Airplane actuator cylinder dismounting device

Abstract

The utility model discloses an aircraft actuator cylinder dismounting device, and relates to the technical field of aircraft maintenance tools. The aircraft actuator cylinder dismounting device comprises a shell; the clamping structure comprises two clamping pieces, the two clamping pieces are rotationally connected to the shell, and one ends of the two clamping pieces are located outside the same side of the shell; the driving structure is used for driving the two clamping pieces to rotate and enabling the ends, located outside the shell, of the two clamping pieces to move close to each other; and the propelling structure comprises a propelling shaft, and the propelling shaft is connected to the exterior of the shell in a sliding mode. The aircraft actuator cylinder has the effect that the aircraft actuator cylinder is convenient to disassemble.

Description

Technical Field

[0001] The present application relates to the technical field of aircraft maintenance tools, and in particular to an aircraft actuator disassembly device. Background Art

[0002] The actuator is a device that drives the linear motion of a rod through hydraulic pressure. It is mainly used in the aerospace field and can be used to drive and execute actions in systems such as aircraft flaps, tail fins and landing legs, as well as rocket trajectory change units.

[0003] The actuator cylinder includes a cylinder body and a rod. One end of the rod is located in the shell and is connected to a round wheel. A rubber ring is provided on the round wheel. The rubber ring can ensure the sealing of the contact between the round wheel and the shell to ensure that the rod can be driven to move linearly by hydraulic pressure. At the same time, in order to ensure the stability of the actuator cylinder structure and the sealing of the hydraulic structure, the actuator cylinder is also provided with multiple threaded connections.

[0004] In order to ensure the sealing of the contact between the round wheel and the housing, the round wheel, the rubber ring and the cylinder are often in close contact, which makes it difficult to remove the rod from the housing; at the same time, the threaded connection on the actuator is relatively smooth, there is no suitable operating structure for unscrewing, and there is no suitable disassembly tool. The above reasons make the disassembly and maintenance of the actuator very inconvenient. Utility Model Content

[0005] In order to facilitate the disassembly of an aircraft actuator, the present application provides an aircraft actuator disassembly device.

[0006] The present application provides an aircraft actuator disassembly device, which adopts the following technical solution:

[0007] An aircraft actuator disassembly device comprises a housing;

[0008] A clamping structure, the clamping structure comprising two clamping members, the clamping members are rotatably connected to the shell, and one end of the two clamping members is located outside the same side of the shell;

[0009] A driving structure, the driving structure is used to drive the two clamping members to rotate and make the ends of the two clamping members located outside the housing move closer to each other;

[0010] The propulsion structure comprises a propulsion shaft, and the propulsion shaft is slidably connected to the outside of the shell.

[0011] By adopting the above technical solution, the parts to be disassembled that are threadedly connected to the actuator can be placed between two clamping members, and the clamping members are driven to rotate by the driving structure so that the ends of the clamping members located outside the shell move closer to each other, thereby clamping the parts to be disassembled of the actuator, and then the entire aircraft actuator disassembly device is rotated to unscrew the threaded connection structure of the actuator. In addition, the propulsion shaft can move on the shell to push the rod in the actuator to move, thereby removing the rod and facilitating the disassembly of the actuator.

[0012] Optionally, one end of the clamping member located in the shell is fixedly connected to a pulling rope, the driving structure includes a pulling member slidably connected to the shell, and one end of the pulling rope away from the clamping member is fixedly connected to the pulling member;

[0013] The rotation axes of the two clamping members coincide with each other, and when the pulling member moves in a direction away from the clamping member, one end of the two clamping members located inside the shell can rotate in a direction toward each other.

[0014] By adopting the above technical solution, the rotation axes of the two clamping members coincide, and the lifting rope can be pulled by the lifting member, thereby pulling the ends of the two clamping members located inside the shell to rotate towards each other. At this time, the ends of the clamping members located outside the shell also move closer and clamp the actuator cylinder, thereby improving the convenience of operating the actuator cylinder disassembly device.

