Quick remodeling device for aircraft structural part machining

Abstract

The quick remodeling device for machining the aircraft structural parts comprises a cuboid clamping part, a first through hole is formed in the center of the clamping part, a plurality of L-shaped first pressing assemblies are connected to the surface of the clamping part, the first pressing assemblies are symmetrically arranged relative to the first through hole, and the adjacent first pressing assemblies are arranged in parallel; l-shaped locking pieces are fixedly connected to the connecting positions of the side walls of the clamping pieces, a plurality of second pressing assemblies are fixedly connected to the locking pieces, the adjacent second pressing assemblies are perpendicularly arranged, and supporting leg assemblies are arranged on the other surfaces of the clamping pieces. The quick remodeling device for machining the aircraft structural parts solves the problems that an existing quick remodeling device for machining the aircraft structural parts is poor in strength at the connecting position and prone to loosening when encountering high-frequency vibration impact of machining.

Description

Technical Field

[0001] The utility model belongs to the technical field of mechanical processing rapid mold change device structure design, in particular to a rapid mold change device used for machining aircraft structural parts. Background Art

[0002] In modern manufacturing, tooling refers to devices used to fix, clamp, position and support parts. It plays a vital role in the production and processing process. Tooling manufacturing is of great significance to improving production efficiency, ensuring product quality and reducing production costs. In the actual processing and manufacturing process of aircraft parts, most complex structural parts need to be positioned and clamped using tooling. In the prior art, the rapid mold change device for aircraft structural parts processing often adopts a fixed design. Under this requirement, the rapid mold change device is difficult to process. In the prior art, the strength of the connection of the rapid mold change device itself is poor, and it is easy to loosen when encountering high-frequency vibration impact of mechanical processing during use. Utility Model Content

[0003] The utility model aims to provide a rapid mold-changing device for machining aircraft structural parts, which solves the problem that the connection of the existing rapid mold-changing device for machining aircraft structural parts has poor strength and is easy to loosen when encountering high-frequency vibration impact during machining.

[0004] The technical solution adopted by the utility model is: it includes a rectangular clamping member 1, a first through hole 2 is opened at the center of the clamping member 1, a plurality of L-shaped first clamping components 3 are connected to the surface of the clamping member 1, the plurality of first clamping components 3 are symmetrically arranged about the first through hole 2, and adjacent first clamping components 3 are arranged in parallel; an L-shaped locking piece 4 is fixedly connected to the side wall connection of the clamping member 1, a plurality of second clamping components 5 are fixedly connected to the locking piece 4, and adjacent second clamping components 5 are arranged vertically; a leg component 6 is provided on the other surface of the clamping member 1.

[0005] The utility model is also characterized in that:

[0006] The leg assembly 6 includes a first support block 601, a second support block 602 is arranged beside the first support block 601, a first semi-square hole 603 is opened in the horizontal direction on the side of the first support block 601 close to the second support block 602, a second semi-square hole 604 is opened in the horizontal direction on the side of the second support block 602 close to the first support block 601, the first semi-square hole 603 is opposite to the second semi-square hole 604, a third support block 605 is attached to the upper surface of the first support block 601, the third support block 605 is in contact with the lower surface of the square clamp 1, a fourth support block 606 is attached to the upper surface of the second support block 602, the third support block 605 is in contact with the lower surface of the clamp 1, and a first fastening bolt 6 is threadedly connected to the side of the upper surface of the third support block 605 away from the fourth support block 606 07, the first fastening bolt 607 passes through the third support block 605 and the first support block 601 in sequence along the vertical direction, the second fastening bolt 608 is threadedly connected to the side of the upper surface of the fourth support block 606 away from the third support block 605, the second fastening bolt 608 passes through the fourth support block 606 and the second support block 602 in sequence along the vertical direction, the side of the upper surface of the fourth support block 606 close to the third support block 605 is provided with a first half-waist-shaped groove 609 in the vertical direction, the side of the upper surface of the third support block 605 close to the fourth support block 606 is provided with a second half-waist-shaped groove 610 in the vertical direction, the first half-waist-shaped groove 609 and the second half-waist-shaped groove 610 are arranged opposite to each other, and the first half-waist-shaped groove 609 and the second half-waist-shaped groove 610 are matched with a waist-shaped connecting piece 611;

[0007] The first clamping assembly 3 includes a first support plate 301, one end of the first support plate 301 is fixedly connected to the upper surface of the clamping member 1, the other end of the first support plate 301 is fixedly connected to a first auxiliary support block 302 in the vertical direction, a first screw hole 303 is provided on the upper surface of the first support plate 301, a first clamping screw 304 is fitted in the first screw hole 303, and the first clamping screw 304 is threadedly connected to a first fastening nut 305;

