Buffer device for aviation landing gear

Abstract

The utility model discloses a buffer device for an aviation undercarriage, which relates to the technical field of undercarriages and comprises a mounting frame, a piston cylinder is fixedly connected to the bottom of the mounting frame, a mounting shaft is fixedly connected to the inside of the telescopic end of the piston cylinder, and aircraft tires are rotatably connected to the outer sides of the two ends of the mounting shaft. A first connecting block is fixedly connected to the outer side of a piston cylinder body, a second connecting block is fixedly connected to the outer side of the telescopic end of the piston cylinder, a first connecting shaft is fixedly connected to the interior of the first connecting block, a second connecting shaft is fixedly connected to the interior of the second connecting block, and first connecting plates are rotationally connected to the outer sides of the two ends of the first connecting shaft; according to the landing gear, the impact force borne by the landing gear from the front side in the taxiing process of an aircraft is reduced, and the stability and safety of the landing gear in the taxiing process of the aircraft are effectively improved.

Description

Technical Field

[0001] The utility model relates to the technical field of landing gears, in particular to a buffer device for aviation landing gears. Background Art

[0002] The landing gear is an accessory device on the lower part of the aircraft used to support the aircraft during takeoff, landing or ground (water) taxiing and used for ground (water) movement. The landing gear is the only component that supports the entire aircraft, so it is an indispensable part of the aircraft; without it, the aircraft cannot move on the ground. After the aircraft takes off, the landing gear can be retracted depending on the flight performance. The landing gear device is an important load-bearing and maneuverable component of the aircraft. It shoulders an extremely important mission in the safe takeoff and landing of the aircraft. The landing gear is a necessary support system for aircraft takeoff, landing, taxiing, ground movement and parking. It is one of the main components of the aircraft. The quality of its performance is directly related to the use and safety of the aircraft.

[0003] After searching, the patent with authorization announcement number CN220199577U discloses a buffer device for aircraft landing gear, including a landing gear top plate, a plurality of positioning holes are opened at the edge of the landing gear top plate, the bottom of the landing gear top plate is fixedly connected with a main cylinder, and the inside of the main cylinder is movably connected with a secondary cylinder; the top of the inner side of the main cylinder is fixedly connected with a piston rod, and the bottom end of the piston rod is fixedly connected with a working piston, which can effectively buffer the landing of the aircraft landing gear, effectively convert the kinetic energy during landing, effectively protect the aircraft itself, have a better buffering effect, and are more durable and reliable to use.

[0004] Although the above technical solution can reduce the impact force of the landing gear in the vertical direction, it cannot effectively alleviate the front and side impact force received by the aircraft landing gear during landing. Therefore, in order to solve the above problem, we propose a buffer device for aircraft landing gear. Utility Model Content

[0005] The utility model aims to solve the defects in the prior art and proposes a buffer device for aviation landing gear.

[0006] In order to achieve the above purpose, the utility model adopts the following technical solutions:

[0007] A buffer device for an aircraft landing gear comprises a mounting frame, wherein a piston cylinder is fixedly connected to the bottom of the mounting frame, a mounting shaft is fixedly connected to the inside of the telescopic end of the piston cylinder, and aircraft tires are rotatably connected to the outer sides of both ends of the mounting shaft, a first connecting block is fixedly connected to the outer side of the piston cylinder body, a second connecting block is fixedly connected to the outer side of the telescopic end of the piston cylinder, a first connecting shaft is fixedly connected to the inside of the first connecting block, a second connecting shaft is fixedly connected to the inside of the second connecting block, first connecting plates are rotatably connected to the outer sides of both ends of the first connecting shaft, second connecting plates are rotatably connected to the outer sides of both ends of the second connecting shaft, a third connecting shaft is rotatably connected to the inside of one end of the second connecting plate, and one end of the first connecting plate is rotatably connected to the outer side of the middle portion of the third connecting shaft.

[0008] Furthermore, a first connecting frame is fixedly connected to the outer side of the middle part of the piston cylinder, a fourth connecting shaft is fixedly connected to the inside of the first connecting frame, a connecting rod is rotatably connected to the outer side of the fourth connecting shaft, a fifth connecting shaft is arranged inside one end of the connecting rod, a second connecting frame is fixedly connected to the outer side of the fifth connecting shaft, and one end of the connecting rod is rotatably connected to the outer side of the fifth connecting shaft.

