Lubricating device before necking of aircraft cylinder damper

Abstract

The utility model relates to the technical field of lubricating devices, and discloses an aircraft cylinder damper necking front lubricating device which comprises a base, a plurality of supporting blocks are fixedly connected to the outer wall of the upper end of the base, guide rods are fixedly connected to the inner walls of the supporting blocks, and a top plate is fixedly connected to the other ends of the guide rods at the same time. A connecting sleeve is fixedly connected to the upper surface of the inner wall of the base, a power mechanism is connected to the bottom face of the connecting sleeve, and the output end of the power mechanism penetrates through the connecting sleeve and is connected with a rotating assembly. According to the lubricating device before necking of the aircraft cylinder damper, when lubricating oil is smeared on the surface of a shell of the aircraft cylinder damper, the damper shell only needs to be placed on the rotating assembly, then the damper shell is pressed from the upper portion of the damper shell through the positioning mechanism, and then the rotating assembly, the oil brushing assembly and the adjusting assembly are driven by the power mechanism to rotate; therefore, the surface of the aircraft cylinder damper shell can be uniformly coated with lubricating oil, manual oil coating can be replaced, and the labor productivity is improved.

Description

Technical Field

[0001] The utility model relates to the technical field of lubrication devices, in particular to a lubrication device before necking of an aircraft cylinder damper. Background Art

[0002] Aircraft damper is an elastic damping element. During the production process, it is necessary to first extrude the cylinder through the necking machine die to reach the specified diameter size and then perform fine processing. In order to reduce the axial resistance during the necking process, make the necking process uniform and continuous, and ensure that the outer wall of the damper is smooth and free of scratches after necking, lubricating oil must be applied first.

[0003] At present, when applying lubricating oil to the outer shell of the aircraft cylinder damper, it is mostly done manually using a brush. This lubrication method is not only inefficient, but may also cause uneven oiling, thereby affecting the extrusion effect and resulting in a high scrap rate in the later stage. Utility Model Content

[0004] In view of the deficiencies in the prior art, the utility model provides a pre-neck lubrication device for an aircraft cylindrical damper, so as to solve the problem that the lubricating oil is currently applied manually to the outer shell of the aircraft cylindrical damper, resulting in low efficiency and uneven oiling, thereby affecting the extrusion effect and causing a high scrap rate in the later stage.

[0005] To achieve the above-mentioned purpose, the utility model provides the following technical solutions: a pre-neck lubrication device for an aircraft cylinder damper, comprising a base, a plurality of support blocks are fixedly connected to the outer wall of the upper end of the base, the inner walls of the plurality of support blocks are fixedly connected to guide rods, the other ends of the plurality of guide rods are also fixedly connected to a top plate, a connecting sleeve is fixedly connected to the upper surface of the inner wall of the base, a power mechanism is connected to the bottom surface of the connecting sleeve, the output end of the power mechanism passes through the connecting sleeve and is connected to a rotating component, two oil brushing components are connected to the inner wall of the rotating component, the other ends of the two oil brushing components are also connected to an adjusting component, the other side of the adjusting component is connected to the bottom surface of the top plate, a positioning mechanism is connected to the upper surface of the top plate, the output end of the positioning mechanism passes through the top plate and the adjusting component, and is located directly above the rotating component, a core shaft is rotatably connected to the middle part of the upper surface of the rotating component, the cross section of the core shaft is conical, and one end of the core shaft cone faces the center of the positioning mechanism.

[0006] Furthermore, the power mechanism includes a motor and a reducer, the output shaft of the motor is fixedly connected to the input shaft of the reducer, the mounting flange of the reducer is fixedly connected to the connecting sleeve, and the output shaft of the reducer is connected to the rotating assembly.

[0007] Furthermore, the rotating assembly includes a support column and a chassis. The bottom surface of the support column is fixedly connected to the output shaft of the reducer. The upper end of the support column passes through the connecting sleeve and is fixedly connected to the bottom surface of the chassis. The upper surface of the chassis is connected to two oil brush assemblies.

[0008] Furthermore, the oil brushing assembly includes a support rod and a brush, the brush is sleeved on and bonded to the outer wall of the support rod, the lower end of the support rod is connected to the upper surface of the chassis, and the upper end of the support rod is connected to the adjustment assembly.

