Aircraft titanium alloy skin cutting tool and method

Abstract

The present invention discloses a tool and method for cutting aircraft titanium alloy skins, belonging to the technical field of aircraft skin processing. The tool comprises a rotating roller frame on which a titanium alloy plate is placed, and further comprises: two symmetrically arranged slide rails, between which a cutting device is slidably mounted, the cutting device comprising a pulley seat rotatably mounted on the slide rails, a vertical frame fixedly mounted on the pulley seat, the vertical frame and the pulley seat being connected by a sprocket unit, and a water jet cutting head mounted on the vertical frame; two symmetrically arranged horizontal shafts fixedly mounted in the rotating roller frame, wherein oppositely arranged clamping members are mounted in the horizontal shafts and the upper slide rails. During cutting, the titanium alloy plate is placed on the rotating roller frame, a second motor is turned on, and the output end of the second motor controls the sprocket unit, causing the sprocket unit to drive the pulley seat to move linearly on the slide rails. During movement, the roller presses the clamping member in the slide rails to clamp the titanium alloy plate at the cutting position, thereby preventing the titanium alloy plate from shaking.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft skin processing, and in particular to a tool and method for cutting aircraft titanium alloy skin. Background Art

[0002] Aircraft skins are the dimensional components that surround the aircraft's frame and are fixed to it with adhesives or rivets, forming the aircraft's aerodynamic shape. The resulting structure, formed by the skin and frame, possesses significant load-bearing capacity and rigidity, yet is lightweight, effectively bearing and transmitting aerodynamic loads. The skin, after receiving aerodynamic forces, transmits these forces to the attached fuselage and wing frames. This complex force distribution, coupled with direct contact with the outside world, requires not only high strength and good plasticity, but also a smooth surface and high corrosion resistance.

[0003] Compared with traditional cutting methods, water jet cutting is faster and more flexible, but during cutting, the skin will be displaced at the moment it is impacted by the water jet. The traditional positioning method uses cylinder fixation, but due to the thin texture of the skin, long-term fixation is prone to indentation, resulting in the surface of the finished product after cutting requiring manual repair, which reduces efficiency. Summary of the Invention

[0004] The purpose of the present invention is to solve the problem that the traditional positioning method in the prior art uses cylinder fixation, but due to the thin texture of the skin, indentations are easily generated during long-term fixation, resulting in the need for manual repair of the surface of the finished product after cutting, which reduces efficiency. A tool and method for cutting aircraft titanium alloy skins are proposed.

[0005] In order to achieve the above object, the present invention adopts the following technical solutions:

[0006] A tool for cutting aircraft titanium alloy skins comprises a rotating roller frame on which a titanium alloy plate is placed, and further comprises: two symmetrically arranged slide rails fixedly mounted on the rotating roller frame, a cutting device slidably mounted between the two slide rails, the cutting device being used for reciprocatingly cutting the titanium alloy plate, the cutting device comprising a pulley seat rotatably mounted on the slide rails, a vertical frame fixedly mounted on the pulley seat, the vertical frame and the pulley seat being connected by a sprocket unit, a water jet cutting head being mounted on the vertical frame; two symmetrically arranged horizontal shafts fixedly mounted in the rotating roller frame, and oppositely arranged clamping members being mounted in the horizontal shafts and the slide rails above.

[0007] Preferably, the clamping member includes: a first metal rod slidably installed in the slide rail, and a first limit block is fixedly installed at both ends of the first metal rod; a coil fixedly installed on the side of the slide rail close to the titanium alloy plate, and the first metal rod is installed in the coil; a second metal rod slidably installed in the horizontal axis, and a first spring is fixedly connected between the second metal rod and the horizontal axis.

[0008] In order to blow off the residue at the cutting site, it further includes: an air box fixedly mounted on the slide rail, a piston plate is slidably mounted in the air box, a pull rod is fixedly connected between the piston plate and the first limit block at the lower end; an air nozzle is fixedly mounted on the air box, and the working surface of the air nozzle faces the titanium alloy plate.

[0009] In order to effectively prevent the cutting device from derailing, further, a metal block is fixedly mounted on the pulley seat, and the metal block and the first metal rod that is energized attract each other.

[0010] In order to recycle water resources, preferably, it also includes: a sliding rod slidably installed in the roller frame, the lower end of the sliding rod passes through the roller frame and is fixedly installed with a water trough, the upper end of the sliding rod passes through the roller frame and is fixedly installed with a second limit block, and a second spring is fixedly connected between the second limit block and the roller frame; a metal filter is slidably installed in the water trough; and a return pipe is fixedly connected between the water trough and the water jet cutting head.