[0009] Furthermore, a movable plate is fixedly connected to the top of the second connecting frame, a mounting seat is arranged on the outer side of one end of the movable plate, a limiting cavity is arranged inside the mounting seat, one end of the movable plate is fixedly connected to the limiting plate, and the limiting plate is arranged inside the limiting cavity.

[0010] Furthermore, a guide rod is fixedly connected to the interior of the limiting cavity, and a return spring is sleeved on the outer side of the guide rod.

[0011] Furthermore, a connecting hole is provided inside one end of the movable plate close to the mounting seat, and one end of the guide rod is arranged inside the connecting hole.

[0012] Compared with the prior art, the beneficial effect of the utility model is that the piston cylinder in the present application can reduce the vertical impact force, and through the connecting rod transmission, the movable plate can compress the return spring in the mounting seat, thereby reducing the front and side impact force on the landing gear during the taxiing of the aircraft, and effectively improving the stability and safety of the landing gear during the taxiing of the aircraft. BRIEF DESCRIPTION OF THE DRAWINGS

[0013] The accompanying drawings are used to provide a further understanding of the present invention and constitute a part of the specification. They are used together with the embodiments of the present invention to explain the present invention and do not constitute a limitation to the present invention.

[0014] Figure 1 It is a schematic diagram of the overall structure of the utility model;

[0015] Figure 2It is an enlarged schematic diagram of the structure at A of the utility model;

[0016] Figure 3 It is a structural schematic diagram of the mounting seat of the utility model.

[0017] In the figure: 1. mounting frame; 2. piston cylinder; 3. mounting shaft; 4. aircraft tire; 5. first connecting frame; 6. connecting rod; 7. second connecting frame; 8. movable plate; 9. mounting seat; 10. first connecting block; 11. second connecting block; 12. first connecting shaft; 13. second connecting shaft; 14. first connecting plate; 15. second connecting plate; 16. third connecting shaft; 17. fourth connecting shaft; 18. fifth connecting shaft; 19. limit plate; 20. limit cavity; 21. guide rod; 22. reset spring; 23. connecting hole. DETAILED DESCRIPTION

[0018] The following will clearly and completely describe the technical solutions in the embodiments of the present invention in conjunction with the accompanying drawings in the embodiments of the present invention;

[0019] Reference Figure 1-3 A buffer device for an aviation landing gear comprises a mounting frame 1, a piston cylinder 2 is fixedly connected to the bottom of the mounting frame 1, a mounting shaft 3 is fixedly connected to the inside of the telescopic end of the piston cylinder 2, and aircraft tires 4 are rotatably connected to the outer sides of both ends of the mounting shaft 3, a first connecting block 10 is fixedly connected to the outer side of the cylinder body of the piston cylinder 2, a second connecting block 11 is fixedly connected to the outer side of the telescopic end of the piston cylinder 2, a first connecting shaft 12 is fixedly connected to the inside of the first connecting block 10, a second connecting shaft 13 is fixedly connected to the inside of the second connecting block 11, first connecting plates 14 are rotatably connected to the outer sides of both ends of the first connecting shaft 12, second connecting plates 15 are rotatably connected to the outer sides of both ends of the second connecting shaft 13, a third connecting shaft 16 is rotatably connected to the inside of one end of the second connecting plate 15, and one end of the first connecting plate 14 is rotatably connected to the outer side of the middle part of the third connecting shaft 16.

[0020] When the aircraft falls and the aircraft tire 4 contacts the ground, the telescopic end of the piston cylinder 2 will move into the cylinder body under pressure to reduce the impact force on the landing gear. During the movement, one end of the first connecting plate 14 and the second connecting plate 15 will rotate along the first connecting axis 12 and the second connecting axis 13 respectively, and the adjacent ends of the first connecting plate 14 and the second connecting plate 15 will rotate along the third connecting axis 16 to cooperate with the movement of the telescopic end of the piston cylinder 2 to ensure the stability and reliability of the operation of the piston cylinder 2.

[0021] The outer side of the middle part of the piston cylinder 2 is fixedly connected with the first connecting frame 5, the inner side of the first connecting frame 5 is fixedly connected with the fourth connecting shaft 17, the outer side of the fourth connecting shaft 17 is rotatably connected with the connecting rod 6, a fifth connecting shaft 18 is arranged inside one end of the connecting rod 6, the outer side of the fifth connecting shaft 18 is fixedly connected with the second connecting frame 7, one end of the connecting rod 6 is rotatably connected to the outer side of the fifth connecting shaft 18, and the connecting rod 6 is used to transmit the impact force and mitigate the impact.