[0015] Optionally, two rotating wheels are rotatably connected in the shell, the rotating wheels are located at one end of the shell close to the clamping member and between the ends of the two clamping members, and a rotating groove for the pulling rope to pass through is opened on the outer wall of the rotating wheel.

[0016] By adopting the above technical solution, the rotating wheel guides the direction in which the lifting rope pulls the clamp, making it easier to pull the lifting rope to clamp the actuator cylinder, thereby improving the ease of use of the aircraft actuator cylinder disassembly device. At the same time, the clamping force of the clamp is greater, the clamping stability is higher, the rotation range of the clamp is larger, and the clamping stability is higher.

[0017] Optionally, a sliding hole for the lifting member to slide is provided on the shell, and a through hole is provided on the shell, the through direction of which is perpendicular to and connected to the through direction of the sliding hole.

[0018] By adopting the above technical solution, when the operator pulls the lifting member, he can hold the shell and the lifting member through the through hole, and then apply a gripping force to make the lifting member slide in the sliding hole, making it easier to operate when pulling the lifting member.

[0019] Optionally, a first fixing portion and a second fixing portion are fixedly connected to an outer wall of the shell, the propulsion shaft passes through the first fixing portion and the second fixing portion at the same time, and the propulsion shaft and the second fixing portion are threadedly connected.

[0020] By adopting the above technical solution, the first fixed part can support and guide the propulsion shaft, and the propulsion shaft is threadedly connected to the second fixed part, so that the propulsion shaft can move when the propulsion shaft is rotated. The movement of the propulsion shaft can be more labor-saving by rotation, making the aircraft actuator disassembly device more convenient to use.

[0021] Optionally, the clamping structure includes an extension section rotatably connected to an end of the clamping member located outside the shell, and the propulsion shaft can pass between the two extension sections when moving on the first fixing portion and the second fixing portion.

[0022] By adopting the above technical solution, the extension section can fix the actuator cylinder body, and then push the rod inside the actuator cylinder through the propulsion shaft, making the actuator cylinder more convenient to disassemble; the extension section and the clamping member are rotatably connected so that the extension section and the actuator cylinder fit better, and can be suitable for actuators of different diameters.

[0023] Optionally, a first anti-slip pad is provided on a surface of the extension section close to the other extension section, and a first groove is provided on the first anti-slip pad; a second anti-slip pad is provided on an end of the clamping member close to the extension section, and the second anti-slip pad is located on a surface of the clamping member close to the other clamping member, and a second groove is provided on the second anti-slip pad.

[0024] By adopting the above technical solution, the first anti-slip pad can increase the friction between the parts to be disassembled that are threadedly connected between the clamping member and the actuator cylinder, the second anti-slip pad can enhance the friction between the extension section and the actuator cylinder body, and the first groove and the second groove can respectively increase the contact area between the first anti-slip pad, the second anti-slip pad and the actuator cylinder, making it more stable when the actuator cylinder is clamped by the clamping member or the extension section.

[0025] Optionally, a tension spring is arranged in the shell, one end of the tension spring is fixedly connected to the inner wall of the shell, and the other end of the tension spring is fixedly connected to an end of the clamping member away from the rotating wheel.

[0026] By adopting the above technical solution, when the lifting member moves in the direction away from the clamping member, the tension spring is stretched. When the lifting member is released, the two clamping members can rotate in the opposite direction through the restoring force of the tension spring, which facilitates the separation of the actuator and the disassembly tool, and also makes it more convenient to place the actuator between the clamping members.

[0027] Optionally, one end of the propulsion shaft away from the extension section is fixedly connected to a handle, and one end of the propulsion shaft away from the handle is fixedly connected to a protrusion.

[0028] By adopting the above technical solution, the handle can easily rotate the propulsion shaft to move the propulsion shaft, and the protrusion can reduce the friction between the propulsion shaft and the actuator rod, making it easier for the propulsion shaft to push the actuator rod.