[0009] Furthermore, the adjustment assembly includes a top plate, a knob, a bidirectional screw and two moving blocks. The upper end of the top plate is connected to the lower end of the top plate. Two symmetrical moving grooves are opened on the bottom surface of the top plate. The outer walls of the two moving blocks are respectively slidably connected to the inner walls of the two moving grooves. The bidirectional screw runs through the two moving blocks and the two moving grooves and is fixedly connected to one side of the knob. The bidirectional screw is threadedly connected to the two moving blocks. The upper ends of the two support rods are respectively fixedly connected to the lower ends of the two moving blocks.

[0010] Furthermore, two slide grooves are provided on the upper surface of the chassis, and sliders are fixedly connected to the sides of the two support rods away from the moving block, and the outer walls of the two sliders are slidably connected to the inner walls of the two slide grooves respectively.

[0011] Furthermore, an anti-slip groove is provided on the bottom surface of the top plate, an anti-slip disc is fixedly connected to the upper surface of the top plate, and an outer wall of the anti-slip disc is rotatably connected to an inner wall of the anti-slip groove.

[0012] Furthermore, the positioning mechanism includes an electric push rod and a pressure plate, the outer wall of the electric push rod is fixedly connected to the upper surface of the top plate, the output flange of the electric push rod passes through the top plate and the top plate, and is fixedly connected to the upper surface of the pressure plate, and the electric push rod and the pressure plate are both located directly above the chassis.

[0013] Compared with the prior art, the utility model has the following beneficial effects:

[0014] The aircraft cylinder damper necking front lubrication device comprises a base, a support block, a guide rod and a top plate to form an external frame, and a power mechanism, a rotating assembly, an oil brushing assembly, an adjustment assembly and a positioning mechanism are arranged inside the frame. When lubricating oil is applied to the outer surface of the aircraft cylinder damper shell, it is only necessary to place the damper shell on the rotating assembly, and then press the damper shell from the top through the positioning mechanism, and then the rotating assembly, the oil brushing assembly and the adjustment assembly are driven to rotate by the power mechanism, so that the lubricating oil can be evenly applied to the outer surface of the aircraft cylinder damper shell, thereby replacing manual oiling and improving labor productivity. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] Figure 1 It is a schematic diagram of the overall appearance of the utility model;

[0016] Figure 2 It is a schematic diagram of the internal structure of the overall components of the utility model;

[0017] Figure 3 It is a cross-sectional schematic diagram of the base, top plate, support block and other components of the utility model;

[0018] Figure 4 It is a detailed connection diagram of the power mechanism, rotating assembly and oil brushing assembly of the utility model;

[0019] Figure 5 For this utility model Figure 4 Exploded diagram of each component in the diagram;

[0020] Figure 6 For this utility model Figure 5 A magnified schematic diagram of center A.

[0021] In the figure: 1. base; 2. support block; 3. guide rod; 4. top plate; 5. electric push rod; 6. pressure plate; 7. top plate; 8. knob; 9. bottom plate; 10. core shaft; 11. brush; 12. two-way screw rod; 13. moving block; 14. motor; 15. reducer; 16. connecting sleeve; 17. support column; 18. anti-slip plate; 19. slider; 20. support rod; 401, anti-slip groove; 701, moving groove; 901, slide groove. DETAILED DESCRIPTION

[0022] The technical solutions in the embodiments of the present invention will be described clearly and completely below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, rather than all of the embodiments.

[0023] See also Figure 1-Figure 6 A front lubrication device for shrinking neck of an aircraft cylinder damper comprises a base 1, a plurality of support blocks 2 are fixedly connected to the outer wall of the upper end of the base 1, a plurality of guide rods 3 are fixedly connected to the inner walls of the plurality of support blocks 2, a top plate 4 is fixedly connected to the other ends of the plurality of guide rods 3, a connecting sleeve 16 is fixedly connected to the upper surface of the inner wall of the base 1, a power mechanism is connected to the bottom surface of the connecting sleeve 16, an output end of the power mechanism passes through the connecting sleeve 16 and is connected to a rotating assembly, two oil brushing assemblies are connected to the inner wall of the rotating assembly, the other ends of the two oil brushing assemblies are connected to an adjusting assembly at the same time, the other side of the adjusting assembly is connected to the bottom surface of the top plate 4, a positioning mechanism is connected to the upper surface of the top plate 4, the output end of the positioning mechanism passes through the top plate 4 and the adjusting assembly and is located directly above the rotating assembly, a core shaft 10 is rotatably connected to the middle part of the upper surface of the rotating assembly, the cross section of the core shaft 10 is conical, and one end of the pointed cone of the core shaft 10 faces the center of the positioning mechanism.

