An aircraft wing jacking apparatus

Abstract

The application relates to the field of aircraft maintenance technology, in particular to an aircraft wing jacking device which comprises a jacking device main body, a liftable threaded rod is arranged on the jacking device main body, a fixed block is fixedly connected to the top of the threaded rod, a top block is inserted on the fixed block, a plug-in block is fixedly connected to the top block, the plug-in block is cuboid, a plug-in groove for inserting the plug-in block is arranged on the fixed block, and a locking assembly for quickly locking the plug-in block is arranged on the fixed block. The application has the effect of improving the problems of low installation efficiency caused by the connection of the jacking device with the top block through the threaded rod and the safety hidden danger of unreliable connection.

Description

Technical Field

[0001] This utility model relates to the field of aircraft maintenance technology, and in particular to an aircraft wing lifting device. Background Technology

[0002] During aircraft wing maintenance, it is often necessary to lift the wing to a specific height for inspection or repair. Existing lifting equipment connects to the lifting block via threaded rods, requiring each thread to be tightened individually for installation, which is inefficient. Furthermore, relying solely on threaded connections makes the lifting block prone to rotation due to vibration or load changes, leading to loosening of the connection and posing a safety hazard. Utility Model Content

[0003] In order to improve the problem that the connection between the lifting device and the top block via the threaded rod results in low installation efficiency and unreliable connection that poses a safety hazard, this application provides an aircraft wing lifting device.

[0004] The aircraft wing lifting device provided in this application adopts the following technical solution:

[0005] An aircraft wing lifting device includes a lifting device body, on which a liftable threaded rod is provided. A fixing block is fixedly connected to the top of the threaded rod. A top block is inserted into the fixing block. An insertion block is fixedly connected to the top block. The insertion block is cubic in shape. An insertion slot for inserting the insertion block is provided on the fixing block. A locking component for quickly locking the insertion block is provided on the fixing block.

[0006] Preferably, the lifting device body includes a fixed pipe, a fixed bearing, a connecting ring plate, a threaded sleeve, a handle, a limiting block, and supporting legs. The fixed bearing is inserted into the fixed pipe, and the outer ring of the fixed bearing is connected to the fixed pipe by bolts. The connecting ring plate is fixedly connected to the inner ring of the fixed bearing, and the axis of the connecting ring plate is collinear with the axis of the fixed bearing. The threaded rod passes through the fixed bearing, and the threaded sleeve is threaded onto the threaded rod. The threaded sleeve is connected to the connecting ring plate by bolts. The handle is fixedly connected to the threaded sleeve. The limiting block is fixedly connected to the inner wall of the fixed pipe, and the threaded rod has a limiting groove for the limiting block to slide. The supporting legs are fixedly connected to the fixed pipe, and several supporting legs are evenly arranged along the circumference of the fixed pipe.

[0007] Preferably, the locking assembly includes a mounting cylinder, a cylinder cover, a locking rod, a sliding plate, a spring, and a lever. The mounting cylinder is connected to a fixing block, and the cylinder cover is connected to the opening of the mounting cylinder. The locking rod passes through the cylinder cover, the mounting cylinder, and the fixing block in sequence. The insertion block has a locking hole for inserting the locking rod. The axis of the locking rod is collinear with the axis of the mounting cylinder. The sliding plate is fixedly connected to the rod body of the locking rod located inside the mounting cylinder. The side wall of the sliding plate slides against the inner wall of the mounting cylinder. The spring is sleeved on the rod body of the locking rod located inside the mounting cylinder. One end of the spring abuts against the sliding plate, and the other end abuts against the cylinder cover. The lever is connected to the end of the locking rod that is not inserted into the mounting cylinder.

[0008] Preferably, a reinforcing rod is fixedly connected to the support leg, and the reinforcing rod is located between adjacent support legs.

[0009] Preferably, a rubber gasket is adhered to the top block.

[0010] In summary, this application includes the following beneficial technical effects:

[0011] This utility model provides an aircraft wing lifting device. By setting a fixing block on a threaded rod and a locking component on the fixing block, and setting a plug-in block on the top block, the plug-in block is inserted into the fixing block during installation and quickly locked by the locking component. The plug-in design replaces the threaded screwing, achieving "one-plug-and-lock". This improves the installation efficiency of the top block on the lifting device. In addition, the plug-in block is cubic in shape to avoid rotation. Thus, it achieves the effect of improving the problem of low installation efficiency and unreliable connection that poses safety hazards when the lifting device is connected to the top block by a threaded rod. Attached Figure Description

[0012] Figure 1 This is a schematic diagram of the structure of the aircraft wing lifting device in the embodiments of this application;

[0013] Figure 2 This is a schematic diagram illustrating the fixed bearing in an embodiment of this application;

[0014] Figure 3 This is a schematic diagram illustrating the locking component in an embodiment of this application.

