Aircraft component assembly lifting tools and aircraft maintenance equipment

Abstract

This disclosure provides a lifting device for assembling aircraft components and aircraft maintenance equipment. The lifting device for assembling aircraft components includes a lifting device and a clamping and locking structure. The clamping and locking structure includes a mounting frame, an upper pressure plate, and a lower support rod. The mounting frame is mounted on the lifting chain of the lifting device, and an installation opening is formed on the mounting frame. The lower support rod is used to penetrate the curved component and is placed horizontally in the installation opening. Each end of the lower support rod is detachably connected to the mounting frame. The upper pressure plate is lifted and positioned in the installation opening and above the lower support rod. Each end of the upper pressure plate is connected to the corresponding end of the lower support rod through a locking assembly. When the locking assembly is locked, the upper pressure plate will approach the curved component and press against the outer surface of the curved component, so that the upper pressure plate and the lower support rod can jointly clamp and restrict the displacement of the curved component, thereby improving the installation reliability of the curved component and the clamping and locking structure.

Description

Technical Field

[0001] This disclosure relates to the technical field of aircraft maintenance, and in particular to a lifting tool for assembling aircraft components and aircraft maintenance equipment. Background Technology

[0002] When assembling aircraft, due to the typically large weight of aircraft components, most manufacturers use lifting devices, such as those disclosed in Chinese patent document CN216272665U, to lift and assemble these components. However, due to the streamlined structural design of the outer surface of aircraft components, the outer surface is often constructed using only cylindrical or rod-shaped curved components to reduce wind resistance. Because of the structural design of the aforementioned lifting devices, the lifting ropes are difficult to securely fix to the curved components or the outer surface of the aircraft. This can cause the aircraft components to loosen during lifting, potentially leading to accidents. Utility Model Content

[0003] The purpose of this disclosure is to overcome the shortcomings of the prior art and provide a lifting device and aircraft maintenance equipment for assembling aircraft components that has a better clamping effect on curved components.

[0004] The purpose of this disclosure is achieved through the following technical solution:

[0005] A lifting device for assembling aircraft parts, comprising:

[0006] A lifting device, which is used to fix the device to the bracket;

[0007] The aircraft component assembly lifting tool also includes a clamping and locking structure;

[0008] The clamping and locking structure includes a mounting frame, an upper pressure plate, and a lower support rod. The mounting frame is mounted on the lifting chain of the hoist, and an installation opening is formed on the mounting frame. The lower support rod is used to pass through the curved component and is placed horizontally within the installation opening. Each end of the lower support rod is detachably connected to the mounting frame. The upper pressure plate is lifted and positioned within the installation opening and above the lower support rod. Each end of the upper pressure plate is connected to the corresponding end of the lower support rod through a locking assembly, and the upper pressure plate is used to press against the outer surface of the curved component when the locking assembly is locked.

[0009] In some embodiments, the upper pressure plate is provided with a plurality of damping protrusions, which are arranged facing the lower support rod; the damping protrusions are used to abut against the outer surface of the curved component.

[0010] In some embodiments, the damping protrusions are toothed or cylindrical.

[0011] In some embodiments, the upper pressure plate and the damping protrusion are integrally formed.

[0012] In some embodiments, the upper pressure plate has an arc-shaped lower surface for fitting and adapting to the outer surface of the curved component; and / or,

[0013] The upper pressure plate has an elastic sheet structure.

[0014] In some embodiments, the mounting bracket has two vertical lifting holes, and each end of the upper pressure plate passes through one of the corresponding vertical lifting holes.

[0015] In some embodiments, the mounting bracket has two mounting holes, and each end of the lower support rod passes through one of the corresponding mounting holes.

[0016] In some embodiments, the locking assembly includes a bolt and a nut, each end of the upper pressure plate has a first through hole, each end of the lower support rod has a second through hole, and the bolt passes through the corresponding first through hole and the corresponding second through hole in sequence and is threaded to the nut.

[0017] In some embodiments, the lifting device is a hand-operated hoist; and / or,

[0018] The outer surface of the mounting bracket has a first adhesive layer; and / or,

[0019] The outer surface of the upper pressure plate has a second adhesive layer.

