Adjustable lifting device for aircraft components and lifting equipment

Abstract

The present disclosure provides an adjustable lifting device for aircraft components and a lifting device; the adjustable lifting device for aircraft components comprises a lifting support, a load-bearing base and a plurality of locking columns; the load-bearing base is installed on the lifting support; each locking column is installed on the load-bearing base; the load-bearing base comprises a left load-bearing body and a right load-bearing body; the left load-bearing body is provided with an insertion sliding groove, and the right load-bearing body is provided with an insertion part; the insertion part is slidably inserted into the insertion sliding groove to lengthen or shorten the length of the load-bearing base; a part of the locking columns are installed on the left load-bearing body, and another part of the locking columns are installed on the right load-bearing body; the length of the load-bearing base can be lengthened or shortened by sliding the insertion part of the right load-bearing body in the insertion sliding groove of the left load-bearing body, so that the distance between the part of the locking columns installed on the left load-bearing body and the part of the locking columns installed on the right load-bearing body can be adjusted synchronously to adapt to the distance between at least two mounting holes on the aircraft component.

Description

Technical Field

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

[0002] During aircraft maintenance and repair, lifting operations of aircraft components are frequently required in workshops or field areas. Therefore, most manufacturers use aircraft lifting devices, such as those described in Chinese patent document CN214399474U, for this purpose. While these devices can smoothly lift aircraft components by engaging with at least two corresponding mounting holes, the significant differences in aircraft component dimensions result in large variations in the spacing between adjacent mounting holes. This can cause obstacles when the aforementioned aircraft lifting devices engage with the mounting holes, necessitating the replacement with a more suitable lifting device, thus affecting the lifting efficiency of the aircraft components. Utility Model Content

[0003] The purpose of this disclosure is to overcome the shortcomings of the prior art and provide an adjustable lifting tool and lifting equipment for aircraft components that can quickly adapt to changes in the size of different aircraft components.

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

[0005] An adjustable lifting device for aircraft parts includes:

[0006] Lifting support;

[0007] A load-bearing base, wherein the load-bearing base is mounted on the lifting bracket; and,

[0008] A plurality of locking pins, each of which is installed on the load-bearing base and is used to mate with mounting holes on aircraft components;

[0009] The load-bearing base includes a left load-bearing body and a right load-bearing body; the left load-bearing body has an insertion groove, and the right load-bearing body has an insertion part; the insertion part is slidably inserted into the insertion groove to lengthen or shorten the length of the load-bearing base; a portion of the locking pins are installed on the left load-bearing body, and another portion of the locking pins are installed on the right load-bearing body; the lifting bracket includes a first rod and a second rod that are rotatably connected to each other, the first rod is rotatably connected to the left load-bearing body, and the second rod is rotatably connected to the right load-bearing body, so that the first rod, the second rod, and the load-bearing base form a triangular structure.

[0010] In some embodiments, the inner wall of the insertion groove is provided with a plurality of adjustment holes, which are arranged along the sliding direction of the insertion part; a telescopic locking assembly is installed on the insertion part, which is used to engage with any one of the adjustment holes to limit the length of the load-bearing base.

[0011] In some embodiments, the telescopic locking assembly includes a docking pin and a compression spring, and the insertion part has an installation groove; the docking pin is slidably disposed in the installation groove and is connected to the groove wall of the installation groove by the compression spring; the docking pin is used to pass through any of the adjustment holes.

[0012] In some embodiments, the mounting groove has a travel track on its wall; the peripheral wall of the docking pin has a limiting protrusion, which is slidably disposed within the travel track.

[0013] In some embodiments, a left hanging lug is formed on the left-side load-bearing body, and the first end of the first rod is rotatably connected to the left hanging lug via a first rotating shaft.

[0014] In some embodiments, there are two left lugs, which are positioned opposite each other; the first end portion of the first rod is located between the two left lugs, and the two left lugs are rotatably connected to the first rod via the same first pivot.

[0015] In some embodiments, a right-hand lug is formed on the right-hand load-bearing body, and the first end of the second rod is rotatably connected to the right-hand lug via a second pivot.

[0016] In some embodiments, there are two right lugs, which are positioned opposite each other; the first end of the second rod is located between the two right lugs, and the two right lugs are rotatably connected to the second rod via the same second pivot.