[0024] like Figures 1 to 6As shown, when applying lubricating oil to the outer shell surface of the aircraft cylindrical damper, the aircraft cylindrical damper front necking lubricating device in the utility model only needs to place the outer shell of the aircraft cylindrical damper that needs to be applied with lubricating oil on the rotating assembly, and then press it onto the rotating assembly from the top of the outer shell of the aircraft cylindrical damper through the positioning mechanism, and then start the power mechanism. After the power mechanism is started, it will drive the rotating assembly to rotate, and after the rotating assembly rotates, it can drive the oil brushing assembly and the adjustment assembly to rotate, and then the outer shell of the aircraft cylindrical damper in the middle of the oil brushing assembly can be rotated, and then the outer shell of the aircraft cylindrical damper can be evenly applied with lubricating oil during the rotation process. After applying, the power mechanism is stopped, and the positioning mechanism is controlled to rise, and then the outer shell of the aircraft cylindrical damper can be removed from the rotating assembly, thereby replacing manual oiling and improving labor productivity.

[0025] By providing the core shaft 10, when placing the aircraft cylinder damper shell on the rotating assembly, the aircraft cylinder damper shell opening only needs to be inserted on the core shaft 10 to automatically locate it in the center position, thereby allowing the two brushes 11 to apply oil more evenly.

[0026] like Figure 2 As shown, the power mechanism includes a motor 14 and a reducer 15, the output shaft of the motor 14 is fixedly connected to the input shaft of the reducer 15, the mounting flange of the reducer 15 is fixedly connected to the connecting sleeve 16, and the output shaft of the reducer 15 is connected to the rotating component.

[0027] More specifically, when it is necessary to control the rotating components, oil brushing components and adjustment components to rotate around the outer shell of the aircraft cylindrical damper, it is only necessary to turn on the motor 14. After the motor 14 is started, the speed can be reduced by the reducer 15 to drive the rotating components to rotate, thereby evenly applying oil to the outer shell surface of the aircraft cylindrical damper.

[0028] It should be noted that: in order to prevent leakage from harming the operator, a 24V low-speed DC motor is used as the power source in this embodiment; and the reducer 15 is a prior art, so its internal structure and principle are not described in detail.

[0029] like Figure 2 , Figure 4 and Figure 5 As shown, the rotating assembly includes a support column 17 and a chassis 9. The bottom surface of the support column 17 is fixedly connected to the output shaft of the reducer 15. The upper end of the support column 17 passes through the connecting sleeve 16 and is fixedly connected to the bottom surface of the chassis 9. The upper surface of the chassis 9 is connected to two oil brush assemblies.

[0030] More specifically, when the reducer 15 rotates, it can drive the support column 17 to rotate. After the support column 17 rotates, it can drive the chassis 9 to rotate. After the chassis 9 rotates, it can drive the two oil brushing components on the surface to rotate in the same direction, thereby oiling the outer shell surface of the aircraft cylinder damper.

[0031] like Figure 1 , Figure 2 , Figure 4-Figure 6 As shown, the oil brushing assembly includes a support rod 20 and a brush 11. The brush 11 is sleeved on and bonded to the outer wall of the support rod 20. The lower end of the support rod 20 is connected to the upper surface of the chassis 9, and the upper end of the support rod 20 is connected to the adjustment assembly.

[0032] More specifically, when the chassis 9 rotates, the support rod 20 connected to its surface can be driven to rotate, and after the support rod 20 rotates, the brush 11 bonded to its surface can be rotated, so that the surface of the aircraft cylinder damper shell can be oiled.

[0033] It should be particularly noted here that the brush 11 and the support rod 20 are bonded together so that the brush 11 can be oiled and replaced when it is worn.