[0015] Explanation of reference numerals in the attached drawings: 1. Main body of the lifting equipment; 11. Fixed pipe; 12. Fixed bearing; 13. Connecting ring plate; 14. Threaded sleeve; 15. Handle; 16. Limiting block; 17. Support leg; 171. Reinforcing rod; 2. Threaded rod; 3. Fixed block; 4. Top block; 41. Insertion block; 42. Rubber pad; 5. Locking assembly; 51. Mounting cylinder; 52. Cylinder cover; 53. Locking rod; 54. Slide plate; 55. Spring; 56. Pulley. Detailed Implementation

[0016] To enable those skilled in the art to better understand the present invention, the solutions in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort should fall within the protection scope of the present invention.

[0017] In the description of this utility model, it should be noted that the terms "center," "upper," "lower," "left," "right," "vertical," "horizontal," "inner," and "outer," etc., indicating the orientation or positional relationship, are based on the orientation or positional relationship shown in the accompanying drawings and are only for the convenience of describing this utility model and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation or specific orientation structure and operation, and therefore should not be construed as a limitation of this utility model; the terms "first," "second," and "third" are used for descriptive purposes only and should not be construed as indicating or implying relative importance. In addition, unless otherwise explicitly specified and limited, the terms "installed," "connected," and "linked" should be interpreted broadly, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium; it can be a connection within two components. For those skilled in the art, the specific meaning of the above terms in this utility model can be understood according to the specific circumstances.

[0018] This application discloses an aircraft wing lifting device. (Refer to...) Figure 1 , Figure 2 and Figure 3 The aircraft wing lifting device includes a lifting device body 1, a liftable threaded rod 2 on the lifting device body 1, a fixing block 3 fixedly connected to the top of the threaded rod 2, a top block 4 inserted into the fixing block 3, and a plug-in block 41 fixedly connected to the top block 4. The plug-in block 41 is cubic in shape. The fixing block 3 has a plug-in slot for the plug-in block 41 to be inserted. The fixing block 3 is provided with a locking component 5 for quickly locking the plug-in block 41.

[0019] The main body 1 of the lifting equipment includes a fixed pipe 11, a fixed bearing 12, a connecting ring plate 13, a threaded sleeve 14, a handle 15, a limiting block 16, and a support leg 17. The fixed bearing 12 is inserted into the fixed pipe 11, and the outer ring of the fixed bearing 12 is connected to the fixed pipe 11 by bolts. The connecting ring plate 13 is fixedly connected to the inner ring of the fixed bearing 12. The axis of the connecting ring plate 13 is collinear with the axis of the fixed bearing 12. The threaded rod 2 passes through the fixed bearing 12. The threaded sleeve 14 is threaded onto the threaded rod 2. The threaded sleeve 14 is connected to the connecting ring plate 13 by bolts. The handle 15 is fixedly connected to the threaded sleeve 14. The limiting block 16 is fixedly connected to the inner wall of the fixed pipe 11. The threaded rod 2 has a limiting groove for the limiting block 16 to slide. The support leg 17 is fixedly connected to the fixed pipe 11, and several support legs 17 are evenly arranged along the circumference of the fixed pipe 11.

[0020] The locking assembly 5 includes a mounting cylinder 51, a cylinder cover 52, a locking rod 53, a sliding plate 54, a spring 55, and a lever 56. The mounting cylinder 51 is connected to the fixing block 3, and the cylinder cover 52 is connected to the opening of the mounting cylinder 51. The locking rod 53 passes through the cylinder cover 52, the mounting cylinder 51, and the fixing block 3 in sequence. The insertion block 41 has a locking hole for the locking rod 53 to be inserted. The axis of the locking rod 53 is collinear with the axis of the mounting cylinder 51. The sliding plate 54 is fixedly connected to the rod of the locking rod 53 located inside the mounting cylinder 51. The side wall of the sliding plate 54 slides against the inner wall of the mounting cylinder 51. The spring 55 is sleeved on the rod of the locking rod 53 located inside the mounting cylinder 51. One end of the spring 55 abuts against the sliding plate 54, and the other end abuts against the cylinder cover 52. The lever 56 is connected to the end of the locking rod 53 that is not inserted into the mounting cylinder 51.

