Positioning tool for aircraft assembly

Abstract

The utility model relates to the technical field of aircraft assembly, and discloses a positioning tool for aircraft assembly, which is characterized in that a rotary clamping mechanism is arranged in a bottom plate, a first aircraft part is arranged at the top of the rotary clamping mechanism, a lifting mechanism is arranged at the back end of the bottom plate, a second aircraft part is arranged at the bottom of the lifting mechanism, and the first aircraft part and the second aircraft part are arranged on the bottom plate. The rotating clamping mechanism comprises a rotating assembly and a clamping assembly, the rotating assembly is arranged at the bottom of the bottom plate, the clamping assembly is arranged in the rotating assembly, the rotating assembly comprises a supporting frame, the supporting frame is fixedly connected to the bottom of the bottom plate, and a rotating rod is rotationally connected to the inner bottom of the supporting frame; the periphery of the rotating rod is fixedly connected with a worm wheel. The first motor drives the worm to rotate, the worm drives the rotating rod to rotate through the worm gear, the rotating rod drives the first aircraft part to rotate through the rotating disc, the first aircraft part can be aligned with the second aircraft part, and the second aircraft part can be inserted into the first aircraft part.

Description

Technical Field

[0001] The utility model relates to the technical field of aircraft assembly, in particular to a positioning tool used for aircraft assembly. Background Art

[0002] In the assembly of aircraft structures and aircraft flight tests and modifications, high assembly accuracy needs to be ensured between parts. Therefore, it is often necessary to manufacture special assembly tools to meet these structural requirements.

[0003] Announcement No. CN 206519880 U discloses a positioning clamping device for aircraft assembly tooling, wherein a supporting rib is threadedly connected to a bolt through a second threaded through hole, the bolt is sleeved with a metal spring, and the end of the bolt is embedded and connected to a metal block through a second circular blind hole.

[0004] The positioning clamping device for aircraft assembly tooling has a second rubber pad fixedly connected to the inner side of the arc-shaped metal support. The second rubber pad can effectively prevent the arc-shaped metal support from rigidly contacting the positioning pin, protect the surface of the positioning pin from being damaged, and can also play a corresponding shock-absorbing role. However, the device is not provided with a device for fine-tuning the aircraft parts. When the corresponding positions of two aircraft parts need to be fine-tuned, the staff needs to adjust manually, which is troublesome, and therefore needs to be improved. Utility Model Content

[0005] The purpose of the utility model is to provide a positioning tool for aircraft assembly to solve the problems raised in the above background technology.

[0006] To achieve the above-mentioned purpose, the utility model provides the following technical solutions: a positioning tool for aircraft assembly, comprising a bottom plate, a rotating clamping mechanism is arranged inside the bottom plate, a first aircraft part is arranged on the top of the rotating clamping mechanism, a lifting mechanism is arranged at the back end of the bottom plate, and a second aircraft part is arranged at the bottom of the lifting mechanism;

[0007] The rotating clamping mechanism comprises a rotating assembly and a clamping assembly, wherein the rotating assembly is arranged at the bottom of the base plate, and a clamping assembly is arranged inside the rotating assembly;

[0008] The rotating assembly includes a support frame, which is fixedly connected to the bottom of the base plate, a rotating rod is rotatably connected to the inner bottom of the support frame, a worm wheel is fixedly connected to the outer periphery of the rotating rod, a worm is meshed with the right side of the worm wheel, a first motor is fixedly connected to the front of the worm, the first motor is fixedly connected to the bottom of the base plate, a rotating disk is fixedly connected to the top of the rotating rod, a supporting disk is fixedly connected to the bottom of the rotating disk, and the top of the supporting disk is in contact with the bottom of the first aircraft component.

[0009] Preferably, a circular groove corresponding to the movement trajectory of the support disk is opened inside the bottom plate, and the support disk is slidably connected inside the circular groove. The circular groove makes the support disk more stable during the rotation process.

[0010] Preferably, a circular hole corresponding to the position of the rotating rod is opened inside the bottom plate, and the rotating rod is rotatably connected to the inner side of the circular hole. Through the opened circular hole, the rotating rod can drive the supporting plate to rotate during the rotation process.

[0011] Preferably, the clamping assembly includes a dual-axis motor, which is fixedly connected to the inside of the base plate, and the dual-axis motor is fixedly connected to a first threaded rod on both sides, the left side of the first threaded rod is rotatably connected to the left side of the rotating disk, the outer periphery of the first threaded rod is threadedly connected to a threaded block, and the top of the threaded block is fixedly connected to a clamping plate.

[0012] Preferably, a limiting groove corresponding to the movement trajectory of the threaded block is opened inside the rotating disk, and the threaded block is slidably connected inside the limiting groove. The limited groove makes the threaded block more stable during the movement.