[0034] like Figure 1 , Figure 2 , Figure 4-Figure 6 As shown, the adjustment component includes a top plate 7, a knob 8, a bidirectional screw rod 12 and two moving blocks 13. The upper end of the top plate 7 is connected to the lower end of the top plate 4. Two symmetrically arranged moving grooves 701 are provided on the bottom surface of the top plate 7. The outer walls of the two moving blocks 13 are respectively slidably connected to the inner walls of the two moving grooves 701. The bidirectional screw rod 12 passes through the two moving blocks 13 and the two moving grooves 701, and is fixedly connected to one side of the knob 8. The bidirectional screw rod 12 and the two moving blocks 13 are both threadedly connected. The upper ends of the two support rods 20 are respectively fixedly connected to the lower ends of the two moving blocks 13.

[0035] More specifically, when the support rod 20 rotates, the top plate 7 can be driven to rotate through the moving block 13, thereby achieving the oiling action.

[0036] The role of the adjustment component here is: because the aircraft cylindrical damper shells processed in the same batch may have different diameters and heights (which can be compensated for by the positioning mechanism), it is necessary to change the distance between the two oil brushing components.

[0037] The specific method is: when the distance between the two brushes 11 needs to be adjusted, just turn the knob 8. After the knob 8 is turned, the bidirectional screw rod 12 can be driven to rotate. After the bidirectional screw rod 12 is rotated, the two moving blocks 13 connected on the surface can be driven to move in the opposite direction, thereby changing the distance between the two moving blocks 13 and the support rod 20 below them.

[0038] like Figure 1 , Figure 2 , Figure 4 and Figure 5 As shown, two slide grooves 901 are provided on the upper surface of the chassis 9 , and sliders 19 are fixedly connected to the sides of the two support rods 20 away from the moving block 13 , and the outer walls of the two sliders 19 are slidably connected to the inner walls of the two slide grooves 901 , respectively.

[0039] More specifically, by providing the slide groove 901 and the slider 19, a limit and support can be added to the bottom surface of the support rod 20 to prevent the support rod 20 and the brush 11 on its surface from opening and tilting outward during oiling.

[0040] like Figure 3 As shown, an anti-slip groove 401 is provided on the bottom surface of the top plate 4 , an anti-slip disc 18 is fixedly connected to the upper surface of the top plate 7 , and an outer wall of the anti-slip disc 18 is rotatably connected to an inner wall of the anti-slip groove 401 .

[0041] More specifically, by providing the anti-drop plate 18 and the anti-drop groove 401, firstly, it can be ensured that the top plate 7 will not fall off the top plate 4; secondly, when the top plate 7 rotates, its rotation will not be affected.

[0042] It should be noted here that bearings can also be used as a substitute as long as the effect is the same.

[0043] like Figure 1 , Figure 2 , Figure 4 and Figure 5 As shown, the positioning mechanism includes an electric push rod 5 and a pressure plate 6. The outer wall of the electric push rod 5 is fixedly connected to the upper surface of the top plate 4. The output flange of the electric push rod 5 passes through the top plate 4 and the top plate 7, and is fixedly connected to the upper surface of the pressure plate 6. The electric push rod 5 and the pressure plate 6 are both located directly above the chassis 9.

[0044] More specifically, when the aircraft cylindrical damper shell needs to be compressed, the electric push rod 5 only needs to be turned on, and the output end of the electric push rod 5 can push the pressure plate 6 down, and then the aircraft cylindrical damper shell can be pressed against the outer wall of the core shaft 10 from above the aircraft cylindrical damper shell.

[0045] It should be noted that when the electric push rod 5 and the pressure plate 6 are used to limit the downward pressure on the aircraft cylinder damper shell, there is no need for excessive pressure. It is only necessary to press the damper shell on the surface of the core shaft 10 so that it will not rotate together with the two brushes 11 when they rotate. The pressure here can be controlled in advance by the PLC controller to control the height of the downward pressure (for example, if the height between the pressure plate 6 and the damper shell is 10 cm, then it is only necessary to control the electric push rod 5 to rise 10 cm) to avoid excessive pressure and damage to the damper shell.

[0046] Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that various changes, modifications, substitutions and variations may be made to the embodiments without departing from the principles and spirit of the present invention, and that the scope of the present invention is defined by the appended claims and their equivalents.