[0020] An aircraft maintenance device includes a lifting device for assembling aircraft components according to any of the above embodiments.

[0021] Compared with the prior art, this disclosure has at least the following advantages:

[0022] The aforementioned aircraft component assembly lifting device, after the lower support rod penetrates the interior of the curved component, allows each end of the lower support rod, which is horizontally positioned within the mounting opening, to be detachably connected to the mounting frame, thus confining a portion of the curved component within the mounting opening. Furthermore, because the upper pressure plate, located above the lower support rod, is raised and lowered within the mounting opening, and each end of the upper pressure plate is connected to the corresponding end of the lower support rod via a locking assembly, when the locking assembly is tightened, the upper pressure plate approaches the curved component and presses against its outer surface. This allows the upper pressure plate and the lower support rod to jointly clamp and restrict the displacement of the curved component, thereby improving the reliability of the installation between the curved component and the clamping and locking structure. Thus, after the clamping and locking structure is installed on the lifting chain of the hoist, the aircraft component can be lifted more smoothly by the hoist, reducing the occurrence of accidents. Attached Figure Description

[0023] To more clearly illustrate the technical solutions of the embodiments of this disclosure, the accompanying drawings used in the embodiments will be briefly described below. It should be understood that the following drawings only show some embodiments of this disclosure and should not be regarded as a limitation of the scope. For those skilled in the art, other related drawings can be obtained based on these drawings without creative effort.

[0024] Figure 1 This is a structural schematic diagram of the working state of a lifting device for assembling aircraft components according to an embodiment of the present disclosure;

[0025] Figure 2 for Figure 1 A transverse sectional view of the clamping and locking structure of the aircraft component assembly hoist shown;

[0026] Figure 3 for Figure 2 The enlarged view shown at point A in the middle;

[0027] Figure 4 for Figure 1 A vertical sectional view of the clamping and locking structure of the aircraft component assembly hoist shown;

[0028] Figure 5 for Figure 2 A magnified view of the area shown at point B in the middle.

[0029] Figure label:

[0030] 10. Aircraft components; 20. Curved surface components; 30. Brackets;

[0031] 100. Lifting device; 110. Lifting chain;

[0032] 200. Clamping and locking structure; 210. Mounting bracket; 2101. Lifting vertical hole; 2102. Assembly hole; 2103. Mounting opening; 220. Upper pressure plate; 2210. Damping protrusion; 2201. Arc-shaped lower surface; 2202. First through hole; 230. Lower support rod; 2301. Second through hole;

[0033] 300, Locking assembly; 310, Bolt; 3110, Column part; 3120, Cap part; 320, Nut. Detailed Implementation

[0034] To facilitate understanding of this disclosure, a more complete description will be given below with reference to the accompanying drawings, which illustrate preferred embodiments of the present disclosure. However, this disclosure can be implemented in many different forms and is not limited to the embodiments described herein. Rather, these embodiments are provided to provide a more thorough and complete understanding of the disclosure.

[0035] It should be noted that when an element is referred to as being "fixed to" another element, it can be directly attached to the other element or there may be an intervening element. When an element is referred to as being "connected to" another element, it can be directly connected to the other element or there may be an intervening element. The terms "vertical," "horizontal," "left," "right," and similar expressions used herein are for illustrative purposes only and do not represent the only possible implementation.

[0036] Unless otherwise defined, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this disclosure belongs. The terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of this disclosure. The term "and / or" as used herein includes any and all combinations of one or more of the associated listed items.

[0037] To better understand the technical solutions and beneficial effects of this disclosure, the following detailed description is provided in conjunction with specific embodiments:

