Aircraft hoisting device

Abstract

The utility model relates to the technical field of hoisting tools, in particular to an aircraft hoisting device which comprises a left guide rail and a right guide rail, servo motors are fixedly installed at the ends of the guide rails, lead screws are fixedly installed at the tail ends of output shafts of the servo motors, and a supporting frame is connected to the two guide rails in a sliding mode. The lead screw penetrates through a side edge plate body of the supporting frame and is in threaded connection with the supporting frame, a clamping assembly is arranged on the supporting frame and comprises a left first air cylinder and a right first air cylinder which are fixedly installed on a top plate body of the supporting frame, a cross beam is arranged on telescopic shafts of the two first air cylinders, and a left vertical plate and a right vertical plate are fixedly installed on the bottom face of the cross beam; a second air cylinder is fixedly installed on a bottom plate body of the vertical plate, a clamping plate is arranged at the tail end of a telescopic shaft of the second air cylinder, and a lifting assembly is arranged on the supporting frame. According to the utility model, stable clamping operation is facilitated, shaking is not easy, and stable hoisting operation is facilitated.

Description

Technical Field

[0001] This utility model relates to the field of hoisting tools, and more specifically, to an aircraft hoisting device. Background Technology

[0002] Aircraft sling load technology is an indispensable part of the modern aviation field. It involves the safe and efficient loading of various equipment, cargo or weapons onto aircraft to meet different flight and combat requirements. With the continuous development of aviation technology, aircraft sling load technology is also constantly being innovated and improved to adapt to more complex and ever-changing combat environments and mission requirements.

[0003] While commercially available lifting devices, such as common gantry cranes, can perform lifting operations, they typically rely on steel cables for raising and lowering. These cables, often rope-like, have a significant swing amplitude. During lifting and movement, inertial forces can cause the lifted aircraft components to sway dramatically, affecting the stability of the lifting operation. Furthermore, during aircraft assembly, this swaying can lead to misalignment, impacting the assembly process. Therefore, we propose an aircraft lifting device. Utility Model Content

[0004] The purpose of this invention is to provide an aircraft hoisting device to address the deficiencies mentioned in the background art.

[0005] To achieve the above objectives, this utility model provides the following technical solution:

[0006] An aircraft hoisting device includes two symmetrical guide rails, a servo motor fixedly mounted at the end of each guide rail, a lead screw fixedly mounted at the end of the output shaft of each servo motor, a support frame slidably connected to the two guide rails, the lead screw passing through the side plate of the support frame and threadedly connected to the support frame, a clamping assembly provided on the support frame, the clamping assembly including two symmetrical first cylinders fixedly mounted on the top plate of the support frame, a crossbeam provided on the telescopic shaft of the two first cylinders, two symmetrical vertical plates fixedly mounted on the bottom surface of the crossbeams, a second cylinder fixedly mounted on the bottom plate of the vertical plates, and a clamping plate provided at the end of the telescopic shaft of the second cylinder.

[0007] Preferably, side frames are fixedly installed on both sides of the support frame, and the lead screw passes through the side frame and is threadedly connected to the side frame.

[0008] Preferably, a steel plate is fixedly installed at the end of the telescopic shaft of the first cylinder, and the crossbeam is fixedly installed on the bottom surface of the two steel plates.

[0009] Preferably, a rectangular plate is fixedly installed at the end of the telescopic shaft of the second cylinder, and the clamping plate is fixedly installed on the side of the rectangular plate.

[0010] Preferably, a first guide post is fixedly installed on the side of the rectangular plate, and a first guide sleeve is fixedly installed on the inner side of the vertical plate. The first guide sleeve is fitted onto the first guide post and is slidably connected to the first guide post.

[0011] Preferably, the support frame is provided with a lifting assembly, which includes a third cylinder fixedly installed on the top plate of the support frame. The end of the telescopic shaft of the third cylinder is provided with a fixed seat. A fourth cylinder is fixedly installed on the bottom surface of the fixed seat. A frame plate is fixedly installed on the end of the telescopic shaft of the fourth cylinder. A support plate is fixedly installed on the side of the frame plate. A fifth cylinder is fixedly installed on the support plate. The end of the telescopic shaft of the fifth cylinder is fixedly installed with a lifting plate.