[0029] In summary, the present application includes at least one of the following beneficial effects:

[0030] 1. The clamping structure makes it easy to unscrew the threaded connection structure of the actuator, which greatly facilitates the disassembly of the actuator;

[0031] 2. The cooperation between the pushing structure and the clamping structure can facilitate the removal of the rod from the actuator, thereby facilitating the disassembly of the actuator;

[0032] 3. The rotating wheel can guide the direction in which the lifting rope pulls the clamping piece, making it easier to tighten the lifting piece;

[0033] 4. The extension section is rotatably connected to the clamping member, so that the actuator disassembly device can be suitable for actuators of different diameters. BRIEF DESCRIPTION OF THE DRAWINGS

[0034] Figure 1 It is a schematic diagram of the overall structure of an embodiment of the present application;

[0035] Figure 2 is a schematic diagram showing a clamping structure and a driving structure in an embodiment of the present application;

[0036] Figure 3 yes Figure 2 A partial enlarged view of point A in the middle.

[0037] Explanation of the accompanying drawings: 1. Shell; 11. Through hole; 12. Sliding hole; 13. First fixing portion; 14. Second fixing portion; 15. Top cover; 2. Clamping structure; 21. Clamping member; 22. Extension section; 23. Tension spring; 3. Driving structure; 31. Lifting rope; 32. Lifting member; 33. Rotating wheel; 331. Rotating groove; 4. Propelling structure; 41. Propelling shaft; 42. Handle; 43. Protrusion; 5. First anti-slip pad; 51. First groove; 6. Second anti-slip pad; 61. Second groove. DETAILED DESCRIPTION

[0038] The following is combined with Figure 1-3 This application is described in further detail.

[0039] The present application discloses an aircraft actuator disassembly device, referring to Figure 1 and Figure 2 The aircraft actuator disassembly device includes a shell 1, to which a clamping structure 2, a driving structure 3 and a propulsion structure 4 are connected. The driving structure 3 can drive the clamping structure 2 to clamp the to-be-disassembled part of the actuator threadedly connected, thereby separating the threaded connection structure of the actuator. At the same time, the actuator can be clamped by the clamping structure 2, and then the rod in the actuator can be pushed by the propulsion structure 4, so as to remove the rod, making the disassembly of the actuator more convenient.

[0040] Reference Figure 1 and Figure 2 The shell 1 is a long hollow shape, and includes a triangular portion that tapers at one end, and the triangular portion is provided with an opening that communicates with the inner cavity of the shell 1. The shell 1 includes a top cover 15 that can be removed by screws, and the top cover 15 can facilitate the installation of the structure inside the shell 1. The clamping structure 2 includes two clamping members 21, which are coaxially rotatably connected to the inner wall of the sharp corner of the shell 1, and one end of the two clamping members 21 is located outside the shell 1. The driving structure 3 can drive the ends of the two clamping members 21 located outside the shell 1 to rotate in a direction close to each other, thereby clamping the actuator.

[0041] Reference Figure 2 and Figure 3 The driving structure 3 includes a lifting rope 31 and a lifting member 32. One end of the lifting rope 31 is fixedly connected to one end of the clamping member 21 located in the housing 1, and the end of the lifting rope 31 away from the clamping member 21 is fixedly connected to the lifting member 32. Sliding holes 12 are provided on the opposite side walls of the housing 1. Both ends of the lifting member 32 are located in the sliding holes 12 and can slide in the sliding holes 12 in the direction of approaching and moving away from the clamping member 21. The housing 1 is provided with a through hole 11 whose penetration direction is perpendicular to and connected to the penetration direction of the sliding hole 12. The operator can pull the lifting member 32 to slide in the sliding hole 12 through the through hole 11, thereby driving the lifting rope 31. The lifting rope 31 pulls the two clamping members 21 to rotate, so that the clamping member 21 can clamp the parts to be disassembled that are threadedly connected to the actuator, which is convenient for unscrewing the threaded connection structure of the actuator, and reduces the difficulty of disassembling the actuator.

