Clamping device for machining and production of aircraft parts

Abstract

The utility model belongs to the technical field of clamping devices, and discloses a clamping device for aircraft part machining and production, the clamping device comprises a workbench, two guide grooves are formed in the top surface of the workbench in parallel, and two guide blocks are slidably mounted in each guide groove. A contact block is arranged on the supporting piece, a second threaded column with a clamping piece and a butterfly nut is arranged on the supporting piece and corresponds to the contact block, the aircraft part makes contact with the contact block on the supporting piece, then the butterfly nut on the surface of the second threaded column is rotated, and the butterfly nut drives the clamping piece to move downwards synchronously in the downward moving stage. Compared with the prior art, the arc-shaped aircraft part clamping device has the advantage that the arc-shaped aircraft part clamping device is suitable for clamping operation of arc-shaped aircraft parts.

Description

Technical Field

[0001] This application relates to the technical field of clamping devices, and more specifically, to a clamping device for machining and producing aircraft parts. Background Art

[0002] Aircraft parts refer to the various components that make up an aircraft, including the fuselage, wings, engines, landing gears, flaps, slats, etc. Among them, the fuselage, wings, landing gears, etc. are the main load-bearing components of the aircraft. In order to facilitate the machining of aircraft parts (especially the aircraft shell), it is necessary to use a clamping device to fix them.

[0003] After retrieval, the publication number: CN213106161U discloses a quick-clamping hardware fitting grinding device, which includes a workbench. Opposite vertical plates 1 and 2 are arranged on the top of the workbench, and a clamping assembly 1 for clamping and fixing both sides of the hardware fitting is arranged between the vertical plate 1 and the vertical plate 2. The clamping assembly 1 includes two clamping plates 1 arranged in parallel between the vertical plate 1 and the vertical plate 2. A screw rod 1 that is vertically inserted through the vertical plate 1 and is in threaded cooperation with it is provided. One end of the screw rod 1 is rotatably connected to the plate body of the adjacent clamping plate 1, and a telescopic rod 1 is connected between the vertical plate 1 and the adjacent clamping plate 1. Through the clamping assembly 1 arranged between the vertical plates on the workbench and the clamping assembly 2 arranged on the clamping plate 1 of the clamping assembly 1, hardware fittings with different lengths and thicknesses can be quickly clamped and fixed, improving the adaptability to the hardware fittings, and ensuring the clamping and positioning effect, grinding efficiency, and grinding effect of the hardware fittings.

[0004] However, the clamping device in the above solution is not convenient for clamping aircraft parts with arc surfaces, and it is difficult to ensure the reliability and stability of aircraft parts during the machining stage in actual use.

[0005] In order to solve the above problems, this application provides a clamping device for machining and producing aircraft parts. Utility Model Content

[0006] The clamping device for machining and producing aircraft parts provided by this application adopts the following technical solutions:

[0007] A clamping device for aircraft component processing and production, including a workbench. Two guiding grooves are parallelly arranged on the top surface of the workbench, and two guiding blocks are slidably installed in each guiding groove. A bidirectional screw rod is rotatably installed in each of the two guiding grooves of the workbench through a shaft seat. The two guiding blocks are respectively threadedly connected to the bidirectional screw rod through screw holes. A first threaded column is welded to the top of the guiding block, and a support member is sleeved on the surface of the first threaded column. And a hexagonal nut that abuts against the support member is screwed on the surface of the first threaded column. A contact block is welded to the top surface of the support member, and an arc surface is arranged on the top surface of the contact block. And a second threaded column welded to the support member is arranged on the left side of the contact block. A clamping member is sleeved on the surface of the second threaded column. Both ends of the clamping member are integrally cast with bent portions. And a wing nut that contacts the clamping member is screwed on the upper part of the second threaded column.

[0008] Through the above technical solution, in order to avoid unnecessary obstacles to the clamping of aircraft components by the first threaded column, the height of the first threaded column is lower than that of the second threaded column. In order to increase the reliability of clamping automotive components, a support member is respectively arranged at the four corners of the top surface of the workbench.

