CN218694405U

CN218694405U - Aircraft skin guillootine

Info

Publication number: CN218694405U
Application number: CN202222931066.5U
Authority: CN
Inventors: 周松; 沈轶鸥
Original assignee: Shanghai Mopu Technology Co ltd
Current assignee: Shanghai Mopu Technology Co ltd
Priority date: 2022-11-03
Filing date: 2022-11-03
Publication date: 2023-03-24
Anticipated expiration: 2032-11-03

Abstract

The utility model discloses an aircraft skin guillootine, including the mounting bracket, fixedly connected with drive structure on the mounting bracket, the mounting bracket top is fixed with the shearing structure, and the shearing structure is used for cutting the aircraft skin; install the regulation structure in drive structure top, the mounting panel that the removal of catch bar can drive among the drive structure in can adjusting the structure removes. This guillootine passes through electric telescopic handle work, can drive first catch bar and second catch bar and stretch out and draw back, first catch bar and second catch bar stretch out and draw back and can drive first mounting panel and the second mounting panel of its top and stretch out and draw back, make the distance between first mounting panel and the second mounting panel adjustable, adjusted the distance between the clamping structure on first mounting panel and the second mounting panel, both conveniently will be in the covering of lax state and flare-out, also make things convenient for the covering of the different specification and dimension of centre gripping, and the work efficiency is improved.

Description

Aircraft skin guillootine

Technical Field

The utility model relates to an aircraft parts processing technology field especially relates to an aircraft skin guillootine.

Background

With the continuous development of science and technology, the requirements on the aircraft are gradually increased. In order to meet the requirement of lightweight aircrafts, the skins of the aircrafts at the present stage are mostly made of alloy sheets of light alloy, the deadweight of the aircrafts can be effectively reduced by using the alloy sheets, meanwhile, when the sheets are applied to different parts, special-shaped processing is easy to perform, and a cutting device is used for cutting according to the required size in the production process.

At present, the skin in-process is being cut to current guillootine, often directly fixes the skin on the holding frame after directly cutting, but the skin after fixing like this is in the lax state easily and leads to the cutting difficulty, and the rejection rate is high, needs the artificial interference to straighten, and the artificial interference can increase the cost of labor, has influenced work efficiency and productivity.

SUMMERY OF THE UTILITY MODEL

The utility model aims at solving the defects in the prior art, and provides an aircraft skin cutting machine, which comprises a mounting rack, wherein a driving structure is fixedly connected on the mounting rack, and a shearing structure is fixed above the mounting rack and used for cutting the aircraft skin;

the adjusting structure is arranged above the driving structure, and the driving structure drives the mounting plate in the adjusting structure to move by the movement of the pushing plate;

and the clamping structure is fixed on the adjusting structure, and the adjusting structure is used for clamping the aircraft skin.

Preferably, the driving structure comprises an installation box, electric telescopic rods are fixed inside the installation box, one ends of the electric telescopic rods are detachably connected with the first pushing plate and the second pushing plate through screws respectively, and the lower side of the installation box is fixedly connected with the installation frame through screws.

Preferably, the regulation structure includes the regulating plate, two spouts have been seted up to the regulating plate inside, the inside slide that is provided with the looks adaptation of spout, two slide one end is connected through screw and first mounting panel and second mounting panel can be dismantled respectively, screw and install bin fixed connection are passed through to the regulating plate below.

Preferably, the lower parts of the first mounting plate and the second mounting plate are detachably connected with the first pushing plate and the second pushing plate through screws respectively.

Preferably, the clamping structure comprises a connecting block, an upper clamping plate and a lower clamping plate are fixed on one side of the connecting block, and a fixing threaded rod is connected to the upper clamping plate in a threaded manner.

Preferably, a threaded hole is formed in the upper clamping plate, and the fixed threaded rod is matched with the threaded hole.

Preferably, the shearing mechanism comprises a cutting knife, the upper portion of the cutting knife is fixedly connected with a driving box, a lifting mechanism and a rotating mechanism are arranged in the driving box, the driving box is used for driving the cutting knife to cut the skin of the airplane, a sliding rail is arranged between the driving box and the mounting rack, and the sliding rail facilitates the position moving of the cutting knife.

Preferably, a control panel is fixedly connected to the outer side of the driving structure.

Preferably, the support legs are fixed below the mounting rack.

Preferably, the clamping structure is provided with four.

The technical scheme has the following advantages or beneficial effects:

the utility model discloses an electric telescopic handle work can drive first catch bar and second catch bar and stretch out and draw back, first catch bar and second catch bar stretch out and draw back first mounting panel and the second mounting panel that can drive its top and stretch out and draw back, make the distance between first mounting panel and the second mounting panel adjustable, adjusted the distance between the clamping structure on first mounting panel and the second mounting panel, both made things convenient for the covering that is in lax state to flare-out, also made things convenient for the covering of the different specification and size of centre gripping, and the work efficiency is improved.