[0013] Preferably, the lifting mechanism includes a fixed frame, which is fixedly connected to the back end of the base plate, a second motor is fixedly connected to the top of the fixed frame, a second threaded rod is fixedly connected to the bottom of the second motor, a support plate is rotatably connected to the bottom of the second threaded rod, and the support plate is fixedly connected to the bottom of the back end of the fixed frame, a threaded disk is threadedly connected to the outer periphery of the second threaded rod, a connecting plate is fixedly connected to the front of the threaded disk, a fixed plate is fixedly connected to the top of the connecting plate, a cylinder is fixedly connected to the right side of the fixed plate, a push plate is fixedly connected to the left side of the cylinder, an anti-skid plate is fixedly connected to the bottom of the push plate, and the inner side of the anti-skid plate is in contact with the outer periphery of the second aircraft component.

[0014] Preferably, a slide groove corresponding to the movement trajectory of the threaded disk is opened inside the fixing frame, and the threaded disk is slidably connected inside the slide groove. Through the opened slide groove, the threaded disk can drive the connecting plate to move during the movement.

[0015] Compared with the prior art, the utility model provides a positioning tool for aircraft assembly, which has the following beneficial effects:

[0016] 1. The positioning tool for aircraft assembly places the first aircraft part on the top of the rotating disk through the provided rotating clamping mechanism, drives the first threaded rod to rotate through the dual-axis motor, and drives the clamping plate to move through the threaded block, so that the clamping plate can clamp the first aircraft part. When the first aircraft part needs to be fine-tuned, the worm is driven to rotate through the first motor, so that the worm drives the rotating rod to rotate through the worm gear, and the rotating rod drives the first aircraft part to rotate through the rotating disk, so that the first aircraft part can be aligned with the second aircraft part, and the second aircraft part can be inserted into the first aircraft part.

[0017] 2. The positioning tool for aircraft assembly, through the provided lifting mechanism, when the second aircraft part needs to be installed, drives the push plate to move through the cylinder, so that the push plate can drive the anti-slide plate to move, so that the anti-slide plate can clamp the second aircraft part, and drives the second threaded rod to rotate through the second motor, so that the second threaded rod drives the threaded disk to move downward, so that the threaded disk drives the connecting plate to move, so that the connecting plate drives the second aircraft part to move downward, so that the second aircraft part can be inserted into the first aircraft part for installation. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] In order to more clearly illustrate the technical solutions in the embodiments of the present invention, the following briefly introduces the drawings required for use in the description of the embodiments. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative labor:

[0019] Figure 1 This is a schematic diagram of the front view structure of the utility model;

[0020] Figure 2 It is a schematic diagram of the structure of the rotary clamping mechanism;

[0021] Figure 3 It is a schematic diagram of the rotating component structure;

[0022] Figure 4 It is a schematic diagram of the structure of the clamping assembly;

[0023] Figure 5 It is a schematic diagram of the lifting mechanism structure.

[0024] In the figure: 1, bottom plate; 2, first aircraft part; 3, second aircraft part; 4, lifting mechanism; 41, anti-skid plate; 42, connecting plate; 43, fixing plate; 44, pushing plate; 45, cylinder; 46, second motor; 47, threaded disk; 48, fixing frame; 49, supporting plate; 401, second threaded rod; 5, rotating clamping mechanism; 51, rotating assembly; 511, worm; 512, first motor; 513, rotating rod; 514, worm gear; 515, supporting frame; 516, rotating disk; 517, supporting disk; 52, clamping assembly; 521, clamping plate; 522, threaded block; 523, first threaded rod; 524, dual-axis motor. DETAILED DESCRIPTION

[0025] The following will be combined with the drawings in the embodiments of the utility model to clearly and completely describe the technical solutions in the embodiments of the utility model. Obviously, the described embodiments are only part of the embodiments of the utility model, not all of the embodiments. Based on the embodiments in the utility model, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the utility model.

[0026] In the present invention, unless otherwise clearly specified and limited, the terms "install", "connect", "connect", "fix" and the like should be understood in a broad sense, 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 the internal connection of two elements or the interaction relationship between two elements. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0027] The utility model provides the following technical solutions:

[0028] Embodiment 1

[0029] See also Figure 1-5 The utility model provides a technical solution: a positioning tool for aircraft assembly, comprising a bottom plate 1, a rotating clamping mechanism 5 is arranged inside the bottom plate 1, a first aircraft part 2 is arranged on the top of the rotating clamping mechanism 5, a lifting mechanism 4 is arranged at the back end of the bottom plate 1, and a second aircraft part 3 is arranged at the bottom of the lifting mechanism 4;

[0030] The rotating clamping mechanism 5 includes a rotating assembly 51 and a clamping assembly 52. ​​The rotating assembly 51 is arranged at the bottom of the base plate 1, and the clamping assembly 52 is arranged inside the rotating assembly 51.