[0017] In some embodiments, the second end of the first rod is rotatably connected to the second end of the second rod via a third pivot.

[0018] A lifting device, comprising an adjustable lifting device for aircraft components according to any of the above embodiments.

[0019] Compared with the prior art, this disclosure has at least the following advantages:

[0020] 1) Since the insertion part of the right-side load-bearing body is slidably inserted into the insertion groove of the left-side load-bearing body, and some locking pins are installed on the left-side load-bearing body and others are installed on the right-side load-bearing body, when the size of the aircraft component changes, that is, after the spacing between the corresponding mounting holes on the aircraft component changes, the insertion part of the right-side load-bearing body can slide into the insertion groove of the left-side load-bearing body, thereby lengthening or shortening the length of the load-bearing base. This allows the spacing between the locking pins installed on the left-side load-bearing body and the locking pins installed on the right-side load-bearing body to be adjusted synchronously to match the spacing between at least two mounting holes on the aircraft component. This reduces the need to replace the entire device and ultimately improves the hoisting efficiency of the aircraft component.

[0021] 2) Since the first rod is rotatably connected to the left support and the second rod is rotatably connected to the right support, and the first rod and the second rod are rotatably connected to each other, when the insertion part of the right support slides in the insertion groove of the left support, the first rod rotates relative to the left support and the second rod rotates relative to the right support. The first rod and the second rod rotate synchronously, so that the first rod, the second rod and the support base always maintain a stable triangular structure, and thus the support base can be lifted smoothly by the lifting bracket. Attached Figure Description

[0022] 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.

[0023] Figure 1 This is a transverse cross-sectional view of an adjustable lifting device for aircraft components according to an embodiment of the present disclosure;

[0024] Figure 2 This is a longitudinal sectional view of an adjustable lifting device for aircraft components according to an embodiment of the present disclosure;

[0025] Figure 3 for Figure 2 A magnified view of the area shown at point A in the middle.

[0026] Figure label:

[0027] 10. Aircraft components; 1001. Mounting holes;

[0028] 100. Lifting support; 110. First rod; 120. Second rod; 130. Third pivot;

[0029] 200. Load-bearing base; 210. Left load-bearing body; 2110. Left hanging lug; 2101. Insertion groove; 2111. Adjustment hole; 2120. First rotating shaft; 220. Right load-bearing body; 2210. Insertion part; 2220. Right hanging lug; 2230. Second rotating shaft; 2201. Mounting groove; 2211. Travel rail;

[0030] 300. Locking pin; 310. Nut;

[0031] 400. Telescopic locking assembly; 410. Connecting pin; 4110. Limiting protrusion; 420. Compression spring. Detailed Implementation

[0032] 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.

[0033] 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.

[0034] 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.

[0035] To better understand the technical solutions and beneficial effects of this disclosure, the following detailed description is provided in conjunction with specific embodiments:

[0036] Please see Figure 1An adjustable lifting device for aircraft components according to one embodiment includes a lifting bracket 100, a load-bearing base 200, and a plurality of locking pins 300; the load-bearing base 200 is mounted on the lifting bracket 100; each locking pin 300 is mounted on the load-bearing base 200 and is used to mate with corresponding mounting holes 1001 on the aircraft component 10; the load-bearing base 200 includes a left load-bearing body 210 and a right load-bearing body 220; the left load-bearing body 210 has an insertion groove 2101, and the right load-bearing body 220 has an insertion part 2210; the insertion part 2210 slides. Inserted into the insertion groove 2101 to lengthen or shorten the length of the load-bearing base 200; a portion of the locking pins 300 are installed on the left load-bearing body 210, and another portion of the locking pins 300 are installed on the right load-bearing body 220; the lifting bracket 100 includes a first rod 110 and a second rod 120 rotatably connected to each other, the first rod 110 being rotatably connected to the left load-bearing body 210, and the second rod 120 being rotatably connected to the right load-bearing body 220, so that the first rod 110, the second rod 120, and the load-bearing base 200 form a triangular structure. In some embodiments, two locking pins 300 are respectively installed on the left load-bearing body 210 and the right load-bearing body 220, the first end of the locking pin 300 is welded to the load-bearing base 200, and the second end of the locking pin 300 passes through the mounting hole 1001 on the aircraft component 10 and is threadedly locked with a nut 310.