[0008] The second clamping assembly 5 includes a second support plate 501, one end of the second support plate 501 is fixedly connected to the upper surface of the locking plate 4, the other end of the second support plate 501 is fixedly connected to a second auxiliary support block 502 in the vertical direction, a second screw hole 503 is provided on the upper surface of the second support plate 501, a second clamping screw 504 is matched in the second screw hole 503, and the second clamping screw 504 is threadedly connected to a second fastening nut 505;

[0009] A first anti-loosening washer 612 is disposed between the first fastening bolt 607 and the third supporting block 605 , and a second anti-loosening washer 613 is disposed between the second fastening bolt 608 and the fourth supporting block 606 .

[0010] The beneficial effects of the utility model are as follows: the utility model is a quick mold-changing device for processing aircraft structural parts, which solves the problem of great difficulty in processing the quick mold-changing device in the prior art by splitting the quick mold-changing device for processing aircraft structural parts into a clamping part and a leg assembly. In addition, the leg assembly of the utility model adopts a mortise and tenon structure design, and utilizes bolts and anti-loosening washers for fastening and installation, thereby enhancing the strength of the quick mold-changing device itself and the stability of its function. BRIEF DESCRIPTION OF THE DRAWINGS

[0011] Figure 1 This is a schematic diagram of the structure of the rapid mold change device used for machining aircraft structural parts of the utility model;

[0012] Figure 2 This is a schematic diagram of the structure of the clamping parts of the quick-change device for machining aircraft structural parts of the utility model;

[0013] Figure 3 This is a schematic diagram of the structure of the leg assembly of the quick-change device for machining aircraft structural parts of the utility model;

[0014] Figure 4 This is the AA sectional view of the leg assembly of the quick-change device for machining aircraft structural parts of the utility model;

[0015] Figure 5 This is a schematic diagram of the structure of the first clamping assembly of the quick-change device for machining aircraft structural parts of the utility model;

[0016] Figure 6 The utility model is a schematic diagram of the structure of the second clamping assembly of the rapid mold change device used for machining aircraft structural parts.

[0017] In the figure, 1. clamping member, 2. first through hole, 3. first clamping assembly, 301. first support plate, 302. first auxiliary support block, 303. first screw hole, 304. first clamping screw, 305. first fastening nut, 4. locking plate, 5. second clamping assembly, 501. second support plate, 502. second auxiliary support block, 503. second screw hole, 504. second clamping screw, 505. second fastening nut, 6. leg assembly, 601. first support block, 602. second support block, 603. first semi-square hole, 604. second semi-square hole, 605. third support block, 606. fourth support block, 607. first fastening bolt, 608. second fastening bolt, 609. first semi-waist-shaped groove, 610. second semi-waist-shaped groove, 611. waist-shaped connecting piece, 612. first anti-loosening washer, 613. second anti-loosening washer. DETAILED DESCRIPTION

[0018] The utility model is described in detail below with reference to the accompanying drawings and specific implementation modes.

[0019] like Figure 1 , Figure 2 As shown, a quick-change device for machining aircraft structural parts comprises a rectangular clamping member 1, which is an important part of the quick-change device for machining aircraft structural parts. A first through hole 2 is provided at the center of the clamping member 1, and a plurality of L-shaped first clamping assemblies 3 are connected to the surface of the clamping member 1 along the length direction. The lateral sides of the first clamping assemblies 3 are in contact with the surface of the clamping member 1, and the plurality of first clamping assemblies 3 are symmetrically arranged about the first through hole 2. An L-shaped locking piece 4 is fixedly connected to the side wall connection of the clamping member 1, and the locking piece 4 is perpendicularly arranged to the side edge of the clamping member 1. Two second clamping assemblies 5 are fixedly connected to each locking piece 4, and the plurality of second clamping assemblies 5 are not in the same plane. A leg assembly 6 is provided on the other surface of the clamping member 1.