[0011] In order to make the residues produced by cutting fall to a lower place for centralized collection, the metal filter is further in the shape of a mountain with a high middle and low sides, so that the debris produced by cutting falls to a lower place along the shape of the metal filter.

[0012] In order to separate the solid and liquid in the water tank, a slide groove is further opened on the inner wall of the water tank, a sliding pin is fixedly installed on the metal filter, and a third spring is fixedly connected between the sliding pin and the bottom surface of the slide groove; a slag outlet is opened on the inner wall of the water tank.

[0013] In order to effectively prevent the metal filter from being blocked by residue, the system further includes: a bottom plate fixedly mounted on the roller frame, a pry bar rotatably mounted on the bottom plate, and the pry bar is rotatably connected to the water tank; a first motor fixedly mounted on the bottom plate, an output end of the first motor is connected to a first connecting shaft, a cam fixedly mounted on the first connecting shaft, and the cam is against the pry bar.

[0014] In order to push the water in the water tank upward to form a water column and flush the cutting area, it further includes: a second connecting shaft rotatably installed in the water tank, the second connecting shaft is connected to the first connecting shaft through a belt drive, two eccentric blocks are fixedly installed on the second connecting shaft, a push rod is rotatably connected between the two eccentric blocks, and a piston block is rotatably installed on the push rod; a sleeve is fixedly installed in the water tank, and the piston block is slidably installed in the sleeve.

[0015] A method for cutting aircraft titanium alloy skins, the operating steps are as follows:

[0016] Step 1: Place the titanium alloy plate where it will be cut;

[0017] Step 2: Use a water jet to cut the titanium alloy plate and fix it on both sides of the cut to avoid cracks caused by tension;

[0018] Step 3: Recycle water during water jet cutting to avoid waste;

[0019] Step 4: Rinse the cut area with wastewater generated during cutting to effectively reduce the amount of residue.

[0020] Compared with the prior art, the present invention provides a tool and method for cutting aircraft titanium alloy skins, which have the following beneficial effects:

[0021] 1. The aircraft titanium alloy skin cutting tool places the titanium alloy plate on the rotating roller frame, turns on the second motor, and the output end of the second motor controls the sprocket unit, so that the sprocket unit drives the pulley seat to move linearly on the slide rail. During movement, the roller presses down the first metal rod, so that the first metal rod is separated from the center position of the coil and attracts the second metal rod in the horizontal axis, so that the second metal rod moves up, thereby fixing it on both sides of the titanium alloy plate to prevent shaking. As the roller continues to move, the pressure of the roller is lost, and the first metal rod will be re-absorbed to the center position of the coil. The second metal rod is pulled back to its original position by the first spring to reduce the generation of indentations. During the process of the first metal rod being re-absorbed, the first limit block under the first metal rod pushes the pull rod, so that the pull rod pushes the piston plate, and the air in the air box is quickly ejected from the air nozzle, so as to clean up the residue generated by cutting, effectively reducing manual labor.

[0022] 2. This aircraft titanium alloy skin cutting tool uses a first motor that rotates a cam at its output, intermittently lifting a pry bar. This causes the water trough to slide up and down beneath the roller frame. The resulting vibration effectively prevents debris from clogging the metal filter and causes the debris to quickly slide downward. When the second metal rod rises under the influence of the magnetic force, the metal filter also rises, pushing the collected debris into the slag outlet.

[0023] 3. In this aircraft titanium alloy skin cutting tool, during the rotation of the first connecting shaft, the second connecting shaft is driven to rotate by a belt. The rotating second connecting shaft drives the two eccentric blocks to rotate, so that the two eccentric blocks convert the rotational motion into linear motion of the piston block in the sleeve through the push rod. Under the impact of the piston block, the water in the sleeve will be agitated upward to form a water column, which will flush the cutting area and reduce manual labor. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] Figure 1 This is a schematic structural diagram of an aircraft titanium alloy skin cutting tool proposed by the present invention;

[0025] Figure 2 This is a schematic diagram of the structure of a clamping part of an aircraft titanium alloy skin cutting tool proposed by the present invention;

[0026] Figure 3 This is a schematic structural diagram of a cutting device of an aircraft titanium alloy skin cutting tool proposed by the present invention;

[0027] Figure 4 The invention proposes an aircraft titanium alloy skin cutting tool Figure 1 Schematic diagram of the structure of part A;

[0028] Figure 5 This is a schematic diagram of the air box structure of an aircraft titanium alloy skin cutting tool proposed by the present invention;

[0029] Figure 6 This is a schematic diagram of the water tank structure of an aircraft titanium alloy skin cutting tool proposed by the present invention;

[0030] Figure 7 This is a schematic diagram of the piston block structure of an aircraft titanium alloy skin cutting tool proposed by the present invention.