[0037] It is understandable that, since the insertion part 2210 of the right-side load-bearing body 220 is slidably inserted into the insertion groove 2101 of the left-side load-bearing body 210, and a portion of the locking pins 300 are installed on the left-side load-bearing body 210 and another portion of the locking pins 300 are installed on the right-side load-bearing body 220, when the size of the aircraft component 10 changes, that is, after the spacing between the corresponding mounting holes 1001 on the aircraft component 10 changes, the insertion part 2210 of the right-side load-bearing body 220 can slide into the insertion groove 2101 of the left-side load-bearing body 210, thereby lengthening or shortening the length of the load-bearing base 200. This allows the spacing between the portion of the locking pins 300 installed on the left-side load-bearing body 210 and the portion of the locking pins 300 installed on the right-side load-bearing body 220 to be adjusted synchronously to match the spacing between at least two mounting holes 1001 on the aircraft component 10, thereby reducing the need to replace the entire device and ultimately improving the hoisting efficiency of the aircraft component 10.

[0038] It is understandable that, since the first rod 110 is rotatably connected to the left support 210 and the second rod 120 is rotatably connected to the right support 220, and the first rod 110 and the second rod 120 are rotatably connected to each other, when the insertion part 2210 of the right support 220 slides in the insertion groove 2101 of the left support 210, the first rod 110 rotates relative to the left support 210 and the second rod 120 rotates relative to the right support 220. The first rod 110 and the second rod 120 rotate synchronously, so that the first rod 110, the second rod 120 and the support base 200 always maintain a stable triangular structure, and thus the support base 200 can be lifted smoothly by the lifting bracket 100.

[0039] Please see Figure 1 and Figure 2 In some embodiments, the inner wall of the insertion groove 2101 is provided with a plurality of adjustment holes 2111, which are arranged along the sliding direction of the insertion part 2210; a telescopic locking assembly 400 is installed on the insertion part 2210, which is used to engage with any one of the adjustment holes 2111 to limit the length of the load-bearing base 200. It is understandable that, since the several adjustment holes 2111 on the inner wall of the insertion groove 2101 are arranged along the sliding direction of the insertion part 2210, when the insertion part 2210 of the right support body 220 slides into the insertion groove 2101 of the left support body 210, the telescopic locking assembly 400 is in a retracted state. After the length of the support base 200 is adjusted, the telescopic locking assembly 400 extends into the adjustment hole 2111. At this time, the left support body 210 and the right support body 220 are restricted, thereby limiting the length of the support base 200 so that the locking pin 300 on the support base 200 can better fit the corresponding mounting hole 1001 on the aircraft component 10. In some other embodiments, the number of telescopic locking assemblies 400 is multiple.

[0040] Please see Figure 3In some embodiments, the telescopic locking assembly 400 includes a docking pin 410 and a compression spring 420. The insertion part 2210 has an installation groove 2201. The docking pin 410 is slidably disposed in the installation groove 2201 and is connected to the groove wall of the installation groove 2201 by the compression spring 420. The docking pin 410 is used to pass through any one of the adjustment holes 2111. It is understandable that, since the docking pin 410, which is slidably set in the mounting groove 2201, is connected to the groove wall of the mounting groove 2201 by the compression spring 420, when the insertion part 2210 of the right support body 220 slides in the insertion slide groove 2101 of the left support body 210, the docking pin 410 can be pressed so that the docking pin 410 retracts into the mounting groove 2201, thereby reducing interference with the mounting groove 2201. After the length of the support base 200 is adjusted, the docking pin 410 can be pushed through any adjustment hole 2111 by the compression spring 420 to limit the position of the insertion part 2210 in the insertion slide groove 2101.

[0041] Please see Figure 3 In some embodiments, a travel track 2211 is formed on the wall of the mounting groove 2201; a limiting protrusion 4110 is formed on the peripheral wall of the docking post 410, and the limiting protrusion 4110 is slidably disposed within the travel track 2211. It can be understood that by having the limiting protrusion 4110 formed on the peripheral wall of the docking post 410 slidably disposed within the travel track 2211 formed on the wall of the mounting groove 2201, the sliding travel of the docking post 410 can be limited by the travel track 2211, thereby reducing the occurrence of the docking post 410 dislodging from the mounting groove 2201.