Drawings

Fig. 1 is a schematic structural view of a cutting machine according to an embodiment of the present invention;

fig. 2 is a front view of a cutting machine according to an embodiment of the present invention;

fig. 3 is a schematic structural view of an adjustment structure in the clipper of fig. 1;

fig. 4 is a schematic structural view of a clamping structure of the cutting machine of fig. 1.

Illustration of the drawings:

1. a mounting frame; 2. a drive structure; 3. an adjustment structure; 4. a clamping structure; 5. shearing the structure; 6. a control panel; 7. a support leg; 201. installing a box; 202. an electric telescopic rod; 203. a first push plate; 204. a second pusher plate; 31. an adjusting plate; 32. a chute; 33. a slide plate; 34. a first mounting plate; 35. a second mounting plate; 41. connecting blocks; 42. an upper splint; 43. a lower splint; 44. fixing a threaded rod; 45. a threaded hole; 51. a cutting knife; 52. a drive box; 53. a slide rail.

Detailed Description

The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative work belong to the protection scope of the present invention.

The first embodiment is as follows:

as shown in fig. 1-4, the cutting machine for aircraft skin of the present invention comprises a mounting frame 1, a driving structure 2 is fixedly connected to the mounting frame 1, a shearing structure 5 is fixed above the mounting frame 1, and the shearing structure 5 is used for cutting the aircraft skin; the adjusting structure 3 is arranged above the driving structure 2, and the pushing plate in the driving structure 2 moves to drive the mounting plate in the adjusting structure 3 to move; the clamping structure 4 is fixed on the adjusting structure 3, and the adjusting structure 3 is used for clamping the aircraft skin; the aircraft skin to be cut is fixed on the clamping structure 4, then the mounting plate in the adjusting structure 3 is driven to move outwards through the work of the driving structure 2, the aircraft skin clamped on the adjusting structure 3 is straightened, and then the aircraft skin clamped below is cut through the work of the control shearing structure 5.

As shown in fig. 1 and fig. 2, further, the shearing structure 5 includes a cutting knife 51, the upper side of the cutting knife 51 is fixedly connected with a driving box 52, a lifting and rotating mechanism is arranged in the driving box 52, the driving box 52 is used for driving the cutting knife 51 to cut the skin of the airplane, a sliding rail 53 is arranged between the driving box 52 and the mounting frame 1, the sliding rail 53 facilitates the position movement of the cutting knife 51, and the lower sides of the first mounting plate 34 and the second mounting plate 35 are detachably connected with a first pushing plate 203 and a second pushing plate 204 through screws respectively; control drive box 52 work through control panel 6, drive cutting knife 51 through the inside elevating system of drive box 52 and go up and down, drive cutting knife 51 rotatory cutting aircraft skin through the inside rotary mechanism of drive box 52, be provided with the slide with slide rail 53 looks adaptation through drive box 52 top for the convenience removes drive box 52, conveniently adjusts the position of cutting knife 51.

As shown in fig. 3, the driving structure 2 includes an installation box 201, electric telescopic rods 202 are fixed inside the installation box 201, one ends of the two electric telescopic rods 202 are detachably connected with a first pushing plate 203 and a second pushing plate 204 through screws, one end of the two electric telescopic rods 202 are fixedly connected with the installation frame 1 through screws, the adjusting structure 3 includes an adjusting plate 31, two sliding grooves 32 are formed inside the adjusting plate 31, adaptive sliding plates 33 are arranged inside the sliding grooves 32, one ends of the two sliding plates 33 are detachably connected with a first installation plate 34 and a second installation plate 35 through screws, and one end of the adjusting plate 31 is fixedly connected with the installation box 201 through screws; work through electric telescopic handle 202, can drive first catch plate 203 and second catch plate 204 and stretch out and draw back, first catch plate 203 and second catch plate 204 stretch out and draw back and can drive first mounting panel 34 and the second mounting panel 35 of its top and stretch out and draw back, make the distance between first mounting panel 34 and the second mounting panel 35 adjustable, adjusted first mounting panel 34 and second mounting panel 35 on the distance between the clamping structure 4, both conveniently will be in the covering of lax state and flare-out, also make things convenient for the covering of the different specification and size of centre gripping, and the work efficiency is improved.

Example two:

as shown in fig. 4, on the basis of the first embodiment, the utility model provides a technical solution: the clamping structure 4 comprises a connecting block 41, an upper clamping plate 42 and a lower clamping plate 43 are fixed on one side of the connecting block 41, a fixed threaded rod 44 is connected to the upper clamping plate 42 in a threaded manner, a threaded hole 45 is formed in the upper clamping plate 42, and the fixed threaded rod 44 is matched with the threaded hole 45; by placing the aircraft skin between the upper clamping plate 42 and the lower clamping plate 43 and then rotating the fixed threaded rod 44, the aircraft skin can be extruded between the fixed threaded rod 44 and the lower clamping plate 43, the aircraft skin is conveniently fixed, and the distance between the bottom of the fixed threaded rod 44 and the lower clamping plate 43 is adjustable, so that the aircraft skin with different thicknesses can be conveniently clamped.

