Aviation skin cutting positioning assembly

Abstract

The utility model discloses an aviation skin cutting and positioning assembly, which belongs to the technical field of skin processing equipment, and comprises a support column, a joint piece arranged at the top of the support column and used for adjusting a horizontal deflection angle, and a connecting shaft rotationally arranged in the joint piece, the clamping device comprises a connecting shaft, a supporting arm fixed to the connecting shaft, an adjusting piece arranged on the supporting arm, the connecting shaft rotationally arranged on the adjusting piece, and a clamping part fixed to the connecting shaft and used for clamping the aviation skin. According to the clamping device, the joint piece, the adjusting piece, the two sets of connecting shafts, the limiting part and other structures are used in cooperation, the orientation angle of a clamping opening between the two clamping arms can be adjusted in a large range in a three-dimensional space, the clamping device can clamp and fix the edges of skins in various dimensions in the three-dimensional space, the aviation skins are supported in a horizontal state, and the working efficiency is improved. Therefore, skins in different dimensions can be cut conveniently, and the application range of the cutting device is widened.

Description

Technical Field

[0001] The utility model relates to the technical field of skin processing equipment, in particular to an aviation skin cutting and positioning component. Background Art

[0002] Aviation skin refers to a dimensional component that is wrapped around the aircraft frame and fixed with adhesives or rivets to form the aerodynamic shape of the aircraft. Aviation skin is generally made of metal or repositioned fiber materials, so it is generally a more three-dimensional shape and its surface is relatively flat. Existing aviation skin cutting fixtures only use multiple sets of relatively arranged fixtures to support and fix the edges of the aviation skin to facilitate cutting of the aviation skin. However, the fixtures used are generally U-shaped fixtures, and their clamps are always facing the horizontal direction, which makes it difficult to clamp and fix aviation skins of different dimensions, and it is difficult to place the dimensional aviation skins in a horizontal state.

[0003] The existing patent application number: 202120112978.2 discloses a laser cutting fixture for aircraft skin manufacturing, which clamps and fixes the aircraft skin through two sets of clamping plates arranged opposite to each other, and fixes irregular objects by installing auxiliary plates. In the above-mentioned prior art, the U-shaped clamping area enclosed by the clamping plate and the auxiliary plate in the device also has a horizontal clamping opening, and the above-mentioned technical problems still exist. Utility Model Content

[0004] The utility model aims to provide an aviation skin cutting and positioning assembly to solve the problem in the above background technology that it is difficult to clamp and fix aviation skins of different dimensions.

[0005] In order to achieve the above purpose, the utility model adopts the following technical solutions:

[0006] The utility model provides an aviation skin cutting and positioning assembly, comprising a support column and a joint member arranged on the top of the support column for adjusting the horizontal deflection angle, and the aviation skin cutting and positioning assembly also includes:

[0007] The connecting shaft disposed in the joint member is rotated.

[0008] A support arm is fixed on the connecting shaft.

[0009] An adjusting member is arranged on the supporting arm.

[0010] Rotate the connecting shaft disposed on the adjusting member.

[0011] A clamping part fixed on the connecting shaft is used to clamp the aviation skin, and the adjusting member is used to adjust the rotation angle of the clamping part along the circumference of the support arm.

[0012] Two limiting parts are respectively arranged on the two connecting shafts, and the two limiting parts are respectively used to limit and fix the positions of the support arm and the clamping part after the rotation angle is adjusted.

[0013] The limiting part comprises:

[0014] A limiting block is slidably sleeved with a limiting groove arranged on one end surface of the connecting shaft.

[0015] A through hole is provided on the other end surface of the connecting shaft, and a spring groove is provided in the connecting shaft for connecting the limiting groove and the through hole.

[0016] A tension spring is slidably sleeved in the spring groove.

[0017] A push rod is slidably sleeved in the through hole, and one end of the push rod axially passes through the interior of the spring slot and is fixed on the limit block.

[0018] An outer convex plate fixed on the limiting block.