[0042] Reference Figure 2 and Figure 3 There are two rotating wheels 33 rotatably connected in the shell 1. The two rotating wheels 33 are located at one end of the shell 1 close to the clamping member 21 and between the ends of the two clamping members 21. A rotating groove 331 for the pulling rope 31 to pass through is opened on the outer wall of the rotating wheel 33. The rotating wheel 33 can adjust the direction in which the pulling rope 31 pulls the clamping member 21, so that it is more labor-saving to pull the pulling rope 31 through the pulling member 32 to drive the clamping member 21 to clamp.

[0043] A tension spring 23 is provided at one end of the clamping member 21 located in the shell 1, and one end of the tension spring 23 is fixedly connected to the side wall of the clamping member 21 away from the rotating wheel 33, and the end of the tension spring 23 away from the clamping member 21 is fixedly connected to the inner wall of the shell 1. When the lifting member 32 moves in the direction away from the clamping member 21, the tension spring 23 is stretched. When the lifting member 32 is released, the restoring force of the tension spring 23 allows the two clamping members 21 to rotate in the opposite direction, which is convenient for separating the actuator and the disassembly tool, and also convenient for placing the actuator between the clamping members 21, making the actuator disassembly device more convenient to use.

[0044] Reference Figure 1 and Figure 2 One end of the clamping member 21 located outside the housing 1 is rotatably connected to an extension section 22 parallel to the rotation axis of the clamping member 21. The extension section 22 can clamp the actuator cylinder as the clamping member 21 rotates. The extension section 22 is rotatably connected to the clamping member 21 so that the extension section 22 clamps the actuator cylinder more closely and more firmly, and at the same time, the extension section 22 can clamp actuator cylinders of different diameters.

[0045] The propulsion structure 4 includes a propulsion shaft 41, and a first fixing portion 13 and a second fixing portion 14 are fixedly connected on one side of the outer wall of the shell 1. The propulsion shaft 41 passes through the first fixing portion 13 and the second fixing portion 14, and the axis of the propulsion shaft 41 is located between the two extension sections 22. The propulsion shaft 41 is threadedly connected to the second fixing portion 14, and the end of the propulsion shaft 41 away from the extension section 22 is fixedly connected to the handle 42, and the end of the propulsion shaft 41 away from the handle 42 is fixedly connected to a plastic protrusion 43.

[0046] The first fixing portion 13 can support and guide the propulsion shaft 41; when the extension section 22 clamps the actuator, since the propulsion shaft 41 and the second fixing portion 14 are threadedly connected, the handle 42 can be turned to move the propulsion shaft 41 and press against the rod in the actuator, thereby pushing the rod out of the actuator body, making it easier to disassemble the actuator, and moving the propulsion shaft 41 by rotation can be more labor-saving, making the aircraft actuator disassembly device more convenient to use; the plastic protrusion 43 can reduce the friction between the propulsion shaft 41 and the actuator rod, making it easier to rotate the propulsion shaft 41 through the handle 42.

[0047] Reference Figure 1 and Figure 2 A first anti-skid pad 5 is fixedly connected to one side of the clamping member 21 that presses against the actuator, and a first groove 51 is provided on the first anti-skid pad 5; a second anti-skid pad 6 is fixedly connected to one side of the extension section 22 that presses against the actuator, and a second groove 61 is provided on the second anti-skid pad 6; the first anti-skid pad 5 and the first groove 51 can increase the friction between the clamping member 21 and the actuator, and the second anti-skid pad 6 and the second groove 61 can increase the friction between the extension section 22 and the actuator, so that the clamping member 21 and the extension section clamp the actuator more firmly.

[0048] The implementation principle of an aircraft actuator disassembly device according to an embodiment of the present application is as follows: when it is necessary to disassemble the threaded connection component of the actuator, the component to be disassembled is placed between the two first grooves 51, the lifting member 32 is tightened, the component to be disassembled that is threadedly connected to the actuator is clamped by the clamping member 21, and then the actuator disassembly device is rotated to unscrew the component to be disassembled; when it is necessary to remove the rod from the actuator, the actuator can be placed between the two second grooves 61, the lifting member 32 is tightened, the actuator is fixed, and then the handle 42 is rotated to move the propulsion shaft 41 along the axial direction, thereby pushing the rod in the actuator and pushing the rod out of the actuator. Through the aircraft actuator disassembly device, the threaded connection components of the actuator and the rod in the actuator are more convenient to disassemble, making it more convenient to disassemble the aircraft actuator.