[0012] Preferably, a sliding groove is provided on one side plate of the support frame, which is arranged in a vertical direction, and a slider is fixedly installed on the side of the fixed seat. The slider is located in the sliding groove and is slidably connected to the sliding groove.

[0013] Preferably, a second guide post is fixedly installed on the side of the frame plate, and a second guide sleeve is fixedly installed on the side plate of the fixing seat. The second guide sleeve is sleeved on the second guide post and slidably connected to the second guide post.

[0014] Compared with the prior art, the beneficial effects of this utility model are:

[0015] 1. This utility model achieves smooth sliding of the support frame on the guide rail by using a servo motor to drive the lead screw to rotate, thereby enabling adjustment of the lifting position. At the same time, the clamping component is designed with multi-stage cylinder linkage. The first cylinder pushes the crossbeam to move, and the second cylinder further drives the clamping plate to firmly clamp the aircraft or load, ensuring safety and stability during the lifting process. In addition, the sliding connection between the first guide post and the first guide sleeve enhances the guidance and stability of the clamping component during movement, achieving the effect of stable clamping and lifting.

[0016] 2. This utility model, through the setting of the lifting component, utilizes the multi-stage telescopic function of the third, fourth and fifth cylinders to realize the use of the lifting plate to support the bottom of the hoisted aircraft parts, making the hoisted aircraft parts more stable. Attached Figure Description

[0017] Figure 1 This is a schematic diagram of the overall structure of this utility model;

[0018] Figure 2This is a schematic diagram of the exploded structure of this utility model;

[0019] Figure 3 This is a partial structural schematic diagram of the present invention;

[0020] Figure 4 This is a schematic diagram of the clamping assembly of this utility model;

[0021] Figure 5 This is a schematic diagram of the structure of the lifting component of this utility model;

[0022] The meanings of the labels in the diagram are as follows:

[0023] 1. Guide rail; 10. Servo motor; 11. Lead screw;

[0024] 2. Support frame; 20. Slide rail; 21. Side frame;

[0025] 3. Clamping assembly; 30. First cylinder; 301. Steel plate; 31. Crossbeam; 32. Vertical plate; 33. Second cylinder; 34. Rectangular plate; 35. Clamping plate; 36. First guide post; 37. First guide sleeve;

[0026] 4. Lifting assembly; 40. Third cylinder; 41. Fixed base; 42. Slider; 43. Fourth cylinder; 44. Frame plate; 45. Support plate; 46. Fifth cylinder; 47. Lifting plate; 48. Second guide post; 49. Second guide sleeve. Detailed Implementation

[0027] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the protection scope of the present utility model.

[0028] Please see Figures 1-5 This utility model provides a technical solution: an aircraft hoisting device, including two symmetrical guide rails 1 on the left and right, a servo motor 10 fixedly installed at the end of the guide rail 1, a lead screw 11 fixedly installed at the end of the output shaft of the servo motor 10, the lead screw 11 is located inside the guide rail 1, a support frame 2 is slidably connected on the two guide rails 1, the lead screw 11 passes through the side plate of the support frame 2 and is threadedly connected to the support frame 2, so as to enable the support frame 2 to move left and right for position adjustment operation;

[0029] Specifically, the support frame 2 is equipped with a clamping assembly 3, which includes two symmetrical first cylinders 30 fixedly mounted on the top plate of the support frame 2. A crossbeam 31 is mounted on the telescopic shaft of the two first cylinders 30. Two symmetrical vertical plates 32 are fixedly mounted on the bottom surface of the crossbeam 31. A second cylinder 33 is fixedly mounted on the bottom plate of the vertical plates 32. A clamping plate 35 is mounted at the end of the telescopic shaft of the second cylinder 33. The operation of the first cylinders 30 drives the clamping plates 35 to move up and down, and the operation of the second cylinders 33 drives the two clamping plates 35 to perform clamping operations on aircraft parts.

[0030] In this embodiment, side frames 21 are fixedly installed on both sides of the support frame 2. The lead screw 11 passes through the side frame 21 and is threadedly connected to the side frame 21, which enhances the stability of the support frame 2 sliding on the guide rail 1 and also ensures the accuracy and reliability of the lead screw 11 when driving the support frame 2 to move.

