CN213443138U

CN213443138U - Buffer device for airplane traction rod

Info

Publication number: CN213443138U
Application number: CN202022265984.XU
Authority: CN
Inventors: 孙方杰
Original assignee: Zhejiang Lijia Aviation Equipment Manufacturing Co ltd
Current assignee: Zhejiang Lijia Aviation Equipment Manufacturing Co ltd
Priority date: 2020-10-13
Filing date: 2020-10-13
Publication date: 2021-06-15
Anticipated expiration: 2030-10-13

Abstract

The utility model relates to an aircraft traction lever technical field, the utility model discloses a technical scheme does: a buffering device for a traction rod of an airplane comprises a rod body and a buffering structure, wherein a first flange is arranged outside the rod body, a sleeve is welded inside the rod body, and a blocking sleeve is movably arranged in the sleeve; the buffer structure comprises a double-flange pipe, a first buffer washer and a second buffer washer are arranged on the left side and the right side of the inside of the double-flange pipe respectively, a plurality of buffer rubber rings are further arranged inside the double-flange pipe and are located between the first buffer washer and the second buffer washer, the left end of the double-flange pipe is connected with the first flange plate in a fastening mode, and the right end of the double-flange pipe is connected with the second flange plate in a fastening mode. Through setting up a plurality of cushion rubber circles in the inside of two flange pipes for no matter really pulling the tail ring or brake during operation, can both provide a buffer power through cushion rubber circle and replace current rigid connection mode, can play fine buffering effect.

Description

Buffer device for airplane traction rod

Technical Field

The utility model relates to an aircraft traction lever technical field especially involves a buffer for aircraft traction lever.

Background

The tail ring and the rod body flange of the original airplane traction rod are in electric welding connection, the impact load generated when the tractor is started and braked is easily and directly transmitted to the nose landing gear of the airplane in a hard connection mode, the service life of the overload device can be greatly shortened by the frequently generated impact load, and therefore a brand new buffer device needs to be designed to realize flexible connection between the tractor and the landing gear of the airplane.

SUMMERY OF THE UTILITY MODEL

The utility model aims at providing a buffer for aircraft traction lever.

The above technical purpose of the utility model is realized with following technical scheme:

a buffering device for a traction rod of an airplane comprises a rod body and a buffering structure, wherein a first flange is arranged outside the rod body, a sleeve is welded inside the rod body, and a blocking sleeve is movably arranged in the sleeve;

the buffer structure comprises a double-flange pipe, a first buffer washer and a second buffer washer are respectively arranged on the left side and the right side of the interior of the double-flange pipe, a plurality of buffer rubber rings are further arranged in the double-flange pipe and are positioned between the first buffer washer and the second buffer washer, the left end of the double-flange pipe is tightly connected with the first flange, and the right end of the double-flange pipe is tightly connected with the second flange;

the tail ring includes the traction ring, set up in the left first body of rod of traction ring and set up in the left second body of rod of first body of rod, the tail ring is the integrated into one piece structure, the first body of rod pass ring flange two and with cushion ring two contacts, the left side end of the second body of rod is equipped with the screw thread end, the second body of rod passes cushion ring two, cushion rubber circle, cushion ring one in proper order and extends to inside the sleeve pipe, shelves cover screw thread connect soon to the screw thread end.

The utility model discloses a further set up to: the first buffer washer and the second buffer washer are both annular steel check rings.

The utility model discloses a further set up to: the middle part of the gear sleeve is provided with a first round hole in a penetrating mode, the threaded end is provided with a second round hole in a penetrating mode in a position corresponding to the round hole, and the gear sleeve is connected to the threaded end in a screwing mode through threads and is fixedly connected through a fixing pin.

The utility model discloses a further set up to: the aperture of the two through holes of the flange plate is the same as the diameter of the first rod body, the diameter of the first rod body is larger than that of the second rod body, the inner diameters of the first buffer washer, the second buffer washer and the buffer rubber ring are the same, and the diameter of the second rod body is the same as that of the first buffer washer.

To sum up, the utility model discloses following beneficial effect has:

1) the buffer rubber rings are arranged in the double-flange pipe, so that no matter the tail ring is pulled or the brake works, a buffer force can be provided by the buffer rubber rings to replace the existing rigid connection mode, a good buffer effect can be achieved, and the service life of the device is prolonged;

2) when the tail ring is pulled rightwards by the trailer, the baffle sleeve is pulled rightwards by the second rod body of the tail ring to generate a rightward trend, so that the first buffer gasket is pushed rightwards, and the second buffer gasket cannot move rightwards due to the fact that the second buffer gasket is in contact with the flange plate, so that the buffer rubber ring in the middle is compressed after the first buffer gasket moves rightwards, and a buffer effect is achieved; when the tail ring is pulled leftwards by the trailer, the diameter of the first rod body of the tail ring is larger than that of the inner ring of the second buffer washer, the first rod body pushes the second buffer washer to move leftwards, and at the moment, the first buffer washer is blocked by the sleeve pipe, the first buffer washer cannot move leftwards, so that the second buffer washer moves leftwards to compress the middle buffer rubber ring, and the buffer effect is achieved; the two extrusion buffering modes can effectively prevent the service life of the device from being prolonged.