[0019] The aviation skin cutting and positioning assembly also includes an annular tooth surface arranged on one side of the outer convex disc, and an annular tooth surface is also arranged on the planes of the joint part and the adjusting part opposite to the outer convex disc.

[0020] Furthermore, the inner diameter of the through hole is smaller than the inner diameter of the spring slot, and the inner diameter of the spring slot is smaller than the width of the limiting slot.

[0021] Furthermore, two ends of the tension spring are respectively fixed on the limit block and the inner wall of the spring slot, and the tension spring is located between the arc-shaped outer wall of the push rod and the arc-shaped inner wall of the spring slot.

[0022] Furthermore, the annular tooth surface is located between the boundary of the limiting groove and the outer convex disk, and two adjacent annular tooth surfaces are meshed with each other.

[0023] Furthermore, the joint component comprises:

[0024] A joint shaft rotatably connected to a limiting shaft hole arranged at the top of the support column.

[0025] A support frame is fixed to the top of the joint shaft, and the opposing surfaces of the support frame and the support column are both provided with limiting tooth surfaces, the two limiting tooth surfaces are meshed with each other, and one of the annular tooth surfaces is located on the support frame.

[0026] Furthermore, the joint shaft and the limiting shaft hole are in a sliding connection relationship along the axial direction.

[0027] Furthermore, the adjusting member comprises:

[0028] A screw rod is threadedly connected to a screw hole provided on the end surface of the support arm.

[0029] A connecting seat is fixed on the screw rod, and the remaining annular tooth surface is located on the connecting seat.

[0030] Furthermore, the clamping portion comprises:

[0031] A clamping seat is fixed on one of the end faces of the connecting shaft.

[0032] A clamping arm is relatively hinged in the clamping seat.

[0033] A fixed suction cup is fixed on the clamping arm, and two fixed suction cups are respectively located on opposite surfaces of the two clamping arms.

[0034] A telescopic cylinder is arranged between the clamping arm and the clamping seat, and two ends of the telescopic cylinder are respectively hinged on the clamping arm and the clamping seat.

[0035] Furthermore, the aviation skin cutting and positioning assembly also includes a base for supporting a support column, the base is provided with a plurality of insertion holes, and an insertion block is fixedly provided at the bottom of the support column, and the insertion block is inserted into the insertion hole.

[0036] Compared with the prior art, one or more of the above technical solutions have the following beneficial effects:

[0037] 1. The utility model can adjust the angle of the clamping opening between the two clamping arms in a wide range in three-dimensional space through the mutual cooperation of the joint parts, the adjusting parts, the two sets of connecting shafts and the limiting parts, so that the utility model can clamp and fix the edges of various dimensional skins in three-dimensional space, and lift the aviation skin in a horizontal state, so as to facilitate the cutting of skins of different dimensional shapes, thereby expanding its scope of application;

[0038] 2. The utility model uses a plurality of sockets on the base in conjunction with the plug blocks at the bottom of the support column. The position of the clamping part can be flexibly arranged on the base according to the contour of the skin. In conjunction with the use of structures such as joints, adjustment parts, two sets of connecting shafts and limit parts, the position of the clamping part can be flexibly adjusted in space so that it can fit the edge trend of the aviation skin. The skin can be adsorbed and clamped by a fixed suction cup, thereby improving the clamping and fixing effect without affecting its shape. BRIEF DESCRIPTION OF THE DRAWINGS

[0039] Figure 1 It is an axonometric drawing of the utility model;

[0040] Figure 2 It is a partial axonometric drawing of the utility model;

[0041] Figure 3 It is an axonometric view of the joint member in the utility model;

[0042] Figure 4 It is an axonometric view of the clamping part in the utility model;

[0043] Figure 5 for Figure 4 Enlarged view of part A.