[0020] like Figure 3 , Figure 4 As shown, the leg assembly 6 of the quick-change device for processing aircraft structural parts includes a first support block 601, the cross section of the first support block 601 is arc-shaped, a second support block 602 is arranged beside the first support block 601, the first support block 601 and the second support block 602 are equal in size and shape, a first semi-square hole 603 is opened in the horizontal direction on the side of the first support block 601 close to the second support block 602, a second semi-square hole 604 is opened in the horizontal direction on the side of the second support block 602 close to the first support block 601, the first semi-square hole 603 and the second semi-square hole 604 are opposite to each other, a third support block 605 is attached to the upper surface of the first support block 601, and the third support block 605 is in contact with the lower surface of the clamp 1, and a fourth support block 606 is attached to the upper surface of the second support block, and the third support block 605 is in contact with the lower surface of the clamp 1 Surface contact, the third support block 605 is threadedly connected to the side away from the fourth support block 606 with a first fastening bolt 607, the first fastening bolt 607 penetrates the third support block 605 and the first support block 601 in sequence along the vertical direction, the fourth support block is threadedly connected to the side away from the third support block 605 with a second fastening bolt 608, the second fastening bolt 608 penetrates the fourth support block 606 and the second support block 602 in sequence along the vertical direction, the fourth support block 606 has a first semi-waist-shaped groove 609 on the side close to the third support block 605 on the upper surface along the vertical direction, the third support block 605 has a second semi-waist-shaped groove 610 on the side close to the fourth support block 606 on the upper surface along the vertical direction, the first semi-waist-shaped groove 609 and the second semi-waist-shaped groove 610 are arranged with opposite notches, and are matched with a waist-shaped connecting piece 611.

[0021] like Figure 5As shown, the first clamping assembly 3 includes a first support plate 301, one end of the first support plate 301 is fixedly connected to the upper surface of the clamping member 1, and the other end of the first support plate 301 is fixedly connected to a first auxiliary support block 302 along the vertical direction. A first screw hole 303 is provided on the upper surface of the first support plate 301, and a first clamping screw 304 is fitted in the first screw hole 303. The first clamping screw 304 is threadedly connected to a first fastening nut 305.

[0022] The working principle of the quick-changing device for machining aircraft structural parts of the utility model is as follows: first, a traveling crane is used to lift the aircraft structural part to be machined to a certain height above the working table of a numerical control machine tool, so that the aircraft structural part is suspended in the air, and the leg assembly 6 is placed at a suitable position below the suspended aircraft structural part, and the crane is started again to adjust the posture of the aircraft structural part, and then the aircraft structural part is lowered so that the aircraft structural part is completely seated on the four leg assemblies 6, and the clamping member 1 is placed on the leg assembly so that the leg assembly and the clamping member 1 cooperate, and the aircraft structural part passes through the through hole 2 provided on the clamping member 1, and a dial indicator is used to align the XYZ direction of machining the aircraft structural part, specifically, a plane on the aircraft structural part is selected as a reference plane, the dial indicator head is lightly touched to the plane, the aircraft structural part is moved, and the reading change of the dial indicator is observed, and the position of the aircraft structural part is adjusted according to the reading of the dial indicator until the dial indicator shows that the aircraft structural part has no offset in this direction, and the dial indicator is selected. Another plane on the aircraft structure is used as a reference plane, the dial indicator head is lightly touched to the plane, the part is moved, and the reading change of the dial indicator is observed. The position of the part is adjusted according to the reading of the dial indicator until the dial indicator shows that there is no offset in this direction on the aircraft structure. A vertical plane or end face on the aircraft structure is selected as a reference plane, the dial indicator head is lightly touched to the plane, the aircraft structure is moved, and the reading change of the dial indicator is observed until the dial indicator shows that there is no offset in this direction on the aircraft structure. Then the first fastening nut 305 and the second fastening nut 505 are rotated so that the first support plate 301 and the second support plate 501 press the aircraft structure. Then the dial indicator is used again to align the processing XYZ direction of the part. If there is no error, L-shaped locking plates 4 are fixed on the four vertical edges of the clamp 1. Then, the exposed device portion of the part is subjected to rough and fine processing, and the inner and outer contours of the part, the inner and outer annular grooves, and the top surface features of the part can be processed.

[0023] Example 1

[0024] A quick-change device for processing aircraft structural parts includes a rectangular clamping member 1, a first through hole 2 is opened at the center of the clamping member 1, a plurality of L-shaped first clamping components 3 are connected to the surface of the clamping member 1 along the length direction, the lateral sides of the first clamping components 3 are in contact with the surface of the clamping member 1, the plurality of first clamping components 3 are symmetrically arranged about the first through hole 2, an L-shaped locking piece 4 is fixedly connected to the side wall connection of the clamping member 1, the locking piece 4 is perpendicularly arranged to the side edge of the clamping member 1, each locking piece 4 is fixedly connected to two second clamping components 5, the plurality of second clamping components 5 are not in the same plane, and a leg component 6 is provided on the other surface of the clamping member 1.