[0038] Please see Figure 1 and Figure 2 One embodiment of the aircraft component assembly lifting device includes a lifting device 100 and a clamping and locking structure 200. The lifting device 100 is fixedly mounted on a bracket 30. The clamping and locking structure 200 includes a mounting frame 210, an upper pressure plate 220, and a lower support rod 230. The mounting frame 210 is mounted on the lifting chain 110 of the lifting device 100, and an installation opening 2103 is formed on the mounting frame 210. The lower support rod 230 is used to pass through the curved component 20 and is placed horizontally in the installation opening 2103. Each end of the lower support rod 230 is detachably connected to the mounting frame 210. The upper pressure plate 220 is raised and lowered in the installation opening 2103 and is located above the lower support rod 230. Each end of the upper pressure plate 220 is connected to the corresponding end of the lower support rod 230 through a locking assembly 300. The upper pressure plate 220 is used to press against the outer surface of the curved component 20 when the locking assembly 300 is locked. Specifically, the curved surface component 20 is a cylindrical component, and the lower support rod 230 is used to penetrate the inner cylinder of the cylindrical component; or, the curved surface component 20 is a round rod component, and the lower support rod 230 is used to penetrate the inner rod of the round rod component.

[0039] It is understood that after the lower support rod 230 penetrates the interior of the curved component 20, by making each end of the lower support rod 230, which is horizontally placed in the mounting opening 2103, detachably connected to the mounting bracket 210, a portion of the curved component 20 can be confined within the mounting opening 2103. Furthermore, because the upper pressure plate 220, located above the lower support rod 230, is vertically positioned within the mounting opening 2103, and each end of the upper pressure plate 220 is connected to the corresponding end of the lower support rod 230 via a locking assembly 300, when the locking assembly 300 is locked, the upper pressure plate 220 will approach the curved component 20 and press against its outer surface. This allows the upper pressure plate 220 and the lower support rod 230 to jointly clamp and restrict the displacement of the curved component 20, thereby improving the reliability of the installation between the curved component 20 and the clamping and locking structure 200. Thus, after the clamping and locking structure 200 is installed on the lifting chain 110 of the hoist 100, the aircraft component 10 can be lifted more smoothly by the hoist 100, thereby reducing the occurrence of accidents.

[0040] Please see Figure 2 and Figure 3 In some embodiments, the upper pressure plate 220 is provided with a plurality of damping protrusions 2210, which are arranged facing the lower support rod 230; the damping protrusions 2210 are used to abut against the outer surface of the curved member 20. It can be understood that since the plurality of damping protrusions 2210 provided on the upper pressure plate 220 are arranged facing the lower support rod 230, when the locking assembly 300 is locked, the upper pressure plate 220 will approach the curved member 20, and the damping protrusions 2210 abut against the outer surface of the curved member 20, thereby increasing the friction between the upper pressure plate 220 and the outer surface of the curved member 20, and further improving the reliability of the installation of the curved member 20 and the clamping and locking structure 200. Specifically, the damping protrusion 2210 can be in the shape of a tooth, a cylinder, etc. That is, the damping protrusion 2210 can be in various shapes such as a tooth-shaped protrusion and a cylindrical protrusion. This is only an example and is not intended to limit the scope of protection of this disclosure.

[0041] Please see Figure 2 In some embodiments, the upper pressure plate 220 and the damping protrusion 2210 are integrally molded structures. It can be understood that the upper pressure plate 220 and the damping protrusion 2210 are integrally molded rubber structures, resulting in a compact structure and greater durability.

[0042] Please see Figure 4In some embodiments, the upper pressure plate 220 has an arc-shaped lower surface 2201, which is used to adhere to and adapt to the outer surface of the curved component 20. It can be understood that because the upper pressure plate 220 has an arc-shaped lower surface 2201, by adhering to and adapting the arc-shaped lower surface 2201 to the outer surface of the curved component 20, the contact area between the upper pressure plate 220 and the outer surface of the curved component 20 can be further increased, thereby further improving the secure installation of the curved component 20 and the clamping and locking structure 200.

[0043] Please see Figure 4 In some embodiments, the upper pressure plate 220 is an elastic sheet structure. It can be understood that, since the upper pressure plate 220 is an elastic sheet structure, after the upper pressure plate 220 presses against the outer surface of the curved member 20, as the locking assembly 300 continuously tightens, the upper pressure plate 220 can deform and adapt to the outer surface of the curved member 20, thereby enabling the upper pressure plate 220 to adapt to the outer surface of the curved member 20 with different curvatures.