[0044] In the figure: 1. base; 2. socket; 3. plug block; 4. support column; 5. joint part; 51. limit shaft hole; 52. joint shaft; 53. support frame; 54. limit tooth surface; 6. support arm; 7. adjustment part; 71. screw hole; 72. screw rod; 73. connecting seat; 8. clamping part; 81. clamping seat; 82. clamping arm; 83. fixed suction cup; 84. telescopic cylinder; 9. limit part; 91. limit groove; 92. limit block; 93. through hole; 94. spring groove; 95. push rod; 96. tension spring; 97. outer convex disc; 10. connecting shaft; 11. annular tooth surface. DETAILED DESCRIPTION

[0045] In order to enable those skilled in the art to better understand the solution of the present application, the technical solution in the embodiments of the present application will be clearly and completely described below in conjunction with the drawings in the embodiments of the present application.

[0046] like Figures 1 to 5 As shown, an aviation skin cutting and positioning assembly includes a support column 4 and a joint 5 disposed on the top of the support column 4 for adjusting the horizontal deflection angle. The aviation skin cutting and positioning assembly also includes:

[0047] The connecting shaft 10 disposed in the joint component 5 is rotated.

[0048] The support arm 6 is fixed on the connecting shaft 10.

[0049] An adjusting member 7 is arranged on the supporting arm 6 .

[0050] The connecting shaft 10 disposed on the adjusting member 7 is rotated.

[0051] The clamping part 8 fixed on the connecting shaft 10 is used for clamping the aviation skin, and the adjusting member 7 is used for adjusting the rotation angle of the clamping part 8 along the circumferential direction of the supporting arm 6 .

[0052] Two limiting parts 9 are respectively arranged on the two connecting shafts 10, and the two limiting parts 9 are respectively used to limit and fix the positions of the supporting arm 6 and the clamping part 8 after the rotation angle is adjusted.

[0053] By adjusting the rotation angle of the support arm 6 in the horizontal direction through the joint part 5, and cooperating with the connecting shaft 10 set between the support arm 6 and the joint part 5, the deflection angle of the support arm 6 can be adjusted in the vertical direction, so that the support arm 6 can drive the clamping part 8 to move to several three-dimensional space coordinates within a certain three-dimensional space, and then the opening direction of the clamping part 8 is adjusted along the circumference of the support arm 6 through the adjustment part 7, and cooperating with the connecting shaft 10 between the adjustment part 7 and the clamping part 8, the opening direction of the clamping part 8 can be arbitrarily adjusted in the three-dimensional space. With such a design, since the shape of the aviation skin is three-dimensional, its boundaries may have different three-dimensional inclination angles, and it is difficult for a general U-shaped clamping assembly to use a smaller number of clamping assemblies without affecting its shape. If the parts are used to position and fix it, the clamping assembly may not fit the surface trend of the aviation skin, and the clamping and fixing effect may be poor. However, through the joint use of the joint parts 5, the adjustment parts 7, the two connecting shafts 10 and the two sets of limiting parts 9, it can not only highly fit the surface trend of the aviation skin without affecting its shape, so as to position and clamp it, but also keep it in a horizontal state, be lifted up and fixed firmly, so as to facilitate the efficient and smooth subsequent cutting operations. When a piece of aviation skin is cut into multiple independent pieces of aviation skin, each piece of aviation skin can be cut without position change, which will not interfere with the subsequent cutting operation of the same piece of aviation skin, thereby improving the positioning, clamping and fixing effect of the aviation skin before cutting.

[0054] The limiting part 9 includes:

[0055] A limiting block 92 is slidably sleeved with a limiting groove 91 provided on one end surface of the connecting shaft 10 .

[0056] A through hole 93 is provided on the other end surface of the connecting shaft 10 , and a spring groove 94 is provided in the connecting shaft 10 for connecting the limiting groove 91 and the through hole 93 .

[0057] A tension spring 96 is slidably sleeved in the spring slot 94 .

[0058] A push rod 95 is slidably sleeved in the through hole 93 , and one end of the push rod 95 axially passes through the spring slot 94 and is fixed on the limit block 92 .

[0059] An outer convex plate 97 fixed on the limiting block 92 .

[0060] The aviation skin cutting and positioning assembly also includes an annular tooth surface 11 arranged on one side of the outer convex disc 97 , and an annular tooth surface 11 is also arranged on the planes of the joint member 5 and the adjusting member 7 opposite to the outer convex disc 97 .