[0022] A movable plate 8 is fixedly connected to the top of the second connecting frame 7, a mounting seat 9 is arranged on the outer side of one end of the movable plate 8, a limiting cavity 20 is arranged inside the mounting seat 9, one end of the movable plate 8 is fixedly connected to a limiting plate 19, the limiting plate 19 is arranged inside the limiting cavity 20, and the limiting plate 19 cooperates with the limiting cavity 20 to prevent the movable plate 8 from escaping from the limiting cavity 20.

[0023] A guide rod 21 is fixedly connected to the interior of the limiting cavity 20 , and a return spring 22 is sleeved on the outer side of the guide rod 21 . The guide rod 21 is used to limit the running track of the movable plate 8 .

[0024] A connecting hole 23 is formed inside one end of the movable plate 8 close to the mounting seat 9 , and one end of the guide rod 21 is disposed inside the connecting hole 23 .

[0025] When the aircraft is taxiing, the piston cylinder 2 will be subjected to impact force from the front and side. At this time, the two ends of the connecting rod 6 will rotate along the fourth connecting shaft 17 and the fifth connecting shaft 18 respectively, and push the movable plate 8 to move in the limiting cavity 20. The limiting cavity 20 will move along the guide rod 21 and squeeze the return spring 22 to make the piston cylinder 2 slightly tilted to resist the impact. After the pressure applied to the piston cylinder 2 by the impact force is less than the elastic force of the return spring 22, the return spring 22 pushes the movable plate 8 to return to its original position, so that the piston cylinder 2 is at a normal angle, thereby protecting the piston cylinder 2.

Claims

1. A buffer device for an aircraft landing gear, comprising a mounting frame (1), characterized in that: The bottom of the mounting frame (1) is fixedly connected to a piston cylinder (2); the interior of the telescopic end of the piston cylinder (2) is fixedly connected to a mounting shaft (3); the outer sides of both ends of the mounting shaft (3) are rotatably connected to aircraft tires (4); the outer side of the cylinder body of the piston cylinder (2) is fixedly connected to a first connecting block (10); the outer side of the telescopic end of the piston cylinder (2) is fixedly connected to a second connecting block (11); the interior of the first connecting block (10) is fixedly connected to a first connecting shaft (12); the interior of the second connecting block (11) is fixedly connected to a second connecting shaft (13); the outer sides of both ends of the first connecting shaft (12) are rotatably connected to first connecting plates (14); the outer sides of both ends of the second connecting shaft (13) are rotatably connected to second connecting plates (15); the interior of one end of the second connecting plate (15) is rotatably connected to a third connecting shaft (16); and one end of the first connecting plate (14) is rotatably connected to the outer side of the middle portion of the third connecting shaft (16).

2. The buffer device for an aviation landing gear according to claim 1, characterized in that: The outer side of the middle part of the piston cylinder (2) is fixedly connected to a first connecting frame (5), the interior of the first connecting frame (5) is fixedly connected to a fourth connecting shaft (17), the outer side of the fourth connecting shaft (17) is rotatably connected to a connecting rod (6), one end of the connecting rod (6) is internally provided with a fifth connecting shaft (18), the outer side of the fifth connecting shaft (18) is fixedly connected to a second connecting frame (7), and one end of the connecting rod (6) is rotatably connected to the outer side of the fifth connecting shaft (18).

3. The buffer device for aircraft landing gear according to claim 2, characterized in that: A movable plate (8) is fixedly connected to the top of the second connecting frame (7), a mounting seat (9) is arranged on the outer side of one end of the movable plate (8), a limiting cavity (20) is arranged inside the mounting seat (9), and one end of the movable plate (8) is fixedly connected to a limiting plate (19), and the limiting plate (19) is arranged inside the limiting cavity (20).

4. The buffer device for aircraft landing gear according to claim 3, characterized in that: A guide rod (21) is fixedly connected to the interior of the limiting cavity (20), and a return spring (22) is sleeved on the outer side of the guide rod (21).

5. The buffer device for aircraft landing gear according to claim 4, characterized in that: A connection hole (23) is provided inside one end of the movable plate (8) close to the mounting seat (9), and one end of the guide rod (21) is arranged inside the connection hole (23).

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