[0044] Please see Figures 4 to 5 In some embodiments, the mounting bracket 210 has two vertical lifting holes 2101, and each end of the upper pressure plate 220 is respectively disposed through one of the corresponding vertical lifting holes 2101. It can be understood that since each end of the upper pressure plate 220 is respectively disposed through one of the corresponding vertical lifting holes 2101, each end of the upper pressure plate 220 can move along the vertical lifting hole 2101 under the interference of the hole wall of the vertical lifting hole 2101, so that the upper pressure plate 220 can be raised and lowered smoothly.

[0045] Please see Figure 3 In some embodiments, the mounting bracket 210 has two mounting holes 2102, and each end of the lower support rod 230 passes through a corresponding mounting hole 2102. It can be understood that since each end of the lower support rod 230 passes through a corresponding mounting hole 2102, it facilitates the installation of the lower support rod 230 onto the mounting bracket 2100 after it passes through the curved component 20, making assembly and disassembly convenient.

[0046] Please see Figure 3 and Figure 5In some embodiments, the locking assembly 300 includes a bolt 310 and a nut 320. Each end of the upper pressure plate 220 has a first through hole 2202, and each end of the lower support rod 230 has a second through hole 2301. The bolt 310 passes through the corresponding first through hole 2202 and the corresponding second through hole 2301 in sequence and is threaded to the nut 320. It can be understood that by having the cylindrical portion 3110 of the bolt 310 pass through the corresponding first through hole 2202 and the corresponding second through hole 2301 in sequence and be threaded to the nut 320, the cap portion 3120 of the bolt 310 abuts against the upper pressure plate 220, thereby pushing the upper pressure plate 220 closer to the lower support rod 230. This allows the upper pressure plate 220 and the lower support rod 230 to jointly clamp and restrict the displacement of the curved component 20, thereby improving the reliability of the installation between the curved component 20 and the clamping and locking structure 200. Specifically, the cap body 3120 and the column body 3110 are integrally formed structures.

[0047] Please see Figure 1 In some embodiments, the lifting device 100 is a hand-operated chain hoist. It is understood that the lifting device 100 is a hand-operated chain hoist, which is used to hang on the bracket 30, and the lifting chain 110 of the hand-operated chain hoist is fixedly connected to the mounting frame 210, thereby enabling the lifting of the clamping and locking structure 200 and the aircraft component 10 via the lifting chain 110. The hand-operated chain hoist can adopt a conventional structure, which will not be described in detail here. Of course, the lifting device 100 is not limited to using a hand-operated chain hoist, and those skilled in the art can make other choices.

[0048] In some embodiments, the outer surface of the mounting bracket 210 has a first adhesive layer. It is understood that because the outer surface of the mounting bracket 210 has a first adhesive layer, wear during use can be reduced, making the mounting bracket 210 more durable.

[0049] In some embodiments, the outer surface of the upper pressure plate 220 has a second adhesive layer. It is understood that because the lower support rod 230 of the pressure plate has a second adhesive layer, wear on the upper pressure plate 220 during use can be reduced, making it more durable.

[0050] This disclosure also provides an aircraft maintenance device, including a lifting device for assembling aircraft components according to any of the above embodiments. It is understood that by applying the lifting device for assembling aircraft components of this disclosure to an aircraft maintenance device, after the lower support rod 230 penetrates the interior of the curved member 20, by detachably connecting each end of the lower support rod 230, which is transversely positioned within the mounting opening 2103, to the mounting bracket 210, a portion of the curved member 20 can be confined within the mounting opening 2103. Furthermore, because the upper pressure plate 220, located above the lower support rod 230, is vertically positioned within the mounting opening 2103, and each end of the upper pressure plate 220 is connected to the corresponding end of the lower support rod 230 via a locking assembly 300, when the locking assembly 300 is locked, the upper pressure plate 220 will approach the curved component 20 and press against its outer surface. This allows the upper pressure plate 220 and the lower support rod 230 to jointly clamp and restrict the displacement of the curved component 20, thereby improving the reliability of the installation between the curved component 20 and the clamping and locking structure 200. Thus, after the clamping and locking structure 200 is installed on the lifting chain 110 of the hoist 100, the aircraft component 10 can be lifted more smoothly by the hoist 100, reducing the occurrence of accidents.