[0021] A reinforcing rod 171 is fixedly connected to the support leg 17, and the reinforcing rod 171 is located between adjacent support legs 17.

[0022] A rubber gasket 42 is adhered to the top block 4.

[0023] The implementation principle of an aircraft wing lifting device according to an embodiment of this application is as follows: When installing the top block 4, simply pull the lever 56 outward to make the locking rod 53 exit the insertion slot on the fixing block 3, so as to avoid the locking rod 53 affecting the insertion block 41. Then, insert the insertion block 41 on the top block 4 into the insertion slot of the fixing block 3. After that, release the lever 56, and use the spring 55 to push the slide plate 54 to drive the locking rod 53 into the locking hole of the insertion block 41 to fix the top block 4.

[0024] When raising or lowering the top block 4, manually turn the handle 15 to rotate the threaded sleeve 14. The threaded rod 2 cannot rotate due to the limiting effect of the limiting block 16 and the limiting groove. Under the limiting and guiding effect of the limiting block 16, it can move up and down, thereby driving the top block 4 to rise or fall.

[0025] Finally, it should be noted that the above description is only a preferred embodiment of this utility model, and the protection scope of this utility model is not limited to the above embodiments. All technical solutions within the scope of this utility model's concept are within the protection scope of this utility model. It should be pointed out that for those skilled in the art, any improvements and modifications made without departing from the principle of this utility model should also be considered within the protection scope of this utility model.

Claims

1. An aircraft wing lifting device, characterized in that: The device includes a lifting device body (1), on which a liftable threaded rod (2) is provided. A fixing block (3) is fixedly connected to the top of the threaded rod (2). A top block (4) is inserted into the fixing block (3). A plug-in block (41) is fixedly connected to the top block (4). The plug-in block (41) is cubic in shape. A plug-in slot for inserting the plug-in block (41) is provided on the fixing block (3). A locking component (5) for quickly locking the plug-in block (41) is provided on the fixing block (3).

2. The aircraft wing lifting device according to claim 1, characterized in that: The main body (1) of the lifting equipment includes a fixed pipe (11), a fixed bearing (12), a connecting ring plate (13), a threaded sleeve (14), a handle (15), a limiting block (16), and a support leg (17). The fixed bearing (12) is inserted into the fixed pipe (11). The outer ring of the fixed bearing (12) is connected to the fixed pipe (11) by bolts. The connecting ring plate (13) is fixedly connected to the inner ring of the fixed bearing (12). The axis of the connecting ring plate (13) is collinear with the axis of the fixed bearing (12). The threaded rod (2) The threaded sleeve (14) passes through the fixed bearing (12) and is threaded onto the threaded rod (2). The threaded sleeve (14) is connected to the connecting ring plate (13) by bolts. The handle (15) is fixedly connected to the threaded sleeve (14). The limiting block (16) is fixedly connected to the inner wall of the fixed tube (11). The threaded rod (2) has a limiting groove for the limiting block (16) to slide. The support leg (17) is fixedly connected to the fixed tube (11). Several support legs (17) are evenly arranged along the circumference of the fixed tube (11).

3. The aircraft wing lifting device according to claim 1, characterized in that: The locking assembly (5) includes a mounting cylinder (51), a cylinder cover (52), a locking rod (53), a sliding plate (54), a spring (55), and a lever (56). The mounting cylinder (51) is connected to the fixing block (3), and the cylinder cover (52) is connected to the opening of the mounting cylinder (51). The locking rod (53) passes through the cylinder cover (52), the mounting cylinder (51), and the fixing block (3) in sequence. The insertion block (41) has a locking hole for inserting the locking rod (53). The axis of the locking rod (53) is perpendicular to the mounting cylinder (54). The axes of the mounting cylinder (51) are collinear. The sliding plate (54) is fixedly connected to the rod of the locking rod (53) located inside the mounting cylinder (51). The side wall of the sliding plate (54) slides against the inner wall of the mounting cylinder (51). The spring (55) is sleeved on the rod of the locking rod (53) located inside the mounting cylinder (51). One end of the spring (55) abuts against the sliding plate (54), and the other end abuts against the cylinder cover (52). The lever (56) is connected to the end of the locking rod (53) that is not inserted into the mounting cylinder (51).

4. The aircraft wing lifting device according to claim 2, characterized in that: A reinforcing rod (171) is fixedly connected to the supporting leg (17), and the reinforcing rod (171) is located between adjacent supporting legs (17).

5. The aircraft wing lifting device according to claim 1, characterized in that: A rubber pad (42) is adhered to the top block (4).

Images