Claims

1. A lubrication device for the front necking of an aircraft cylinder damper, characterized in that: The invention comprises a base (1), wherein the outer wall of the upper end of the base (1) is fixedly connected to a plurality of support blocks (2), the inner walls of the plurality of support blocks (2) are fixedly connected to guide rods (3), the other ends of the plurality of guide rods (3) are fixedly connected to a top plate (4), the upper surface of the inner wall of the base (1) is fixedly connected to a connecting sleeve (16), the bottom surface of the connecting sleeve (16) is connected to a power mechanism, the output end of the power mechanism passes through the connecting sleeve (16) and is connected to a rotating assembly, the inner wall of the rotating assembly is connected to two oil brushing assemblies, the other ends of the two oil brushing assemblies are simultaneously connected to an adjusting assembly, the other side of the adjusting assembly is connected to the bottom surface of the top plate (4), the upper surface of the top plate (4) is connected to a positioning mechanism, the output end of the positioning mechanism passes through the top plate (4) and the adjusting assembly and is located directly above the rotating assembly, the middle part of the upper surface of the rotating assembly is rotatably connected to a core shaft (10), the cross section of the core shaft (10) is conical, and one end of the core shaft (10) is pointed toward the center of the positioning mechanism.

2. The aircraft cylinder damper necking front lubrication device according to claim 1, characterized in that: The power mechanism comprises a motor (14) and a reducer (15); the output shaft of the motor (14) is fixedly connected to the input shaft of the reducer (15); the mounting flange of the reducer (15) is fixedly connected to the connecting sleeve (16); and the output shaft of the reducer (15) is connected to the rotating assembly.

3. The aircraft cylinder damper necking front lubrication device according to claim 2, characterized in that: The rotating assembly comprises a support column (17) and a chassis (9); the bottom surface of the support column (17) is fixedly connected to the output shaft of the reducer (15); the upper end of the support column (17) passes through the connecting sleeve (16) and is fixedly connected to the bottom surface of the chassis (9); and the upper surface of the chassis (9) is connected to two oil brush assemblies.

4. The aircraft cylinder damper necking front lubrication device according to claim 3, characterized in that: The oil brushing assembly comprises a support rod (20) and a brush (11), wherein the brush (11) is sleeved on and bonded to the outer wall of the support rod (20), the lower end of the support rod (20) is connected to the upper surface of the chassis (9), and the upper end of the support rod (20) is connected to the adjustment assembly.

5. The aircraft cylinder damper necking front lubrication device according to claim 4, characterized in that: The adjustment assembly comprises a top plate (7), a knob (8), a bidirectional screw rod (12) and two moving blocks (13); the upper end of the top plate (7) is connected to the lower end of the top plate (4); the bottom surface of the top plate (7) is provided with two symmetrically arranged moving grooves (701); the outer walls of the two moving blocks (13) are respectively slidably connected to the inner walls of the two moving grooves (701); the bidirectional screw rod (12) passes through the two moving blocks (13) and the two moving grooves (701) and is fixedly connected to one side of the knob (8); the bidirectional screw rod (12) and the two moving blocks (13) are both threadedly connected; the upper ends of the two support rods (20) are respectively fixedly connected to the lower ends of the two moving blocks (13).

6. The aircraft cylinder damper necking front lubrication device according to claim 5, characterized in that: Two slide grooves (901) are provided on the upper surface of the chassis (9); a slider (19) is fixedly connected to the two support rods (20) on the side away from the moving block (13); and the outer walls of the two sliders (19) are respectively slidably connected to the inner walls of the two slide grooves (901).

7. The aircraft cylinder damper pre-neck lubrication device according to claim 5 or 6, characterized in that: The bottom surface of the top plate (4) is provided with an anti-slip groove (401), the upper surface of the top plate (7) is fixedly connected with an anti-slip disc (18), and the outer wall of the anti-slip disc (18) is rotatably connected to the inner wall of the anti-slip groove (401).

8. The aircraft cylinder damper pre-neck lubrication device according to claim 5 or 6, characterized in that: The positioning mechanism comprises an electric push rod (5) and a pressure plate (6); the outer wall of the electric push rod (5) is fixedly connected to the upper surface of the top plate (4); the output flange of the electric push rod (5) penetrates the top plate (4) and the top plate (7), and is fixedly connected to the upper surface of the pressure plate (6); the electric push rod (5) and the pressure plate (6) are both located directly above the bottom plate (9).

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