Drawings

Fig. 1 is a schematic structural diagram of the present invention.

Fig. 2 is a cross-sectional view of the present invention.

Fig. 3 is a schematic structural view of the tail ring of the present invention receiving a right pulling force.

Fig. 4 is a schematic structural diagram of the left pulling force applied to the tail ring of the present invention.

The corresponding part names indicated by the numbers and letters in the drawings:

wherein: 10. a shaft body; 20. a buffer structure; 30. a second flange plate; 40. a tail ring; 101. a first flange plate; 102. a sleeve; 103. a gear sleeve; 201. a double-flange pipe; 202. a first buffer washer; 203. a second buffer washer; 204. a buffer rubber ring; 401. a traction ring; 402. a first rod body; 403. a second rod body; 404. a threaded end.

Detailed Description

In order to make the technical means, creation features, achievement purposes and functions of the present invention easy to understand, the present invention will be further described with reference to the drawings and the specific embodiments.

In the description of the present invention, it should be noted that the terms "upper", "lower", "inner", "outer", "front end", "rear end", "both ends", "one end", "the other end" and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are only for convenience of description and simplification of description, but do not indicate or imply that the device or element to which the reference is made must have a specific orientation, be constructed in a specific orientation, and be operated, and thus, should not be construed as limiting the present invention. Furthermore, the terms "first" and "second" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.

In the description of the present invention, it is to be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "disposed," "connected," and the like are to be construed broadly, and for example, "connected" may be either fixedly connected or 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 meaning of the above terms in the present invention can be understood in specific cases to those skilled in the art.

As shown in fig. 1 and 2, the buffering device for the airplane drawbar provided by the present invention comprises a bar body 10 and a buffering structure 20, wherein a first flange 101 is arranged outside the bar body 10, a sleeve 102 is welded inside the bar body 10, and a stop sleeve 103 is movably arranged inside the sleeve 102; the buffer structure 20 comprises a double-flange pipe 201, a first buffer gasket 202 and a second buffer gasket 203 are respectively arranged on the left side and the right side of the inside of the double-flange pipe 201, a plurality of buffer rubber rings 204 are further arranged inside the double-flange pipe 201, the plurality of buffer rubber rings 204 are located between the first buffer gasket 202 and the second buffer gasket 203, the left end of the double-flange pipe 201 is fixedly connected with the first flange plate 101, and the right end of the double-flange pipe 201 is fixedly connected with the second flange plate 30; the tail ring 40 includes the drag ring 401, set up in the left first body of rod 402 of drag ring 401 and set up in the left second body of rod 403 of first body of rod 402, the tail ring 40 is the integrated into one piece structure, first body of rod 402 pass flange two 30 and with cushion ring two 203 contacts, the left side end of the second body of rod 403 is equipped with threaded end 404, second body of rod 403 passes cushion ring two 203, cushion rubber circle 204, cushion ring one 202 in proper order and extends to inside the sleeve pipe 102, shelves cover 103 screw thread connects to threaded end 404 soon. Further, the first cushion washer 202 and the second cushion washer 203 are both annular steel check rings. Further, a first round hole is formed in the middle of the gear sleeve 103 in a penetrating mode, a second round hole is formed in the threaded end 404 in a penetrating mode in a position corresponding to the round hole, and the gear sleeve 103 is connected to the threaded end 404 in a screwing mode through threads and is fixedly connected through a fixing pin. Further, the aperture of the through hole of the second flange 30 is the same as the diameter of the first rod 402, the diameter of the first rod 402 is larger than the diameter of the second rod 403, the inner diameters of the first buffer washer 202, the second buffer washer 203 and the buffer rubber ring 204 are the same, and the diameter of the second rod 403 is the same as the inner diameter of the first buffer washer 202.

In the above technical solution, the tail ring 40 is an integrally formed structure, the towing ring 401 is used for connecting with an aircraft trailer, and the first rod body 402 and the second rod body 403 are both in the shape of a round rod; the baffle sleeve 103 is screwed to the outside of the threaded end 404 and is fixedly connected with the threaded end 404 of the second rod body 403 through a fixing pin, the baffle sleeve 103 can move left and right in the sleeve 102, and the diameter of the outer ring of the baffle sleeve 103 is larger than that of the inner ring of the first buffer washer 202; the double-flange pipe 201 is a flange pipe with flanges at two ends, and the flange plate I101 and the double-flange pipe 201, the flange plate II 30 and the double-flange pipe 201 are all fastened and connected through bolts, nuts, spring washers and metal washers; the sleeve 102 located inside the rod body 10 is mainly used for limiting the first buffer washer 202, the diameter of the outer ring of the sleeve 102 is the same as that of the inner ring of the rod body 10, the diameter of the outer ring of the first buffer washer 202 is the same as that of the outer ring of the sleeve 102, the diameter of the inner ring of the sleeve 102 is larger than that of the inner ring of the first buffer washer 202, and the diameter of the inner ring of the sleeve 102 is the same as that of the outer ring of the baffle sleeve 103.