[0042] Please see Figure 1 In some embodiments, a left hanging lug 2110 is formed on the left-side load-bearing body 210, and the first end of the first rod 110 is rotatably connected to the left hanging lug 2110 via a first rotating shaft 2120. It can be understood that because the first end of the first rod 110 is rotatably connected to the left hanging lug 2110 formed on the left-side load-bearing body 210 via the first rotating shaft 2120, the first end of the first rod 110 can lift the left-side load-bearing body 210 while rotating relative to the left hanging lug 2110. In this embodiment, the left hanging lug 2110 is welded to the left-side load-bearing body 210.

[0043] Please see Figure 1In some embodiments, there are two left lugs 2110, which are positioned opposite each other. The first end of the first rod 110 is located between the two left lugs 2110, and the two left lugs 2110 are rotatably connected to the first rod 110 via the same first pivot 2120. It can be understood that because the two left lugs 2110 are rotatably connected to the first rod 110 via the same first pivot 2120, a stable rotatable connection structure can be formed between the two oppositely positioned left lugs 2110 and the first end of the first rod 110. This results in higher structural strength between the first rod 110 and the load-bearing base 200, thereby improving the load-bearing capacity of the load-bearing base 200.

[0044] Please see Figure 1 In some embodiments, a right lug 2220 is formed on the right-side load-bearing body 220, and the first end of the second rod 120 is rotatably connected to the right lug 2220 via a second pivot 2230. It can be understood that because the first end of the second rod 120 is rotatably connected to the right lug 2220 formed on the right-side load-bearing body 220 via the second pivot 2230, the first end of the second rod 120 can lift the right-side load-bearing body 220 while rotating relative to the right lug 2220. In this embodiment, the right lug 2220 is welded to the right-side load-bearing body 220.

[0045] Please see Figure 2 In some embodiments, there are two right-hand lugs 2220, which are positioned opposite each other. The first end of the second rod 120 is located between the two right-hand lugs 2220, and the two right-hand lugs 2220 are rotatably connected to the second rod 120 via the same second pivot 2230. It can be understood that because the two right-hand lugs 2220 are rotatably connected to the second rod 120 via the same second pivot 2230, a stable rotatable connection structure can be formed between the two oppositely positioned right-hand lugs 2220 and the first end of the second rod 120. This results in higher structural strength between the second rod 120 and the load-bearing base 200, thereby improving the load-bearing capacity of the load-bearing base 200.

[0046] Please see Figure 1In some embodiments, the second end of the first rod 110 and the second end of the second rod 120 are rotatably connected via a third pivot 130. It can be understood that, since the second ends of the first rod 110 and the second ends of the second rod 120 are rotatably connected via the third pivot 130, when the insertion portion 2210 of the right-side load-bearing body 220 slides within the insertion groove 2101 of the left-side load-bearing body 210, the first rod 110 and the second rod 120 can rotate synchronously relative to each other to flexibly adapt to changes in the length of the load-bearing base 200. In other embodiments, the second ends of the first rod 110 and the second ends of the second rod 120 can be hinged together.

[0047] Please see Figures 1 to 3 This disclosure also provides a lifting device, including an adjustable lifting device for aircraft components according to any of the above embodiments. It can be understood that by applying the adjustable lifting device for aircraft components of this disclosure to a lifting device, since the insertion portion 2210 of the right-side load-bearing body 220 is slidably inserted into the insertion groove 2101 of the left-side load-bearing body 210, and a portion of the locking pins 300 are installed on the left-side load-bearing body 210 and another portion of the locking pins 300 are installed on the right-side load-bearing body 220, when the size of the aircraft component 10 changes, i.e., after the spacing between the corresponding mounting holes 1001 on the aircraft component 10 changes, the right-side load-bearing body can be adjusted... The insertion part 2210 of 220 slides in the insertion groove 2101 of the left support body 210, thereby lengthening or shortening the length of the support base 200. This allows the distance between the locking pins 300 installed on the left support body 210 and the locking pins 300 installed on the right support body 220 to be adjusted synchronously to match the distance between at least two mounting holes 1001 on the aircraft component 10. This reduces the need to replace the entire device and ultimately improves the hoisting efficiency of the aircraft component 10.