As shown in fig. 2, a control panel 6 is fixedly connected to the outer side of the driving structure 2, supporting legs 7 are fixed below the mounting frame 1, and four clamping structures 4 are arranged; the control device is convenient to work through the control panel 6.

The working principle is as follows: the method comprises the following steps that a worker fixes an aircraft skin to be cut on a clamping structure 4, then drives a mounting plate in an adjusting structure 3 to move outwards through a driving structure 2 to work, straightens the aircraft skin clamped on the adjusting structure 3, and cuts the aircraft skin clamped below through controlling a cutting structure 5 to work; work through electric telescopic handle 202, can drive first catch plate 203 and second catch plate 204 and stretch out and draw back, first catch plate 203 and second catch plate 204 stretch out and draw back and can drive first mounting panel 34 and the second mounting panel 35 of its top and stretch out and draw back, make the distance between first mounting panel 34 and the second mounting panel 35 adjustable, the distance between the centre gripping structure 4 on first mounting panel 34 and the second mounting panel 35 has been adjusted, both make things convenient for the skin that is in the lax state to straighten, also make things convenient for the skin of the different specification and size of centre gripping, the work efficiency is improved, through placing aircraft skin between punch holder 42 and lower plate 43, then rotating fixed threaded rod 44, can extrude aircraft skin between fixed threaded rod 44 and lower plate 43, the convenience is fixed aircraft skin.

Finally, it should be noted that: although the present invention has been described in detail with reference to the foregoing embodiments, it will be apparent to those skilled in the art that modifications and variations can be made in the embodiments or in part of the technical features of the embodiments without departing from the spirit and the scope of the invention.

Claims

1. The aircraft skin cutting machine comprises an installation rack (1), and is characterized in that a driving structure (2) is fixedly connected onto the installation rack (1), a shearing structure (5) is fixed above the installation rack (1), and the shearing structure (5) is used for cutting aircraft skins;

the adjusting structure (3) is arranged above the driving structure (2), and the pushing plate in the driving structure (2) moves to drive the mounting plate in the adjusting structure (3) to move;

the clamping structure (4) is fixed on the adjusting structure (3), and the adjusting structure (3) is used for clamping the aircraft skin.

2. The aircraft skin guillotine according to claim 1, wherein: drive structure (2) are including install bin (201), install bin (201) inside is fixed with electric telescopic handle (202), two electric telescopic handle (202) one end is connected through screw and first slurcam (203) and second slurcam (204) can be dismantled respectively, install bin (201) below is through screw and mounting bracket (1) fixed connection.

3. The aircraft skin guillotine according to claim 1, wherein: adjusting structure (3) includes regulating plate (31), two spout (32) have been seted up to regulating plate (31) inside, inside slide (33) that are provided with the looks adaptation of spout (32), two slide (33) one end is connected through screw and first mounting panel (34) and second mounting panel (35) can be dismantled respectively, regulating plate (31) below is through screw and install bin (201) fixed connection.

4. The aircraft skin guillotine according to claim 3, wherein: the lower parts of the first mounting plate (34) and the second mounting plate (35) are detachably connected with the first pushing plate (203) and the second pushing plate (204) through screws respectively.

5. The aircraft skin guillotine according to claim 1, wherein: clamping structure (4) are including connecting block (41), connecting block (41) one side is fixed with punch holder (42) and lower plate (43), threaded connection has fixed threaded rod (44) on punch holder (42).

6. The aircraft skin guillotine of claim 5, wherein: a threaded hole (45) is formed in the upper clamping plate (42), and the fixed threaded rod (44) is matched with the threaded hole (45).

7. The aircraft skin guillotine according to claim 1, wherein: shear structure (5) include cutting knife (51), cutting knife (51) top and drive box (52) fixed connection, lift and rotary mechanism have in drive box (52), drive box (52) are used for driving cutting knife (51) and cut the aircraft skin, be provided with slide rail (53) between drive box (52) and mounting bracket (1), slide rail (53) make things convenient for cutting knife (51) to carry out position shifting.

8. The aircraft skin guillotine according to claim 1, wherein: the outer side of the driving structure (2) is fixedly connected with a control panel (6).

9. The aircraft skin guillotine according to claim 1, wherein: and supporting legs (7) are fixed below the mounting frame (1).

10. The aircraft skin guillotine according to claim 1, wherein: the number of the clamping structures (4) is four.