[0031] Specifically, a steel plate 301 is fixedly installed at the end of the telescopic shaft of the first cylinder 30, and a crossbeam 31 is fixedly installed on the bottom surface of the two steel plates 301 by multiple fastening bolts; a rectangular plate 34 is fixedly installed at the end of the telescopic shaft of the second cylinder 33, and a clamping plate 35 is fixedly installed on the side of the rectangular plate 34 by multiple fastening bolts, which facilitates the fixed installation operation.

[0032] Furthermore, a first guide post 36 is fixedly installed on the side of the rectangular plate 34, and a first guide sleeve 37 is fixedly installed on the inner side of the vertical plate 32. The first guide sleeve 37 is fitted onto the first guide post 36 and slidably connected to the first guide post 36, thereby enhancing the guidance and stability of the clamping assembly 3 during movement.

[0033] In addition, a lifting assembly 4 is provided on the support frame 2. The lifting assembly 4 includes a third cylinder 40 fixedly installed on the top plate of the support frame 2. A fixed seat 41 is provided at the end of the telescopic shaft of the third cylinder 40. A fourth cylinder 43 is fixedly installed on the bottom surface of the fixed seat 41. A frame plate 44 is fixedly installed at the end of the telescopic shaft of the fourth cylinder 43. A support plate 45 is fixedly installed on the side of the frame plate 44. A fifth cylinder 46 is fixedly installed on the support plate 45. A lifting plate 47 is fixedly installed at the end of the telescopic shaft of the fifth cylinder 46. This ensures that when in use, after the clamping plate 35 clamps the aircraft parts and suspends them in mid-air, the lifting plate 47 is used to press against the bottom of the aircraft parts to achieve a further stable support effect.

[0034] It is worth noting that a vertically oriented slide groove 20 is provided on one side plate of the support frame 2, and a slider 42 is fixedly installed on the side of the fixed seat 41. The slider 42 is located in the slide groove 20 and is slidably connected to the slide groove 20, making the fixed seat 41 more stable and smooth when moving up and down.

[0035] It is worth noting that a second guide post 48 is fixedly installed on the side of the frame plate 44, and a second guide sleeve 49 is fixedly installed on the side plate of the fixed seat 41. The second guide sleeve 49 is fitted onto the second guide post 48 and slidably connected to the second guide post 48, ensuring the stability and accuracy of the frame plate 44 and the lifting plate 47 during the lifting process.

[0036] Finally, it should be noted that the servo motor 10, the first cylinder 30, the second cylinder 33, the third cylinder 40, the fourth cylinder 43, and the fifth cylinder 46 involved in this utility model are all general standard parts or parts known to those skilled in the art. Their structures and principles can be learned by those skilled in the art through technical manuals or conventional experimental methods. In the idle space of this device, all the above-mentioned electrical components, which refer to power elements, electrical components, and the adapted controller and power supply, are connected by wires. The specific connection methods should refer to the working principle of this utility model. The electrical connections between each electrical component are completed in the order of operation. The detailed connection methods are all technologies known in the art.

[0037] When using the aircraft hoisting device of this utility model, firstly, the servo motor 10 is started, and its output shaft drives the lead screw 11 to rotate. Since the lead screw 11 is threadedly connected to the support frame 2, the support frame 2 will move left and right along the guide rail 1 to make preliminary position adjustment.

[0038] After the support frame 2 moves to the predetermined position, the first cylinder 30 in the clamping assembly 3 is activated. The telescopic shaft of the first cylinder 30 pushes the steel plate 301 and the crossbeam 31 downward until the vertical plate 32 approaches the aircraft part to be lifted. Then, the second cylinder 33 is activated, and its telescopic shaft pushes the rectangular plate 34 and the clamping plate 35 to move inward to clamp the aircraft part.

[0039] After clamping and fixing, the telescopic shaft of the first cylinder 30 shortens, causing the aircraft part clamped by the clamping plate 35 to move upward to the corresponding height. Then, the third cylinder 40 in the lifting assembly 4 is activated. The telescopic shaft of the third cylinder 40 pushes the fixing seat 41 and the fourth cylinder 43 downward to the appropriate position. When the telescopic shaft of the fourth cylinder 43 extends and pushes the frame plate 44 and the lifting plate 47 close to the bottom of the aircraft part, the fifth cylinder 46 is activated. Its telescopic shaft extends and pushes the lifting plate 47 against the bottom of the aircraft part to achieve further support.