[0009] Further, a flat circular structure adjusting hole is arranged on the right side of the surface of the support member, and the inner size of the adjusting hole is adapted to the diameter of the first threaded column.

[0010] Through the above technical solution, through the arrangement of the adjusting hole, it is easy to adjust the position of the support member to meet the clamping requirements of aircraft components of different sizes.

[0011] Further, two sets of threads with opposite directions are arranged on the surface of the bidirectional screw rod, and the two guiding blocks in the guiding groove are respectively connected to the two sets of threads.

[0012] Through the above technical solution, through the two sets of threads with opposite directions, it is easy for the two guiding blocks to move towards or away from each other, which is suitable for clamping aircraft components of different sizes.

[0013] Further, the clamping member is composed of a flat circular metal piece with a central hole and bent portions on both sides thereof.

[0014] Through the above technical solution, through the flat circular metal piece of the clamping member, it is convenient to keep sleeved with the second threaded column. Through the bent portions of the clamping member, it is convenient to contact and fix the aircraft components.

[0015] Further, a disc-shaped handwheel is fixedly connected to the side surface of the workbench corresponding to the bidirectional screw rod, and a ball bearing is arranged at the connection between the bidirectional screw rod and the guiding groove.

[0016] Through the above technical solution, through the arrangement of the disc-shaped handwheel, it is easy to rotate the bidirectional screw rod and convenient to adjust the distance between the two guiding blocks.

[0017] Furthermore, the radian of the arc surface on the top surface of the contact block is adapted to the arc radian of the aircraft component.

[0018] Through the above technical solution, by setting the arc surface, it is easy to provide adaptive support for the arc surface of the aircraft component. In order to be applicable to aircraft components with different radian, the arc radian of the contact block can be prefabricated in different specifications and belong to different support members.

[0019] In summary, the present application includes the following beneficial technical effects:

[0020] By providing a contact block with an arc surface on the support member and a second threaded post with a clamping member and a wing nut corresponding to the contact block on the support member, by bringing the aircraft component into contact with the contact block on the support member, and then rotating the wing nut on the surface of the second threaded post, the wing nut is driven to move downward to drive the clamping member to move downward synchronously, so that the bent portions at both ends of the clamping member abut against the top surface of the aircraft component corresponding to the contact block. Compared with the prior art, it is applicable to the clamping operation of arc-shaped aircraft components. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Figure 1 It is the overall top view of the present application;

[0022] Figure 2 It is the overall side view of the present application;

[0023] Figure 3 It is the schematic structural view of the support member of the present application.

[0024] Description of the reference numerals in the drawings:

[0025] 1, workbench; 2, guide groove; 3, bidirectional screw; 4, guide block; 5, support member; 6, first threaded post; 7, adjustment hole; 8, hexagon nut; 9, contact block; 10, arc surface; 11, second threaded post; 12, clamping member; 13, wing nut; 14, bent portion. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0026] Next, the technical solutions in the embodiments of the present application will be clearly and completely described with reference to the drawings in the embodiments of the present application; obviously, the described embodiments are only a part of the embodiments of the present application, rather than all the embodiments. Based on the embodiments in the present application, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the protection scope of the present application.

[0027] In the description of the present application, it should be noted that the orientation or positional relationship indicated by terms such as "upper", "lower", "inner", "outer", "top / bottom end", etc. is based on the orientation or positional relationship shown in the drawings. It is only for the convenience of describing the present application and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation. Therefore, it should not be construed as a limitation to the present application. In addition, the terms "first" and "second" are only used for descriptive purposes and cannot be construed as indicating or implying relative importance.

[0028] In the description of the present application, it should be noted that unless otherwise clearly specified and limited, terms such as "installed", "provided with", "sheathed / connected", "connected", etc. should be understood in a broad sense. For example, "connected" 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 directly connected or indirectly connected through an intermediate medium, and it can be the communication inside two elements. For those of ordinary skill in the art, the specific meanings of the above terms in the present application can be understood according to specific circumstances.