[0061] After the deflection angle of the support arm 6 or the clamping part 8 is adjusted by the connecting shaft 10, the side of the push rod 95 away from the limit block 92 can be pressed laterally along the circumference of the connecting shaft 10, so that the limit block 92 and the outer convex plate 97 are pushed out to the outside of the limit groove 91 for a certain distance, and in this process, the tension spring 96 is stretched and deformed, so that the annular tooth surface 11 on the outer convex plate 97 is separated from the annular tooth surface 11 on the joint part 5 or the adjusting part 7, and the action of pressing the push rod 95 is maintained. At the same time, the support arm 6 or the clamping part 8 is deflected to the required angular position, and the deflection is adjusted by using the push rod 95. Hold the support arm 6 or the clamping part 8 with your hand, and then release the hand pressing the push rod 95. Under the elastic force of the tension spring 96, the push rod 95, the limit block 92 and the outer convex plate 97 are reset, and the annular tooth surface 11 on the outer convex plate 97 is engaged with the annular tooth surface 11 on the joint part 5 or the adjusting part 7, so as to restrict the circumferential freedom of the connecting shaft 10, so that the support arm 6 or the clamping part 8 keeps its position, which is convenient for clamping and fixing the aviation skin, and can prevent the aviation skin from shifting in position after clamping and fixing, thereby affecting the cutting accuracy, or causing the problem of falling and deformation after cutting.

[0062] In this embodiment, the inner diameter of the through hole 93 is smaller than the inner diameter of the spring groove 94, and the inner diameter of the spring groove 94 is smaller than the width of the limiting groove 91. Such a design can flexibly release the circumferential freedom constraint of the limiting portion 9 on the connecting shaft 10, and facilitate the circumferential rotation of the connecting shaft. After the connecting shaft 10 is adjusted in circumferential rotation, the elastic force of the tension spring 96 is used to reset the limiting portion 9, so that the connecting shaft 10 remains fixed in the state after the rotation adjustment, thereby improving the fixing effect of the connecting shaft 10.

[0063] In this embodiment, the two ends of the tension spring 96 are respectively fixed on the limit block 92 and the inner wall of the spring groove 94, and the tension spring 96 is located between the arc-shaped outer wall of the push rod 95 and the arc-shaped inner wall of the spring groove 94. Such a design can avoid pushing the push rod 95 excessively into the through hole 93 when operating the limit part 9 to release the circumferential freedom of the connecting shaft 10, thereby affecting the normal resetting action of the limit part 9.

[0064] In this embodiment, the annular tooth surface 11 is located between the boundary of the limiting groove 91 and the outer convex plate 97, and two adjacent annular tooth surfaces 11 are meshed with each other. The limiting effect of the annular tooth surfaces 11 when meshing is utilized to realize the constraint of the circumferential degree of freedom of the connecting shaft 10, so as to facilitate the flexible adjustment of the deflection angle of the support arm 6 or the clamping part 8, so that the clamping part 8 can maintain a high degree of fit with the surface trend of the aviation skin, thereby improving its positioning, clamping and fixing effect without affecting its shape.

[0065] In this embodiment, the joint component 5 includes:

[0066] A joint shaft 52 rotatably connected to a limiting shaft hole 51 provided at the top of the support column 4 .

[0067] A support frame 53 is fixed to the top of the joint shaft 52, and limiting tooth surfaces 54 are provided on the opposite surfaces of the support frame 53 and the support column 4. The two limiting tooth surfaces 54 are meshed with each other, and one of the annular tooth surfaces 11 is located on the support frame 53. The joint shaft 52 and the limiting shaft hole 51 are in an axial sliding connection relationship. With such a design, the two limiting tooth surfaces 54 can be separated by pulling up the support frame 53 or the support arm 6, and then the support frame 53 or the support arm 6 can be directly pulled up so that the axis of the connecting shaft 10 between the two points to the desired angle, and the hand that pulls up the support frame 53 or the support arm 6 is released to reset it under the action of gravity, so that the two limiting tooth surfaces 54 are re-meshed and the circumferential freedom of the joint shaft 52 is constrained, which is consistent with the function of the limiting part 9.