[0051] Compared with the prior art, this disclosure has at least the following advantages:

[0052] The aforementioned aircraft component assembly hoist, after the lower support rod 230 penetrates the interior of the curved component 20, allows each end of the lower support rod 230, which is horizontally positioned within the mounting opening 2103, to be detachably connected to the mounting bracket 210. This confines a portion of the curved component 20 within the mounting opening 2103. Furthermore, because the upper pressure plate 220, located above the lower support rod 230, is vertically positioned within the mounting opening 2103, and each end of the upper pressure plate 220 is connected to the corresponding end of the lower support rod 230 via a locking assembly 300, when the locking assembly 300 is tightened, the upper pressure plate 220 approaches the curved component 20 and presses against its outer surface. This allows the upper pressure plate 220 and the lower support rod 230 to jointly clamp and restrict the displacement of the curved component 20, thereby improving the reliability of the installation between the curved component 20 and the clamping and locking structure 200. Thus, after the clamping and locking structure 200 is installed on the lifting chain 110 of the hoist 100, the aircraft component 10 can be lifted more smoothly by the hoist 100, thereby reducing the occurrence of accidents.

[0053] The embodiments described above are merely illustrative of several implementations of this disclosure, and while the descriptions are specific and detailed, they should not be construed as limiting the scope of the utility model patent. It should be noted that those skilled in the art can make various modifications and improvements without departing from the concept of this disclosure, and these all fall within the protection scope of this disclosure. Therefore, the protection scope of this patent should be determined by the appended claims.

Claims

1. A lifting device for assembling aircraft components, comprising: A lifting device, which is used to fix the device to the bracket; The feature is that the lifting device for assembling aircraft components further includes a clamping and locking structure; The clamping and locking structure includes a mounting frame, an upper pressure plate, and a lower support rod. The mounting frame is mounted on the lifting chain of the hoist, and an installation opening is formed on the mounting frame. The lower support rod is used to pass through the curved component and is placed horizontally within the installation opening. Each end of the lower support rod is detachably connected to the mounting frame. The upper pressure plate is lifted and positioned within the installation opening and above the lower support rod. Each end of the upper pressure plate is connected to the corresponding end of the lower support rod through a locking assembly, and the upper pressure plate is used to press against the outer surface of the curved component when the locking assembly is locked.

2. The lifting tool for assembling aircraft components according to claim 1, characterized in that, The upper pressure plate is provided with a plurality of damping protrusions, which are arranged facing the lower support rod; the damping protrusions are used to abut against the outer surface of the curved component.

3. The lifting tool for assembling aircraft components according to claim 2, characterized in that, The damping protrusions are tooth-shaped or cylindrical.

4. The lifting tool for assembling aircraft components according to claim 2, characterized in that, The upper pressure plate and the damping protrusion are integrally formed.

5. The lifting tool for assembling aircraft components according to claim 1, characterized in that, The upper pressure plate has an arc-shaped lower surface, which is used to fit and adapt to the outer surface of the curved component; and / or, The upper pressure plate has an elastic sheet structure.

6. The lifting tool for assembling aircraft components according to claim 1, characterized in that, The mounting bracket has two vertical lifting holes, and each end of the upper pressure plate passes through one of the corresponding vertical lifting holes.

7. The lifting tool for assembling aircraft components according to claim 1, characterized in that, The mounting bracket has two mounting holes, and each end of the lower support rod passes through one of the corresponding mounting holes.

8. The lifting tool for assembling aircraft components according to claim 1, characterized in that, The locking assembly includes a bolt and a nut. Each end of the upper pressure plate has a first through hole, and each end of the lower support rod has a second through hole. The bolt passes through the corresponding first through hole and the corresponding second through hole in sequence and is threaded to the nut.

9. The lifting tool for assembling aircraft components according to claim 1, characterized in that, The lifting device is a hand-operated hoist; and / or... The outer surface of the mounting bracket has a first adhesive layer; and / or, The outer surface of the upper pressure plate has a second adhesive layer.

10. An aircraft maintenance device, characterized in that, The aircraft component assembly hoisting tool includes any one of claims 1 to 9.

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