[0031] The rotating assembly 51 includes a support frame 515, which is fixedly connected to the bottom of the base plate 1. The bottom of the support frame 515 is rotatably connected to a rotating rod 513, and the outer periphery of the rotating rod 513 is fixedly connected to a worm gear 514. A worm 511 is meshed on the right side of the worm gear 514. A first motor 512 is fixedly connected to the front of the worm gear 511. The first motor 512 is fixedly connected to the bottom of the base plate 1. A rotating disk 516 is fixedly connected to the top of the rotating rod 513. A supporting disk 517 is fixedly connected to the bottom of the rotating disk 516. The top of the supporting disk 517 is in contact with the bottom of the first aircraft component 2.

[0032] Furthermore, a circular groove corresponding to the movement trajectory of the support plate 517 is opened inside the bottom plate 1, and the support plate 517 is slidably connected inside the circular groove. The opening of the circular groove makes the support plate 517 more stable during the rotation process.

[0033] Furthermore, a circular hole corresponding to the position of the rotating rod 513 is opened inside the bottom plate 1, and the rotating rod 513 is rotatably connected to the inner side of the circular hole. Through the opened circular hole, the rotating rod 513 can drive the supporting plate 517 to rotate during the rotation process.

[0034] Embodiment 2

[0035] See also Figure 1-5 On the basis of the first embodiment, the clamping assembly 52 further comprises a dual-axis motor 524, the dual-axis motor 524 is fixedly connected to the inside of the bottom plate 1, the dual-axis motor 524 is fixedly connected to the first threaded rod 523 on both sides, the left side of the first threaded rod 523 is rotatably connected to the left side of the rotating disk 516, the outer periphery of the first threaded rod 523 is threadedly connected to a threaded block 522, and the top of the threaded block 522 is fixedly connected to the clamping plate 521.

[0036] Furthermore, a limiting groove corresponding to the movement trajectory of the threaded block 522 is opened inside the rotating disk 516, and the threaded block 522 is slidably connected inside the limiting groove. The limited groove makes the threaded block 522 more stable during the movement.

[0037] Embodiment 3

[0038] See also Figure 1-5On the basis of the first embodiment, the lifting mechanism 4 further comprises a fixing frame 48, the fixing frame 48 is fixedly connected to the back end of the bottom plate 1, the top of the fixing frame 48 is fixedly connected to a second motor 46, the bottom of the second motor 46 is fixedly connected to a second threaded rod 401, the bottom of the second threaded rod 401 is rotatably connected to a support plate 49, the support plate 49 is fixedly connected to the bottom of the back end of the fixing frame 48, the outer periphery of the second threaded rod 401 is threadedly connected to a threaded disk 47, the front side of the threaded disk 47 is fixedly connected to a connecting plate 42, the top of the connecting plate 42 is fixedly connected to a fixing plate 43, the right side of the fixing plate 43 is fixedly connected to a cylinder 45, the left side of the cylinder 45 is fixedly connected to a push plate 44, the bottom of the push plate 44 is fixedly connected to an anti-skid plate 41, and the inner side of the anti-skid plate 41 is in contact with the outer periphery of the second aircraft component 3.

[0039] Furthermore, a slide groove corresponding to the movement trajectory of the threaded disk 47 is opened inside the fixing frame 48, and the threaded disk 47 is slidably connected inside the slide groove. Through the opened slide groove, the threaded disk 47 can drive the connecting plate 42 to move during the movement.

[0040] In actual operation, when the device is used, the cylinder 45 drives the push plate 44 to move, so that the push plate 44 can drive the anti-slide plate 41 to move, so that the anti-slide plate 41 can clamp the second aircraft component 3, and the first aircraft component 2 is placed on the top of the rotating disk 516, and the dual-axis motor 524 drives the first threaded rod 523 to rotate, so that the first threaded rod 523 drives the clamping plate 521 to move through the threaded block 522, so that the clamping plate 521 can clamp the first aircraft component 2;

[0041] The second motor 46 drives the second threaded rod 401 to rotate, so that the second threaded rod 401 drives the threaded disk 47 to move downward, so that the threaded disk 47 drives the connecting plate 42 to move, and the connecting plate 42 drives the second aircraft component 3 to move downward. When the second aircraft component 3 needs to be assembled on the top of the first aircraft component 2 and the first aircraft component 2 needs to be fine-tuned, the first motor 512 drives the worm 511 to rotate, so that the worm 511 drives the rotating rod 513 to rotate through the worm gear 514, and the rotating rod 513 drives the first aircraft component 2 to rotate through the rotating disk 516, so that the first aircraft component 2 can be aligned with the second aircraft component 3, and the second aircraft component 3 can be inserted into the first aircraft component 2.