[0029] Embodiment:

[0030] The embodiment of the present application discloses a clamping device for aircraft parts processing and production. Please refer to Figure 1 and Figure 3 , including.

[0031] Please refer to Figures 1-3, A clamping device for aircraft component processing and production, including a workbench 1. Two guiding grooves 2 are parallelly opened on the top surface of the workbench 1, and two guiding blocks 4 are slidably installed in each guiding groove 2. A bidirectional screw 3 is rotatably installed in each of the two guiding grooves 2 of the workbench 1 through a shaft seat. The two guiding blocks 4 are respectively threadedly connected to the bidirectional screw 3 through threaded holes. A first threaded column 6 is welded to the top of the guiding block 4, and a support member 5 is sleeved on the surface of the first threaded column 6. And a hexagonal nut 8 that abuts against the support member 5 is screwed on the surface of the first threaded column 6. A contact block 9 is welded to the top surface of the support member 5, and an arc surface 10 is provided on the top surface of the contact block 9. And a second threaded column 11 welded to the support member 5 is provided on the left side of the contact block 9. A clamping member 12 is sleeved on the surface of the second threaded column 11. And bent portions 14 are integrally cast at both ends of the clamping member 12. And a butterfly nut 13 that contacts the clamping member 12 is screwed on the upper part of the second threaded column 11. In order to avoid unnecessary obstruction to the clamping of aircraft components by the first threaded column 6, the height of the first threaded column 6 is lower than the height of the second threaded column 11. In order to increase the reliability of clamping of automotive components, a support member 5 is respectively provided at the four corners of the top surface of the workbench 1. The cross-sections of the guiding groove 2 and the guiding block 4 are both inverted T-shaped structures. Through the guiding block 4 with a threaded hole, on the one hand, it serves as a sliding component that cooperates with the guiding groove 2, and on the other hand, it serves as a threaded connection component with the bidirectional screw 3.

[0032] Please refer to Figures 1-3 , An adjustment hole 7 with an oblate structure is opened on the right side of the surface of the support member 5, and the inner dimension of the adjustment hole 7 is adapted to the diameter of the first threaded column 6. Through the setting of the adjustment hole 7, it is easy to adjust the position of the support member 5 to meet the clamping requirements of aircraft components of different sizes.

[0033] Please refer to Figure 1 , Two sets of threads with opposite directions are provided on the surface of the bidirectional screw 3. The two guiding blocks 4 in the guiding groove 2 are respectively connected to the two sets of threads. Through the two sets of threads with opposite directions, it is easy for the two guiding blocks 4 to move towards or away from each other, which is suitable for clamping aircraft components of different sizes.

[0034] Please refer to Figure 2 and Figure 3 , The clamping member 12 is composed of an oblate metal member with a central hole and the bent portions 14 on both sides thereof. Through the oblate metal member of the clamping member 12, it is convenient to keep sleeved with the second threaded column 11. Through the bent portions 14 of the clamping member 12, it is convenient to contact and fix the aircraft components.

[0035] Please refer to Figure 1, a disc-shaped handwheel is fixedly connected to the side of the workbench 1 corresponding to the bidirectional screw 3. A ball bearing is provided at the connection between the bidirectional screw 3 and the guide groove 2. Through the settings of the ball bearing and the disc-shaped handwheel, the rotational installation of the bidirectional screw 3 is facilitated, and the adjustment of the distance between the two guide blocks 4 is convenient.

[0036] Please refer to Figures 1-3 , the radian of the arc surface 10 on the top surface of the contact block 9 is adapted to the arc surface radian of the aircraft component. Through the setting of the arc surface 10, it is easy to provide adaptive support for the arc surface of the aircraft component. In order to be applicable to aircraft components with different radian, the radian of the arc surface 10 of the contact block 9 can be prefabricated into different specifications and belong to different support members 5.