[0068] In this embodiment, the adjusting member 7 includes:

[0069] A screw rod 72 is threadedly connected to a screw hole 71 provided on the end surface of the support arm 6 .

[0070] The connecting seat 73 is fixed on the screw rod 72, and the remaining annular tooth surface 11 is located on the connecting seat 73. The connecting seat 73 can be twisted circumferentially to adjust the axial deflection angle of the connecting shaft 10 between the clamping portion 8 and the connecting seat 73. The connecting seat 73 can also be twisted circumferentially for multiple turns to extend the clamping portion 8 outward to expand the position adjustment range of the clamping portion 8. Through the coordinated use of the adjusting member 7 and the connecting shaft 10, the clamping direction of the clamping portion 8 can be adjusted at multiple angles in three-dimensional space, so that it can be clamped to the boundary of the aviation skin from any direction, so that it is highly consistent with the boundary trend of the aviation skin, and the clamping portion 8 is prevented from deforming the aviation skin when clamping and fixing it, thereby affecting the subsequent cutting accuracy. Through the use of the joint member 5, the adjusting member 7, the two connecting shafts 10 and the two sets of limiting portions 9, the angle adjustment flexibility of the clamping portion 8 in three-dimensional space is greatly improved, the adjustment blind angle range of its angle and spatial position is reduced, and its clamping and use range for aviation skins of different dimensions is expanded.

[0071] In this embodiment, the clamping portion 8 includes:

[0072] A clamping seat 81 is fixed on the end surface of one of the connecting shafts 10 .

[0073] The clamping arm 82 is relatively hinged in the clamping seat 81.

[0074] The fixed suction cup 83 is fixed on the clamping arm 82 , and the two fixed suction cups 83 are respectively located on opposite surfaces of the two clamping arms 82 .

[0075] The telescopic cylinder 84 is arranged between the clamping arm 82 and the clamping seat 81, and the two ends of the telescopic cylinder 84 are respectively hinged on the clamping arm 82 and the clamping seat 81. Through the coordinated adjustment of the joint part 5, the adjustment part 7, and the two connecting shafts 10, the clamping direction between the two clamping arms 82 can be adjusted to any angle in three-dimensional space, so that it can be highly consistent with the boundary trend of the dimensional aviation skin, and the fixed suction cup 83 can fit the surface undulation of the aviation skin to avoid deformation of the aviation skin caused by the clamping pressure. The flexible fixed suction cup 83 can buffer the pressure when it contacts the aviation skin, and increase the friction and suction between it and the surface of the aviation skin, thereby improving the clamping and fixing stability and firmness of the aviation skin.

[0076] In this embodiment, the aviation skin cutting and positioning assembly also includes a base 1 for supporting the support column 4, and a plurality of sockets 2 are provided on the base 1. A plug block 3 is fixedly provided at the bottom of the support column 4, and the plug block 3 is plugged into the socket 2. With such a design, the position of the support column 4 on the base 1 can be replaced by plugging and unplugging. The operation is simple and efficient, and will not affect the clamping and fixing effect of the aviation skin, so that aviation skins of different sizes can be clamped and fixed, thereby further improving its scope of application.

[0077] The above description is only the preferred embodiment of the utility model, and the parts not described in the utility model can be implemented by adopting or drawing on existing technologies. Of course, the above description is not a limitation of the utility model, and the utility model is not limited to the above examples. The changes, modifications, additions or substitutions made by technicians in this technical field within the essential scope of the utility model should also fall within the protection scope of the utility model.