[0042] It should be noted that, in this article, relational terms such as first and second, etc. are only used to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Moreover, the terms "include", "comprise" or any other variants thereof are intended to cover non-exclusive inclusion, so that a process, method, article or device including a series of elements includes not only those elements, but also other elements not explicitly listed, or also includes elements inherent to such process, method, article or device. In the absence of further restrictions, the elements defined by the statement "comprise a ..." do not exclude the presence of other identical elements in the process, method, article or device including the elements.

Claims

1. A positioning tool for aircraft assembly, comprising a base plate (1), characterized in that: A rotating clamping mechanism (5) is arranged inside the bottom plate (1), a first aircraft component (2) is arranged on the top of the rotating clamping mechanism (5), a lifting mechanism (4) is arranged at the back end of the bottom plate (1), and a second aircraft component (3) is arranged at the bottom of the lifting mechanism (4); The rotating clamping mechanism (5) comprises a rotating assembly (51) and a clamping assembly (52); the rotating assembly (51) is arranged at the bottom of the base plate (1); and the clamping assembly (52) is arranged inside the rotating assembly (51); The rotating assembly (51) comprises a support frame (515), wherein the support frame (515) is fixedly connected to the bottom of the base plate (1), a rotating rod (513) is rotatably connected to the inner bottom of the support frame (515), a worm wheel (514) is fixedly connected to the outer periphery of the rotating rod (513), a worm (511) is meshed on the right side of the worm wheel (514), a first motor (512) is fixedly connected to the front of the worm (511), the first motor (512) is fixedly connected to the bottom of the base plate (1), a rotating disk (516) is fixedly connected to the top of the rotating rod (513), a supporting disk (517) is fixedly connected to the bottom of the rotating disk (516), and the top of the supporting disk (517) is in contact with the bottom of the first aircraft component (2).

2. A positioning tool for aircraft assembly according to claim 1, characterized in that: A circular groove corresponding to the movement track of the support plate (517) is provided inside the bottom plate (1), and the support plate (517) is slidably connected inside the circular groove.

3. A positioning tool for aircraft assembly according to claim 1, characterized in that: A circular hole corresponding to the position of the rotating rod (513) is provided inside the bottom plate (1), and the rotating rod (513) is rotatably connected to the inner side of the circular hole.

4. A positioning tool for aircraft assembly according to claim 1, characterized in that: The clamping assembly (52) comprises a dual-axis motor (524), the dual-axis motor (524) is fixedly connected to the inside of the base plate (1), the dual-axis motor (524) is fixedly connected to first threaded rods (523) on the left and right sides, the left side of the first threaded rod (523) is rotatably connected to the left side of the rotating disk (516), the outer periphery of the first threaded rod (523) is threadedly connected to a threaded block (522), and the top of the threaded block (522) is fixedly connected to a clamping plate (521).

5. A positioning tool for aircraft assembly according to claim 4, characterized in that: A limiting groove corresponding to the movement track of the threaded block (522) is provided inside the rotating disk (516), and the threaded block (522) is slidably connected inside the limiting groove.

6. A positioning tool for aircraft assembly according to claim 1, characterized in that: The lifting mechanism (4) comprises a fixing frame (48), the fixing frame (48) is fixedly connected to the back end of the base plate (1), the top of the fixing frame (48) is fixedly connected to a second motor (46), the bottom of the second motor (46) is fixedly connected to a second threaded rod (401), the bottom of the second threaded rod (401) is rotatably connected to a support plate (49), the support plate (49) is fixedly connected to the bottom of the back end of the fixing frame (48), the outer periphery of the second threaded rod (401) is threadedly connected to a threaded disk (47), the front of the threaded disk (47) is fixedly connected to a connecting plate (42), the top of the connecting plate (42) is fixedly connected to a fixing plate (43), the right side of the fixing plate (43) is fixedly connected to a cylinder (45), the left side of the cylinder (45) is fixedly connected to a push plate (44), the bottom of the push plate (44) is fixedly connected to an anti-slip plate (41), the inner side of the anti-slip plate (41) is mutually fitted with the outer periphery of the second aircraft component (3).

7. A positioning tool for aircraft assembly according to claim 6, characterized in that: A sliding groove corresponding to the movement track of the threaded disc (47) is provided inside the fixing frame (48), and the threaded disc (47) is slidably connected inside the sliding groove.

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