[0031] Figure: 1, roller frame; 101, side plate; 102, support leg; 2, titanium alloy plate; 3, slide rail; 4, pulley seat; 401, roller; 402, rectangular frame; 5, stand; 501, panel; 502, second motor; 6, sprocket unit; 7, water jet cutting head; 701, fourth spring; 8, horizontal axis; 9, first metal rod; 10, first limit block; 11, coil; 12, second metal rod; 13, first spring; 14, air box; 1401, air nozzle; 15, movable Plug plate; 16. Pull rod; 17. Metal block; 18. Slide rod; 19. Water trough; 1901. Chute; 1902. Slag outlet; 1903. Sleeve; 20. Second limit block; 21. Second spring; 22. Metal filter; 2201. Slide pin; 2202. Third spring; 23. Return pipe; 24. Bottom plate; 25. Pry bar; 26. First connecting shaft; 27. Cam; 28. Second connecting shaft; 29. ​​Eccentric block; 30. Push rod; 31. Piston block; 32. First motor. DETAILED DESCRIPTION

[0032] The technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, rather than all the embodiments.

[0033] In the description of the present invention, it should be understood that the terms "upper", "lower", "front", "back", "left", "right", "top", "bottom", "inside", "outside", etc., indicating directions or positional relationships, are based on the directions or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific direction, be constructed and operated in a specific direction, and therefore should not be understood as limiting the present invention.

[0034] Example 1:

[0035] Reference Figure 1-Figure 7 A tool for cutting titanium alloy skins of aircraft comprises a rotating roller frame 1, a titanium alloy plate 2 is placed on the rotating roller frame 1, and further comprises: two symmetrically arranged slide rails 3, fixedly mounted on the rotating roller frame 1, and at a certain distance from the rotating roller frame 1, for the convenience of cutting the titanium alloy plate 2, a cutting device is slidably mounted between the two slide rails 3, the cutting device is used for reciprocatingly cutting the titanium alloy plate 2, the cutting device comprises a pulley seat 4 rotatably mounted on the slide rail 3, a vertical frame 5 is fixedly mounted on the pulley seat 4, the vertical frame 5 and the pulley seat 4 are connected by a sprocket unit 6, and a water jet cutting head 7 is mounted on the vertical frame 5; two symmetrically arranged horizontal shafts 8 are fixedly mounted in the rotating roller frame 1, and relatively arranged clamps are mounted in the horizontal shaft 8 and the slide rail 3 above.

[0036] The roller frame 1 includes two oppositely arranged side panels 101, which can also play a protective role during cutting, effectively preventing residue and water splashing from accidentally injuring workers. Linearly arranged rollers are rotatably installed between the two opposite side panels 101 to support the titanium alloy plate 2. Support legs 102 are also fixedly installed on the lower surface of the side panels 101 to play a supporting role.

[0037] See Figure 1 and Figure 3 and Figure 4 The pulley seat 4 includes two parts, one is a rectangular frame 402, and the other is a roller 401 rotatably mounted on the four corners of the rectangular frame 402 and slidably mounted. The stand 5 is installed on the rectangular frame 402, and a panel 501 is provided in the stand 5. A second motor 502 is fixedly mounted on the panel 501. The output end of the second motor 502 is connected to a sprocket in the sprocket unit 6. The remaining two sprockets in the sprocket unit 6 are respectively mounted on the rectangular frame 402. The three sprockets are tensioned by a chain so that the pulley seat 4 can move on the slide rail 3.

[0038] In addition, a fourth spring 701 is fixedly connected between the mounting position of the water jet cutting head 7 and the stand 5 and the stand 5, which effectively buffers the impact force generated by the water jet cutting head during operation.

[0039] During cutting, the titanium alloy plate 2 is placed on the rotating roller frame 1, and the second motor 502 is turned on. The output end of the second motor 502 controls the sprocket unit 6, so that the sprocket unit 6 drives the pulley seat 4 to move linearly on the slide rail 3. During movement, the roller 401 presses the clamping part in the slide rail 3 to clamp the titanium alloy plate 2 at the cutting position to prevent the titanium alloy plate 2 from shaking.

[0040] See Figure 2 and Figure 5 , the clamping parts in this scheme are further optimized.

[0041] The clamping part includes: a first metal rod 9 slidably installed in the slide rail 3, and a first limit block 10 is fixedly installed at both ends of the first metal rod 9; a coil 11 fixedly installed on the side of the slide rail 3 close to the titanium alloy plate 2, and the first metal rod 9 is installed in the coil 11; a second metal rod 12 slidably installed in the horizontal axis 8, and a first spring 13 is fixedly connected between the second metal rod 12 and the horizontal axis 8.