Claims

1. An aviation skin cutting and positioning assembly, comprising a support column (4) and a joint (5) arranged on the top of the support column (4) for adjusting the horizontal deflection angle, characterized in that: The aviation skin cutting and positioning assembly also includes: Rotating a connecting shaft (10) disposed in the joint component (5); A support arm (6) fixed on the connecting shaft (10); an adjusting member (7) disposed on the supporting arm (6); Rotating a connecting shaft (10) disposed on the adjusting member (7); A clamping portion (8) fixed on the connecting shaft (10) for clamping the aviation skin, and the adjusting member (7) is used to adjust the rotation angle of the clamping portion (8) along the circumference of the support arm (6); Two limiting parts (9) are respectively arranged on the two connecting shafts (10), and the two limiting parts (9) are respectively used to limit and fix the positions of the support arm (6) and the clamping part (8) after the rotation angle is adjusted; The limiting portion (9) comprises: A limiting block (92) slidably sleeved with a limiting groove (91) provided on one end surface of the connecting shaft (10); A through hole (93) is provided on the other end surface of the connecting shaft (10), and a spring groove (94) is provided in the connecting shaft (10) for connecting the limiting groove (91) and the through hole (93); A tension spring (96) slidably sleeved in the spring groove (94); a push rod (95) slidably sleeved in the through hole (93), one end of the push rod (95) axially passing through the interior of the spring slot (94) and fixed on the limit block (92); An outer convex plate (97) fixed on the limiting block (92); The aviation skin cutting and positioning assembly also includes an annular tooth surface (11) arranged on one side of the outer convex disc (97), and an annular tooth surface (11) is also arranged on the plane of the joint part (5) and the adjustment part (7) opposite to the outer convex disc (97).

2. The aviation skin cutting and positioning assembly according to claim 1, characterized in that: The inner diameter of the through hole (93) is smaller than the inner diameter of the spring groove (94), and the inner diameter of the spring groove (94) is smaller than the width of the limiting groove (91).

3. The aviation skin cutting and positioning assembly according to claim 2, characterized in that: The two ends of the tension spring (96) are respectively fixed on the limit block (92) and the inner wall of the spring slot (94), and the tension spring (96) is located between the arc-shaped outer wall of the push rod (95) and the arc-shaped inner wall of the spring slot (94).

4. The aviation skin cutting and positioning assembly according to claim 3, characterized in that: The annular tooth surface (11) is located between the boundary of the limiting groove (91) and the outer convex plate (97), and two adjacent annular tooth surfaces (11) are meshed with each other.

5. The aviation skin cutting and positioning assembly according to claim 4, characterized in that: The joint component (5) comprises: A joint shaft (52) rotatably connected to a limiting shaft hole (51) provided at the top of the support column (4); A support frame (53) is fixed to the top of the joint shaft (52), and the support frame (53) and the support column (4) are provided with limiting tooth surfaces (54) on their opposite surfaces, and the two limiting tooth surfaces (54) are meshed with each other, and one of the annular tooth surfaces (11) is located on the support frame (53).

6. The aviation skin cutting and positioning assembly according to claim 5, characterized in that: The joint shaft (52) and the limiting shaft hole (51) are in a sliding connection relationship along the axial direction.

7. The aviation skin cutting and positioning assembly according to claim 6, characterized in that: The adjusting member (7) comprises: a screw rod (72) threadedly connected to a screw hole (71) provided on an end surface of the support arm (6); A connecting seat (73) is fixed on the screw rod (72), and the remaining annular tooth surface (11) is located on the connecting seat (73).

8. The aviation skin cutting and positioning assembly according to claim 7, characterized in that: The clamping portion (8) comprises: A clamping seat (81) fixed on an end surface of one of the connecting shafts (10); A clamping arm (82) relatively hinged to the clamping seat (81); A fixed suction cup (83) fixed on the clamping arm (82), wherein the two fixed suction cups (83) are respectively located on opposite surfaces of the two clamping arms (82); A telescopic cylinder (84) is arranged between the clamping arm (82) and the clamping seat (81), and two ends of the telescopic cylinder (84) are respectively hinged on the clamping arm (82) and the clamping seat (81).

9. The aviation skin cutting and positioning assembly according to claim 8, characterized in that: The aviation skin cutting and positioning assembly also includes a base (1) for supporting a support column (4), the base (1) is provided with a plurality of insertion holes (2), an insertion block (3) is fixedly provided at the bottom of the support column (4), and the insertion block (3) is inserted into the insertion hole (2).

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