In the technical solution, as shown in fig. 3, when the tail ring 40 is pulled by the trailer to the right by a pull force F1, the stopper sleeve 103 is pulled by the second rod 403 of the tail ring 40 to the right, and a rightward trend F2 is generated, so as to push the first cushion ring 202 to the right, and since the second cushion ring 203 is in contact with the second flange 30, the second cushion ring 203 cannot move to the right, so that the first cushion ring 202 moves to the right and then compresses the middle cushion rubber ring 204, thereby playing a role in buffering; referring to fig. 4, when the tail ring 40 is pulled leftwards by the trailer, F3, since the diameter of the first rod 402 of the tail ring 40 is larger than the diameter of the inner ring of the second cushion ring 203, the first rod 402 pushes the second cushion ring 203 to move leftwards, and at this time, since the first cushion ring 202 is blocked by the sleeve 102, the first cushion ring 202 cannot move leftwards, and the second cushion ring 203 moves leftwards to compress the middle cushion rubber ring 204, thereby playing a role in cushioning.

The utility model discloses an installation principle: firstly, a first buffer gasket 202 is placed on the left side of the interior of the double-flange pipe 201, then a plurality of buffer rubber rings 204 are placed in the interior of the double-flange pipe 201, then a second buffer gasket 203 is placed on the right side of the interior of the double-flange pipe 201, a second rod body 403 of the tail ring 40 penetrates through the second flange plate 30, the second buffer gasket 203, the buffer rubber rings 204 and the first buffer gasket 202 and extends to the exterior of the double-flange pipe 201, then the second flange plate 30 is tightly connected with the double-flange pipe 201 (while a first rod body 402 of the tail ring 40 is in contact with the second buffer gasket 203), a threaded end 404 of the left end of the second rod body 403 is externally screwed with a stop sleeve 103 and fixed by a fixing pin, then the stop sleeve 103 extends into the sleeve 101 of the rod body 10, and then the double-flange pipe 201 is tightly connected with the first flange plate 101, and therefore.

The foregoing shows and describes the general principles, essential features, and advantages of the invention. It will be understood by those skilled in the art that the present invention is not limited to the above embodiments, and that the foregoing embodiments and descriptions are provided only to illustrate the principles of the present invention without departing from the spirit and scope of the present invention. The scope of the invention is defined by the appended claims and equivalents thereof.

Claims

1. A buffer device for a traction rod of an airplane comprises a rod body (10) and a buffer structure (20), wherein a first flange (101) is arranged outside the rod body (10), and the buffer device is characterized in that: a sleeve (102) is welded inside the rod body (10), and a blocking sleeve (103) is movably arranged in the sleeve (102);

the buffer structure (20) comprises a double-flange pipe (201), a first buffer gasket (202) and a second buffer gasket (203) are respectively arranged on the left side and the right side of the interior of the double-flange pipe (201), a plurality of buffer rubber rings (204) are further arranged in the double-flange pipe (201), the buffer rubber rings (204) are located between the first buffer gasket (202) and the second buffer gasket (203), the left end of the double-flange pipe (201) is fixedly connected with the first flange plate (101), and the right end of the double-flange pipe (201) is fixedly connected with the second flange plate (30);

tail ring (40) include towing ring (401), set up in towing ring (401) left first body of rod (402) and set up in first body of rod (402) left second body of rod (403), tail ring (40) are the integrated into one piece structure, first body of rod (402) pass ring flange two (30) and with cushion washer two (203) contact, the left side end of second body of rod (403) is equipped with threaded end (404), second body of rod (403) pass cushion washer two (203), cushion rubber circle (204), cushion washer one (202) in proper order and extend to inside sleeve pipe (102), shelves cover (103) screw thread connect soon to threaded end (404).

2. A damping device for an aircraft tow bar according to claim 1, characterised in that: the first buffer washer (202) and the second buffer washer (203) are both annular steel check rings.

3. A damping device for an aircraft tow bar according to claim 1, characterised in that: a first round hole penetrates through the middle of the gear sleeve (103), a second round hole penetrates through the threaded end (404) at the position corresponding to the round hole, and the gear sleeve (103) is screwed to the threaded end (404) through threads and is fixedly connected through a fixing pin.

4. A damping device for an aircraft tow bar according to claim 1, characterised in that: the aperture of the through hole of the second flange plate (30) is the same as the diameter of the first rod body (402), the diameter of the first rod body (402) is larger than the diameter of the second rod body (403), the inner diameters of the first buffer washer (202), the second buffer washer (203) and the buffer rubber ring (204) are the same, and the diameter of the second rod body (403) is the same as the inner diameter of the first buffer washer (202).