CN216709623U - Buffer mechanism for aviation undercarriage - Google Patents

Abstract

The utility model discloses a buffer mechanism for an aviation undercarriage, which relates to the technical field of aviation, and particularly relates to a buffer mechanism for an aviation undercarriage. This a buffer gear for aviation undercarriage, the outside movable sleeve that makes damping cover top down is equipped with the damping cover, the top surface that makes the bottom block is provided with reset spring with the left side of bottom block, in the twinkling of an eye that the aircraft falls to the ground, ascending impact force can be through the last damping cover of bottom block top, lower damping cover, reset spring cushions, backward power can cushion with reset spring through the left last damping cover of bottom block and lower damping cover, can effectively increase buffer gear's life, the buffering effect has effectively been improved simultaneously.

Description

Buffer mechanism for aviation undercarriage

Technical Field

The utility model relates to the technical field of aviation, in particular to a buffer mechanism for an aviation undercarriage.

Background

The landing gear is an accessory device which is used for supporting the airplane and moving on the ground (water surface) when the lower part of the airplane is used for taking off and landing or sliding on the ground (water surface), and the landing gear is the only part for supporting the whole airplane, so that the landing gear is an inseparable part of the airplane; without the landing gear, the aircraft can not move on the ground, after the aircraft takes off, the landing gear can be retracted according to flight performance, the landing gear device is an important part of the aircraft with force bearing and maneuverability, the landing gear device plays an extremely important role in the safe taking off and landing process of the aircraft, the landing gear is a necessary support system for taking off, landing, running, ground moving and parking of the aircraft, the landing gear is one of main parts of the aircraft, and the quality of the performance of the landing gear device is directly related to the use of the aircraft in safety.

In the landing process of an airplane, an undercarriage is required to be used, the landing of an auxiliary airplane is usually performed, a buffer device is arranged in the undercarriage, the auxiliary airplane stably lands on the ground, the auxiliary airplane can be subjected to force resisting the movement direction of the airplane in the moment of landing of the airplane, the upward force is combined with most of buffer mechanisms, only upward impulsive force is processed by the buffer mechanisms, hormones are decreased in service life of the buffer mechanisms after the buffer mechanisms are used for a period of time, and the stability of buffering is affected.

SUMMERY OF THE UTILITY MODEL

In view of the deficiencies of the prior art, the present invention provides a cushioning mechanism for an aircraft landing gear that solves the problems set forth above in the background.

In order to achieve the purpose, the utility model is realized by the following technical scheme: the utility model provides a buffer gear for aviation undercarriage, includes the roof, the bottom fixed mounting of roof has the connecting plate, the damping cover is gone up to the bottom fixedly connected with of connecting plate, the bottom swing joint who goes up the damping cover inner chamber has lower damping cover, the bottom fixedly connected with reset spring of connecting plate, reset spring's bottom surface fixed mounting has the bottom block, friction line has been seted up to the outside of lower damping cover and the inboard of last damping cover.

Optionally, the left end fixedly connected with drive flexible post of roof bottom, the right-hand member fixedly connected with backup pad of the flexible post output shaft of drive, the right side of backup pad and the left side fixedly connected with in-connection piece of bottom block, the inner chamber movable sleeve of in-connection piece is equipped with the pivot, the outside of pivot is fixed, is connected with the outer connecting block.

Optionally, a pulley is connected to the upper portion of the supporting plate through a supporting column and a bearing, a chute with a T-shaped cross section is formed in the inner cavity of the top plate, and the pulley is located in the chute.

Optionally, the bottom end of the friction line is fixedly connected with the top surface of the bottom block, the return spring is located in the inner cavities of the upper damping sleeve and the lower damping sleeve, and the outer side of the lower damping sleeve is attached to the inner side of the upper damping sleeve.

Optionally, the inner sides of the two outer connecting blocks are provided with an upper damping sleeve, a lower damping sleeve and a return spring through connecting plates, and the return spring is perpendicular to the two connecting plates on the left side.

Optionally, the right surface of the bottom block and the right surface of the top plate are located on the same vertical surface, and the left surface of the driving telescopic column and the left surface of the top plate are located on the same vertical surface.

The utility model provides a buffer mechanism for an aviation undercarriage, which has the following beneficial effects:

1. this a buffer gear for aviation undercarriage, be connected with down the damping cover through top and the left side at the bottom block, the outside movable sleeve that makes damping cover top down is equipped with the damping cover, the top surface that makes the bottom block and the left side of bottom block are provided with reset spring, in the twinkling of an eye that the aircraft lands, ascending impact force can be through the last damping cover of bottom block top, lower damping cover, reset spring cushions, backward power, can cushion with reset spring through the left last damping cover of bottom block and lower damping cover, can effectively increase buffer gear's life, the buffering effect has effectively been improved simultaneously.