[0049] The above are all preferred embodiments of the present application, and the protection scope of the present application is not limited thereto. Therefore, any equivalent changes made according to the structure, shape, and principle of the present application should be included in the protection scope of the present application.

Claims

1. An aircraft actuator disassembly device, characterized in that: comprising a housing (1); A clamping structure (2), the clamping structure (2) comprising two clamping members (21), the clamping members (21) being rotatably connected to the shell (1), and one end of the two clamping members (21) being located outside the same side of the shell (1); A driving structure (3), the driving structure (3) being used to drive the two clamping members (21) to rotate and to cause ends of the two clamping members (21) located outside the housing (1) to move closer to each other; A propulsion structure (4), the propulsion structure (4) comprising a propulsion shaft (41), the propulsion shaft (41) being slidably connected to the outside of the shell (1).

2. The aircraft actuator disassembly device according to claim 1, characterized in that: One end of the clamping member (21) located inside the housing (1) is fixedly connected to a pulling rope (31); the driving structure (3) comprises a pulling member (32) slidably connected to the housing (1); and one end of the pulling rope (31) away from the clamping member (21) is fixedly connected to the pulling member (32); The rotation axes of the two clamping members (21) coincide with each other, and when the lifting member (32) moves in a direction away from the clamping members (21), one end of the two clamping members (21) located inside the housing (1) can rotate in a direction towards each other.

3. The aircraft actuator disassembly device according to claim 2, characterized in that: Two rotating wheels (33) are rotatably connected inside the housing (1); the rotating wheels (33) are located at one end of the housing (1) close to the clamping member (21) and between the ends of the two clamping members (21); and a rotating groove (331) is provided on the outer wall of the rotating wheel (33) for the pulling rope (31) to pass through.

4. The aircraft actuator disassembly device according to claim 2, characterized in that: The shell (1) is provided with a sliding hole (12) for the lifting member to slide, and the shell (1) is provided with a through hole (11) whose penetration direction is perpendicular to and connected to the penetration direction of the sliding hole (12).

5. The aircraft actuator disassembly device according to claim 1, characterized in that: The outer wall of the housing (1) is fixedly connected with a first fixing portion (13) and a second fixing portion (14); the propulsion shaft (41) passes through both the first fixing portion (13) and the second fixing portion (14); and the propulsion shaft (41) and the second fixing portion (14) are threadedly connected.

6. The aircraft actuator disassembly device according to claim 5, characterized in that: The clamping structure (2) comprises an extension section (22) rotatably connected to the clamping member (21) and located at one end outside the housing (1), and the propulsion shaft (41) can pass through the area between the two extension sections (22) when moving on the first fixing portion (13) and the second fixing portion (14).

7. The aircraft actuator disassembly device according to claim 6, characterized in that: A first anti-skid pad (5) is provided on a surface of the extension section (22) close to the other extension section (22), and a first groove (51) is provided on the first anti-skid pad (5); a second anti-skid pad (6) is provided on an end of the clamping member (21) close to the extension section (22), and the second anti-skid pad (6) is located on a surface of the clamping member (21) close to the other clamping member (21), and a second groove (61) is provided on the second anti-skid pad (6).

8. The aircraft actuator disassembly device according to claim 3, characterized in that: A tension spring (23) is arranged in the housing (1); one end of the tension spring (23) is fixedly connected to the inner wall of the housing (1), and the other end is fixedly connected to an end of the clamping member (21) away from the rotating wheel (33).

9. The aircraft actuator disassembly device according to claim 5, characterized in that: One end of the propulsion shaft (41) away from the extension section (22) is fixedly connected to a handle (42), and one end of the propulsion shaft (41) away from the handle (42) is fixedly connected to a protrusion (43).

Images