[0025] Example 2

[0026] The rapid changeover device for processing aircraft structural parts comprises a rectangular clamping part 1, a first through hole 2 is opened at the center of the clamping part 1, a plurality of L-shaped first clamping components 3 are connected to the surface of the clamping part 1 along the length direction, the lateral sides of the first clamping components 3 are in contact with the surface of the clamping part 1, the plurality of first clamping components 3 are symmetrically arranged about the first through hole 2, an L-shaped locking piece 4 is fixedly connected to the side wall connection of the clamping part 1, the locking piece 4 is vertically arranged to the side edge of the clamping part 1, each locking piece 4 is fixedly connected to two second clamping components 5, and the plurality of second The clamping assembly 5 is not in the same plane, and a leg assembly 6 is provided on the other surface of the clamping member 1; the leg assembly 6 includes a first support block 601, a second support block 602 is provided next to the first support block 601, a first semi-square hole 603 is provided on the side of the first support block 601 close to the second support block 602 along the horizontal direction, and a second semi-square hole 604 is provided on the side of the second support block 602 close to the first support block 601 along the horizontal direction, the first semi-square hole 603 is opposite to the second semi-square hole 604, and the upper surface of the first support block 601 The upper surface of the second support block is attached with a third support block 605, and the third support block 605 contacts the lower surface of the cube clamping member 1. The upper surface of the second support block is attached with a fourth support block 606, and the third support block 605 contacts the lower surface of the cube clamping member 1. The upper surface of the third support block 605 is far from the fourth support block 606. The side of the first fastening bolt 607 is threadedly connected. The first fastening bolt 607 passes through the third support block 605 and the first support block 601 in sequence along the vertical direction. The side of the upper surface of the fourth support block away from the third support block 606 is threadedly connected. A second fastening bolt 608 is connected, and the second fastening bolt 608 passes through the fourth support block 606 and the second support block 602 in sequence along the vertical direction. A first semi-waist-shaped groove 609 is opened in the vertical direction on one side of the upper surface of the fourth support block 606 close to the third support block 605, and a second semi-waist-shaped groove 610 is opened in the vertical direction on one side of the upper surface of the third support block 605 close to the fourth support block 606. The first semi-waist-shaped groove 609 and the second semi-waist-shaped groove 610 are arranged with opposite notches, and are matched with a waist-shaped connecting piece 611 inside.

[0027] Example 3

[0028] A quick-change device for processing aircraft structural parts comprises a rectangular clamping part 1, a first through hole 2 is opened at the center of the clamping part 1, a plurality of L-shaped first clamping components 3 are connected to the surface of the clamping part 1 along the length direction, the lateral sides of the first clamping components 3 are in contact with the surface of the clamping part 1, the plurality of first clamping components 3 are symmetrically arranged about the first through hole 2, an L-shaped locking piece 4 is fixedly connected to the side wall connection of the clamping part 1, the locking piece 4 is vertically arranged to the side edge of the clamping part 1, each locking piece 4 is fixedly connected to two second clamping components 5, the plurality of second clamping components 5 are not in the same plane, and a leg assembly 6 is arranged on the other surface of the clamping part 1; the leg assembly 6 includes The first support block 601 includes a first support block 601, a second support block 602 is disposed beside the first support block 601, a first semi-square hole 603 is provided on a side of the first support block 601 close to the second support block 602 along the horizontal direction, a second semi-square hole 604 is provided on a side of the second support block 602 close to the first support block 601 along the horizontal direction, the first semi-square hole 603 is opposite to the second semi-square hole 604, a third support block 605 is attached to the upper surface of the first support block 601, the third support block 605 is in contact with the lower surface of the cube clamp 1, a fourth support block 606 is attached to the upper surface of the second support block, the third support block 605 is in contact with the lower surface of the cube clamp 1 The lower surface of the holder 1 is in contact with the first support block 605, and the first fastening bolt 607 is threadedly connected to the side of the upper surface of the third support block 605 away from the fourth support block 606. The first fastening bolt 607 penetrates the third support block 605 and the first support block 601 in sequence along the vertical direction. The second fastening bolt 608 is threadedly connected to the side of the upper surface of the fourth support block away from the third support block 605. The second fastening bolt 608 penetrates the fourth support block 606 and the second support block 602 in sequence along the vertical direction. The first half-waist groove 609 is opened on the upper surface of the fourth support block 606 close to the third support block 605 in the vertical direction. A second semi-waist-shaped groove 610 is provided on one side of the surface close to the fourth support block 606 in the vertical direction. The first semi-waist-shaped groove 609 and the second semi-waist-shaped groove 610 are arranged with their notches opposite to each other and are matched with a waist-shaped connecting piece 611. The first clamping assembly 3 includes a first support plate 301. One end of the first support plate 301 is fixedly connected to the upper surface of the clamping piece 1. The other end of the first support plate 301 is fixedly connected to the first auxiliary support block 302 in the vertical direction. A first screw hole 303 is provided on the upper surface of the first support plate 301. A first clamping screw 304 is matched in the first screw hole 303. The first clamping screw 304 is threadedly connected with a first fastening nut 305.