2. This a buffer gear for aviation undercarriage, install the flexible post of drive through the left end in the roof bottom, the right-hand member fixedly connected with backup pad that makes the flexible post output shaft of drive, pass through the internal connection piece on the right side of backup pad, the apparatus further comprises a rotating shaft, damping sleeve is connected to external connection piece and connecting plate connection, make the top surface of backup pad pass through the bearing and connect the pulley, conveniently pass through the position of the flexible post control backup pad of drive when using, and then the flight speed according to the aircraft is convenient, make the adjustment of going up damping sleeve and lower damping sleeve to suitable angle, carry out the shock attenuation, the angle of damping sleeve is gone up in the convenient real-time adjustment according to flight speed.

Drawings

FIG. 1 is a schematic structural view of the present invention;

FIG. 2 is a schematic view of the present invention in a disassembled state;

FIG. 3 is a schematic structural view of an upper damping sleeve of the present invention;

fig. 4 is a schematic structural view of the driving telescopic column of the present invention.

In the figure: 1. a top plate; 2. a connecting plate; 3. an upper damping sleeve; 4. a lower damping sleeve; 5. a bottom block; 6. a return spring; 7. rubbing the lines; 8. driving the telescopic column; 9. a support plate; 10. a pulley; 11. an outer connecting block; 12. a rotating shaft; 13. the inner connecting block.

Detailed Description

The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments.

Referring to fig. 1 to 3, the present invention provides a technical solution: a buffer mechanism for an aviation undercarriage comprises a top plate 1, a connecting plate 2 is fixedly arranged at the bottom of the top plate 1, an upper damping sleeve 3 is fixedly connected at the bottom of the connecting plate 2, a lower damping sleeve 4 is movably connected at the bottom end of an inner cavity of the upper damping sleeve 3, a reset spring 6 is fixedly connected at the bottom of the connecting plate 2 and the upper damping sleeve 3 through the arrangement of the connecting plate 2 and the lower damping sleeve 4, the impact force of the airplane falling to the ground is buffered conveniently during use, the impact force of the airplane falling to the ground can be effectively increased, the upper damping sleeve 3 and the lower damping sleeve 4 are conveniently buffered when being impacted, the buffering of a device is facilitated, a bottom block 5 is fixedly arranged at the bottom surface of the reset spring 6, friction grains 7 are arranged on the outer side of the lower damping sleeve 4 and the inner side of the upper damping sleeve 3, the friction grains 7 are arranged, and the friction between the upper damping sleeve 3 and the lower damping sleeve 4 is conveniently increased during use, make and go up damping sleeve 3 and damping sleeve 4 can fully slow down the impact force down, the aircraft can receive ascending impact force, the impact force can promote the upward motion of bottom piece 5, make bottom piece 5 promote damping sleeve 4 upward motion down, make damping sleeve 4 move the inner chamber to the supreme damping sleeve 3 down, make reset spring 6 be in compression state simultaneously, cushion the impact force through last damping sleeve 3 and lower damping sleeve 4, can stably descend, the bottom of friction line 7 and the top surface fixed connection of bottom piece 5, reset spring 6 is located the inner chamber of last damping sleeve 3 and lower damping sleeve 4, the outside of lower damping sleeve 4 is laminated with the inboard of last damping sleeve 3, conveniently increase the frictional force between damping sleeve 3 and the lower damping sleeve 4, make last damping sleeve 3 and lower damping sleeve 4 accomplish the buffering to the impact force, the use of convenient device, the stability of aircraft has been improved.

Referring to fig. 4, a driving telescopic column 8 is fixedly connected to the left end of the bottom end of a top plate 1, the right side of a bottom block 5 and the right side of the top plate 1 are located on the same vertical plane, the left side of the driving telescopic column 8 and the left side of the top plate 1 are located on the same vertical plane, the driving telescopic column 8 is arranged, and according to the flight speed of the airplane, the output shaft of the driving telescopic column 8 is controlled to extend out or retract to a proper position, so that a support plate 9 moves to a proper position, the left upper damping sleeve 3, the left lower damping sleeve 4 and the left bottom block 5 are conveniently controlled to be located at proper positions, so that the left upper damping sleeve 3, the left lower damping sleeve 4 and the bottom block 5 are fully damped, the practicability of the device is increased, the support plate 9 is fixedly connected to the right end of the output shaft of the driving telescopic column 8, an inner connecting block 13 is fixedly connected to the right side of the support plate 9 and the left side of the bottom block 5, a rotating shaft 12 is movably sleeved in an inner cavity of the inner connecting block 13, the outer side of the rotating shaft 12 is fixed and connected with an outer connecting block 11, the rotating shaft 12 and an inner connecting block 13 are arranged, so that the upper damping sleeve 3 and the lower damping sleeve 4 can be conveniently adjusted to a proper angle, the rotating shaft 12 plays a role in connecting the inner connecting block 13 and the outer connecting block 11, the adjustment of a device is convenient, the connection of the bottom block 5 and the driving telescopic column 8 is convenient, the backward impact force is sufficiently reduced, the upper damping sleeve 3, the lower damping sleeve 4 and the reset spring 6 are arranged on the inner sides of the two outer connecting blocks 11 through the connecting plates 2, the left reset spring 6 is mutually vertical to the two left connecting plates 2, the upper damping sleeve 3, the lower damping sleeve 4 and the bottom block 5 on the left side are arranged, the backward impact force is sufficiently buffered through the upper damping sleeve 3, the lower damping sleeve 4 and the bottom block 5 when the device is used, the upper part of the supporting plate 9 is connected with a pulley 10 through a supporting column and a bearing, the cross-section is seted up for the spout of T shape in the inner chamber of roof 1, and pulley 10 is located the spout, and the setting of spout conveniently makes backup pad 9 control activity about, conveniently controls the angle of damping cover 3, lower damping cover 4, bottom block 5 on the left side, and the usability of device has been increased in the use of making things convenient for the device, and pulley 10 sets up and makes things convenient for backup pad 9 to connect roof 1, and slides.