[0037] The implementation principle of this embodiment is as follows: During use, first rotate the bidirectional screw 3 installed in the guide groove 2 to cause the two guide blocks 4 with threaded holes to move towards or away from each other along the surface of the bidirectional screw 3, so that the two guide blocks 4 drive the corresponding support members 5 to move towards or away from each other respectively. Then, push the support member 5 horizontally along the workbench 1, so that the first threaded post 6 of the guide block 4 moves in the oval adjustment hole 7 on the surface of the support member 5 to adjust the position of the contact block 9, so as to adjust the positions of multiple support members 5 on the workbench 1 according to the size of the aircraft component to be clamped. When the positions of multiple support members 5 meet the size of the aircraft component to be clamped, the aircraft component is brought into contact with the contact block 9 on the support member 5, and then the wing nut 13 on the surface of the second threaded post 11 is rotated to cause the wing nut 13 to move downward to drive the clamping member 12 to move downward synchronously, so that the bent portions 14 at both ends of the clamping member 12 abut against the top surface of the aircraft component corresponding to the contact block 9. When it is necessary to clamp aircraft components with different arc surfaces, unlock the hexagon nut 8 on the surface of the first threaded post 6, disassemble this support member 5, and replace it with a support member 5 that conforms to the arc surface of the corresponding aircraft component, so that the arc surface 10 of the contact block 9 on this support member 5 matches the arc surface of the aircraft component.

[0038] The above are all the preferred embodiments of this application, and the protection scope of this application is not limited accordingly. Therefore, all equivalent changes made according to the structure, shape, and principle of this application should be covered within the protection scope of this application.

Claims

1. A clamping device for aircraft component processing and production, comprising a workbench (1), characterized in that: On the top surface of the workbench (1), two guiding grooves (2) are arranged in parallel, and two guiding blocks (4) are slidably installed in each guiding groove (2). A bidirectional screw rod (3) is rotatably installed in each of the two guiding grooves (2) of the workbench (1) through a shaft seat. The two guiding blocks (4) are respectively threadedly connected to the bidirectional screw rod (3) through threaded holes. A first threaded column (6) is welded to the top of the guiding block (4), and a support member (5) is sleeved on the surface of the first threaded column (6). A hexagonal nut (8) that abuts against the support member (5) is screwed onto the surface of the first threaded column (6). A contact block (9) is welded to the top surface of the support member (5), and an arc surface (10) is arranged on the top surface of the contact block (9). A second threaded column (11) welded to the support member (5) is arranged on the left side of the contact block (9). A holding member (12) is sleeved on the surface of the second threaded column (11), and bent portions (14) are integrally cast at both ends of the holding member (12). A wing nut (13) that contacts the holding member (12) is screwed onto the upper part of the second threaded column (11).

2. The clamping device for processing and manufacturing aircraft parts according to claim 1, wherein: An adjustment hole (7) with an oblate structure is formed on the right side of the surface of the support member (5), and the inner dimension of the adjustment hole (7) is adapted to the diameter of the first threaded column (6).

3. The clamping device for aircraft component processing and production according to claim 1, characterized in that: Two groups of threads with opposite directions are arranged on the surface of the bidirectional screw rod (3), and the two guiding blocks (4) in the guiding groove (2) are respectively connected to the two groups of threads.

4. The clamping device for processing and manufacturing aircraft parts according to claim 1, wherein: The holding member (12) is composed of an oblate metal member with a central hole and bent portions (14) on both sides thereof.

5. A clamping device for aircraft component processing and production according to claim 1, characterized in that: A disc-shaped handwheel is fixedly connected to the side surface of the workbench (1) corresponding to the bidirectional screw rod (3), and a ball bearing is arranged at the connection between the bidirectional screw rod (3) and the guiding groove (2).

6. The clamping device for aircraft component processing and production according to claim 1, wherein: The radian of the arc surface (10) on the top surface of the contact block (9) is adapted to the arc radian of the aircraft part.

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