with a liquid cavity inside the shock absorber body, and an opening for a charging nipple for pouring fluid into the cavity of the shock absorber rod, and holes are provided in the shock absorber rod for fluid to flow into the shock absorber fluid cavity when filling it, bypassing the throttling holes A hole, and a spring-loaded valve is installed on the stem. 3. The support according to claim 1, characterized in that the cylinder body is pivotally connected to the lever, and the shock absorber rod is connected to the fuselage. 4. A retractable landing gear support of the aircraft, comprising a lever with a wheel pivotally mounted on the fuselage, coaxially arranged cleaning-exhaust cylinder with locks of the released and retracted position, the cavities of which are connected with the hydraulic system of the aircraft, and a gas-hydraulic shock absorber, characterized in that the latter is located in the cavity of the hydraulic cylinder with the formation of a pair of "pipe in pipe" and the ability to perform the functions of the rod of the hydraulic cylinder, while the hydraulic cylinder is equipped with a high-pressure gas chamber, the cavity of the cat swarm is formed suspension rod, a piston mounted in the cavity, and an additional stationary axle box. 5. Support according to claim 4, characterized in that the shock absorber rod is movable relative to the shock absorber body during compression of the latter, while a cavity filled with gas and liquid is made in it, with a separation piston and a diaphragm with a calibrated hole that separates the liquid cavity shock absorber. 6. Support according to claim 4, characterized in that the shock absorber rod is pivotally connected to the lever and the hydraulic cylinder body is connected to the fuselage.

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