Claims

1. A rapid changeover device for machining aircraft structural parts, characterized in that: The invention comprises a rectangular clamping member (1), wherein a first through hole (2) is provided at the center of the clamping member (1), and a plurality of L-shaped first clamping assemblies (3) are connected to the surface of the clamping member (1), wherein the plurality of first clamping assemblies (3) are symmetrically arranged about the first through hole (2), and adjacent first clamping assemblies (3) are arranged in parallel; an L-shaped locking plate (4) is fixedly connected to the side wall connection of the clamping member (1), and a plurality of second clamping assemblies (5) are fixedly connected to the locking plate (4), and adjacent second clamping assemblies (5) are arranged vertically; and a leg assembly (6) is provided on the other surface of the clamping member (1).

2. The rapid mold change device for machining aircraft structural parts according to claim 1, characterized in that: The leg assembly (6) comprises a first support block (601), a second support block (602) is arranged beside the first support block (601), a first semi-square hole (603) is opened in the horizontal direction on a side of the first support block (601) close to the second support block (602), a second semi-square hole (604) is opened in the horizontal direction on a side of the second support block (602) close to the first support block (601), the first semi-square hole (603) and the second semi-square hole (604) are opposite to each other, a third support block (605) is attached to the upper surface of the first support block (601), the third support block (605) is in contact with the lower surface of the square clamp (1), a fourth support block (606) is attached to the upper surface of the second support block (602), the third support block (605) is in contact with the lower surface of the clamp (1), and a first threaded connection is arranged on the upper surface of the third support block (605) away from the fourth support block (606). A fastening bolt (607) is provided, wherein the first fastening bolt (607) sequentially penetrates the third support block (605) and the first support block (601) in a vertical direction, and a second fastening bolt (608) is threadedly connected to the upper surface of the fourth support block (606) on a side away from the third support block (605), and the second fastening bolt (608) sequentially penetrates the fourth support block (606) and the second support block (602) in a vertical direction, and the upper surface of the fourth support block (606) is threadedly connected to the second support block (602) on a side away from the third support block (605). A first half-waist-shaped groove (609) is provided in the vertical direction on one side of the surface close to the third support block (605), and a second half-waist-shaped groove (610) is provided in the vertical direction on one side of the upper surface of the third support block (605) close to the fourth support block (606). The first half-waist-shaped groove (609) and the second half-waist-shaped groove (610) are arranged opposite to each other, and waist-shaped connecting pieces (611) are matched in the first half-waist-shaped groove (609) and the second half-waist-shaped groove (610).

3. The rapid mold change device for machining aircraft structural parts according to claim 1, characterized in that: The first clamping assembly (3) comprises a first support plate (301), one end of the first support plate (301) is fixedly connected to the upper surface of the clamping member (1), the other end of the first support plate (301) is fixedly connected to a first auxiliary support block (302) in a vertical direction, a first screw hole (303) is provided on the upper surface of the first support plate (301), a first clamping screw (304) is fitted in the first screw hole (303), and the first clamping screw (304) is threadedly connected to a first fastening nut (305).

4. The rapid mold change device for machining aircraft structural parts according to claim 1, characterized in that: The second clamping assembly (5) comprises a second support plate (501), one end of the second support plate (501) is fixedly connected to the upper surface of the locking plate (4), the other end of the second support plate (501) is fixedly connected to a second auxiliary support block (502) in a vertical direction, a second screw hole (503) is provided on the upper surface of the second support plate (501), a second clamping screw (504) is fitted in the second screw hole (503), and the second clamping screw (504) is threadedly connected to a second fastening nut (505).

5. The rapid mold change device for machining aircraft structural parts according to claim 2, characterized in that: A first anti-loosening washer (612) is provided between the first fastening bolt (607) and the third supporting block (605), and a second anti-loosening washer (613) is provided between the second fastening bolt (608) and the fourth supporting block (606).

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