[0048] Compared with the prior art, this disclosure has at least the following advantages:

[0049] 1) Since the insertion part 2210 of the right support body 220 is slidably inserted into the insertion groove 2101 of the left support body 210, and a part of the locking pin 300 is installed on the left support body 210 and another part of the locking pin 300 is installed on the right support body 220, when the size of the aircraft component 10 changes, that is, after the distance between the corresponding mounting holes 1001 on the aircraft component 10 changes, the insertion part 2210 of the right support body 220 can slide into the insertion groove 2101 of the left support body 210, thereby lengthening or shortening the length of the support base 200. This allows the distance between the locking pins 300 installed on the left support body 210 and the locking pins 300 installed on the right support body 220 to be adjusted synchronously to match the distance between at least two mounting holes 1001 on the aircraft component 10, thereby reducing the need to replace the entire device and ultimately improving the hoisting efficiency of the aircraft component 10.

[0050] 2) Since the first rod 110 is rotatably connected to the left support 210 and the second rod 120 is rotatably connected to the right support 220, and the first rod 110 and the second rod 120 are rotatably connected to each other, when the insertion part 2210 of the right support 220 slides in the insertion groove 2101 of the left support 210, the first rod 110 rotates relative to the left support 210 and the second rod 120 rotates relative to the right support 220. The first rod 110 and the second rod 120 rotate synchronously, so that the first rod 110, the second rod 120 and the support base 200 always maintain a stable triangular structure, and thus the support base 200 can be lifted smoothly by the lifting bracket 100.

[0051] 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. An adjustable lifting device for aircraft parts, comprising: Lifting support; A load-bearing base, which is installed on the lifting bracket; and, A plurality of locking pins, each of which is installed on the load-bearing base and is used to mate with mounting holes on aircraft components; The load-bearing base is characterized by comprising a left load-bearing body and a right load-bearing body; the left load-bearing body has an insertion groove, and the right load-bearing body has an insertion part; the insertion part is slidably inserted into the insertion groove to lengthen or shorten the length of the load-bearing base; a portion of the locking pins are installed on the left load-bearing body, and another portion of the locking pins are installed on the right load-bearing body; the lifting bracket comprises a first rod and a second rod rotatably connected to each other, the first rod being rotatably connected to the left load-bearing body, and the second rod being rotatably connected to the right load-bearing body, so that the first rod, the second rod, and the load-bearing base form a triangular structure.

2. The adjustable hanger for aircraft parts according to claim 1, characterized in that The inner wall of the insertion groove is provided with a plurality of adjustment holes, which are arranged along the sliding direction of the insertion part; a telescopic locking assembly is installed on the insertion part, which is used to engage with any one of the adjustment holes to limit the length of the load-bearing base.

3. The adjustable lifting device for aircraft components according to claim 2, characterized in that, The telescopic locking assembly includes a docking pin and a compression spring. The insertion part has an installation groove. The docking pin is slidably disposed in the installation groove and is connected to the groove wall of the installation groove by the compression spring. The docking pin is used to pass through any of the adjustment holes.

4. The adjustable lifting device for aircraft components according to claim 3, characterized in that, The mounting groove has a travel track on its wall; the peripheral wall of the docking pin has a limiting protrusion, which is slidably disposed within the travel track.

5. The adjustable lifting device for aircraft components according to claim 1, characterized in that, A left hanging lug is formed on the left-side load-bearing body, and the first end of the first rod is rotatably connected to the left hanging lug via a first rotating shaft.

6. The adjustable lifting device for aircraft components according to claim 5, characterized in that, There are two left hooks, and the two left hooks are positioned opposite each other; the first end of the first rod is located between the two left hooks, and the two left hooks are rotatably connected to the first rod through the same first pivot.

7. The adjustable lifting device for aircraft components according to claim 1, characterized in that, A right hanging lug is formed on the right-side load-bearing body, and the first end of the second rod is rotatably connected to the right hanging lug via a second rotating shaft.

8. The adjustable lifting device for aircraft components according to claim 7, characterized in that, There are two right lugs, and the two right lugs are positioned opposite each other; the first end of the second rod is located between the two right lugs, and the two right lugs are rotatably connected to the second rod via the same second pivot.

9. The adjustable lifting device for aircraft components according to claim 1, characterized in that, The second end of the first rod is rotatably connected to the second end of the second rod via a third rotating shaft.

10. A hoisting device, characterized in that, The adjustable lifting device for aircraft components includes any one of claims 1 to 9.

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