To sum up, when the buffer mechanism for the aviation landing gear is used, firstly, the top plate 1 is placed outside an airplane, then, according to the flying speed of the airplane, the output shaft of the telescopic column 8 is controlled and driven to extend out or retract to a proper position, the supporting plate 9 is moved to a proper position, then, at the moment that the airplane lands, the airplane can be subjected to an upward impact force, the impact force can push the bottom block 5 to move upwards, the bottom block 5 can push the lower damping sleeve 4 to move upwards, the lower damping sleeve 4 can move to the inner cavity of the upper damping sleeve 3, meanwhile, the return spring 6 is in a compression state, the impact force is buffered through the upper damping sleeve 3 and the lower damping sleeve 4, meanwhile, the bottom block 5 can be pushed by a force in the direction opposite to the moving direction of the airplane, the bottom block 5 has the tendency of moving towards the upper left direction, and the left upper damping sleeve 3 and the left lower damping sleeve 4 can be compressed simultaneously in the upward movement process of the bottom block 5, and buffering the impact force.

In the description of the present invention, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc., indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are only for convenience of description and simplicity of description, but do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus, should not be construed as limiting the present invention; the terms "first," "second," and "third" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance, and furthermore, unless otherwise explicitly stated or limited, the terms "mounted," "connected," and "connected" are to be construed broadly and may be, for example, fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meanings of the above terms in the present invention can be understood in specific cases to those skilled in the art. Also, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus.

Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that changes, modifications, substitutions and alterations can be made in these embodiments without departing from the principles and spirit of the utility model, the scope of which is defined in the appended claims and their equivalents.

Claims (6)

1. A damping mechanism for aircraft landing gears, comprising a top plate (1), characterized in that: the bottom fixed mounting of roof (1) has connecting plate (2), damping cover (3) are gone up to the bottom fixedly connected with of connecting plate (2), the bottom swing joint of going up damping cover (3) inner chamber has lower damping cover (4), the bottom fixedly connected with reset spring (6) of connecting plate (2), the bottom surface fixed mounting of reset spring (6) has bottom (5), friction line (7) have been seted up in the outside of damping cover (4) and the inboard of last damping cover (3) down.

2. A cushioning mechanism for an aircraft landing gear according to claim 1, wherein: the left end fixedly connected with drive flexible post (8) of roof (1) bottom, the right-hand member fixedly connected with backup pad (9) of drive flexible post (8) output shaft, the right side of backup pad (9) and the left side fixedly connected with in-connection piece (13) of bottom block (5), the inner chamber movable sleeve of in-connection piece (13) is equipped with pivot (12), the outside of pivot (12) is fixed, is connected with outer connecting block (11).

3. A cushioning mechanism for an aircraft landing gear according to claim 2, wherein: the top of backup pad (9) is connected with pulley (10) through support column and bearing, the spout that the cross-section is T shape is seted up to the inner chamber of roof (1), pulley (10) are located the spout.

4. A cushioning mechanism for an aircraft landing gear according to claim 1, wherein: the bottom end of the friction grains (7) is fixedly connected with the top surface of the bottom block (5), the reset spring (6) is located in the inner cavities of the upper damping sleeve (3) and the lower damping sleeve (4), and the outer side of the lower damping sleeve (4) is attached to the inner side of the upper damping sleeve (3).

5. A cushioning mechanism for an aircraft landing gear according to claim 2, wherein: two damping cover (3), lower damping cover (4), reset spring (6) are installed through connecting plate (2) to the inboard of outer connecting block (11), and the left side reset spring (6) and two connecting plate (2) mutually perpendicular in the left side.

6. A cushioning mechanism for an aircraft landing gear according to claim 2, wherein: the right side of the bottom block (5) and the right side of the top plate (1) are located on the same vertical surface, and the left side of the driving telescopic column (8) and the left side of the top plate (1) are located on the same vertical surface.

Images