[0040] Finally, the servo motor 10 is started to drive the support frame 2 and the clamped aircraft parts to the loading position for assembly.

[0041] The foregoing has shown and described the basic principles, main features, and advantages of this utility model. Those skilled in the art should understand that this utility model is not limited to the above embodiments. The embodiments and descriptions in the specification are merely preferred examples and are not intended to limit the utility model. Various changes and modifications can be made to this utility model without departing from its spirit and scope, and all such changes and modifications fall within the scope of the claimed utility model. The scope of protection of this utility model is defined by the appended claims and their equivalents.

Claims

1. An aircraft loading device comprising two mutually symmetrical rails (1) on the left and right, characterized in that: The end of the guide rail (1) is fixedly installed with a servo motor (10), the output shaft end of the servo motor (10) is fixedly installed with a lead screw (11), two guide rails (1) are slidably connected with a support frame (2), the lead screw (11) penetrates through the side plate body of the support frame (2) and is threadedly connected with the support frame (2), the support frame (2) is provided with a clamping assembly (3), the clamping assembly (3) comprises two first air cylinders (30) which are symmetrically arranged and fixedly installed on the top plate body of the support frame (2), a cross beam (31) is arranged on the telescopic shaft of the two first air cylinders (30), two vertical plates (32) which are symmetrically arranged are fixedly installed on the bottom surface of the cross beam (31), a second air cylinder (33) is fixedly installed on the bottom plate body of the vertical plate (32), and a clamping plate (35) is arranged at the end of the telescopic shaft of the second air cylinder (33).

2. The aircraft load-hoist device of claim 1, wherein: The both side plate bodies of the support frame (2) are fixedly installed with side frames (21), the lead screw (11) penetrates through the side frames (21) and is threadedly connected with the side frames (21).

3. The aircraft load-hoist device of claim 1, wherein: The end of the telescopic shaft of the first air cylinder (30) is fixedly installed with a steel plate (301), and the cross beam (31) is fixedly installed on the bottom surface of the two steel plates (301).

4. The aircraft load-hoist device of claim 1, wherein: The end of the telescopic shaft of the second air cylinder (33) is fixedly installed with a rectangular plate (34), and the clamping plate (35) is fixedly installed on the side surface of the rectangular plate (34).

5. The aircraft load-hoist device of claim 4, wherein: A first guide column (36) is fixedly installed on the side surface of the rectangular plate (34), a first guide sleeve (37) is fixedly installed on the inner side surface of the vertical plate (32), and the first guide sleeve (37) is sleeved on the first guide column (36) and is slidably connected with the first guide column (36).

6. The aircraft load-hoist device of claim 1, wherein: The support frame (2) is provided with a lifting assembly (4), the lifting assembly (4) comprises a third air cylinder (40) which is fixedly installed on the top plate body of the support frame (2), a fixing seat (41) is arranged at the end of the telescopic shaft of the third air cylinder (40), a fourth air cylinder (43) is fixedly installed on the bottom surface of the fixing seat (41), a frame plate (44) is fixedly installed at the end of the telescopic shaft of the fourth air cylinder (43), a supporting plate (45) is fixedly installed on the side surface of the frame plate (44), a fifth air cylinder (46) is fixedly installed on the supporting plate (45), and a lifting plate (47) is fixedly installed at the end of the telescopic shaft of the fifth air cylinder (46).

7. The aircraft load-hoist device of claim 6, wherein: A sliding groove (20) which is arranged along the vertical direction is arranged on one side plate body of the support frame (2), a sliding block (42) is fixedly installed on the side surface of the fixing seat (41), and the sliding block (42) is located in the sliding groove (20) and is slidably connected with the sliding groove (20).

8. The aircraft load-hoist device of claim 7, wherein: A second guide column (48) is fixedly installed on the side surface of the frame plate (44), a second guide sleeve (49) is fixedly installed on the side plate body of the fixing seat (41), and the second guide sleeve (49) is sleeved on the second guide column (48) and is slidably connected with the second guide column (48).

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