[0042] The coil 11 is energized. Since the magnetic field density is the largest at the center of the coil 11, the first metal rod 9 will be attracted to the center of the coil 11, and the first metal rod 9 will also be affected by the magnetic force and become a magnet. During the movement of the roller 401, the first metal rod 9 is pressed down, so that the first metal rod 9 is separated from the center of the coil 11 and attracts the second metal rod 12 in the horizontal axis 8, so that the second metal rod 12 moves upward, thereby fixing it on both sides of the titanium alloy plate 2 to prevent shaking. The first limit block 10 increases the contact area with the titanium alloy plate 2 and reduces the generation of indentations.

[0043] The clamping parts are arranged in a mirror image on both sides with the cutting seam of the titanium alloy plate 2 as the axis, which effectively avoids the crack problem caused by cutting tension.

[0044] See Figure 5 The aircraft titanium alloy skin cutting tool in this embodiment also includes: an air box 14 fixedly mounted on the slide rail 3, a piston plate 15 is slidably mounted in the air box 14, and a pull rod 16 is fixedly connected between the piston plate 15 and the first limit block 10 at the lower end; an air nozzle 1401 is fixedly mounted on the air box 14, and the working surface of the air nozzle 1401 faces the titanium alloy plate 2.

[0045] Without the pressure of the roller 401, the first metal rod 9 will be sucked back into the center of the coil 11, and the second metal rod 12 will be pulled back to its original position by the first spring 13. During the process of the first metal rod 9 being sucked back into the center, the first limit block 10 under the first metal rod 9 pushes the pull rod 16, causing the pull rod 16 to push the piston plate 15, and the air in the air box 14 will be quickly ejected from the air nozzle 1401 to clean up the residue produced by cutting.

[0046] It should be noted that an air pipe for air inlet and outlet is fixedly installed on the air box 14, and a one-way valve is fixedly installed in both air pipes. The one-way valve in the outlet air pipe allows the air in the air box 14 to be ejected only from the air nozzle 1401, while the one-way valve in the inlet pipe allows the air to enter the air box 14 only from the outside.

[0047] See Figure 2 and Figure 5 Furthermore, a metal block 17 is fixedly mounted on the pulley seat 4, and the metal block 17 and the first metal rod 9 that is energized attract each other.

[0048] The energized first metal rod 9 generates magnetic attraction on the metal block 17 , causing the metal block 17 to deviate toward the first metal rod 9 , effectively preventing the pulley seat 4 from separating from the slide rail 3 .

[0049] In general, when cutting the titanium alloy skin of an aircraft, the titanium alloy plate 2 is placed on the rotating roller frame 1, and the second motor 502 is turned on. The output end of the second motor 502 controls the sprocket unit 6, so that the sprocket unit 6 drives the pulley seat 4 to move linearly on the slide rail 3. During movement, the roller 401 presses down the first metal rod 9, so that the first metal rod 9 is separated from the center position of the coil 11 and attracts the second metal rod 12 in the horizontal axis 8, so that the second metal rod 12 moves up, thereby fixing it on both sides of the titanium alloy plate 2 to prevent shaking. As the roller 401 continues to move, the pressure of the roller 401 is lost, and the first metal rod 9 will be re-absorbed in the center position of the coil 11, and the second metal rod 12 is pulled back to its original position by the first spring 13. In the process of the first metal rod 9 being re-absorbed, the first limit block 10 under the first metal rod 9 pushes the pull rod 16, so that the pull rod 16 pushes the piston plate 15, and the air in the air box 14 is quickly ejected from the air nozzle 1401, cleaning the residue produced by cutting, and effectively reducing manual labor.

[0050] Example 2:

[0051] See Figure 1-Figure 7 , which is basically the same as Example 1. On the basis of Example 1, the entire technical solution is further optimized.

[0052] See Figure 1 and Figure 6In order to conserve and recycle water resources, the aircraft titanium alloy skin cutting tool in this embodiment further includes: a slide bar 18 slidably mounted within the roller frame 1; the lower end of the slide bar 18 passes through the roller frame 1 and is fixedly mounted with a water trough 19; the upper end of the slide bar 18 passes through the roller frame 1 and is fixedly mounted with a second limit block 20; a second spring 21 is fixedly connected between the second limit block 20 and the roller frame 1; a metal filter 22 is slidably mounted within the water trough 19; the metal filter 22 is in a mountainous shape with a high center and low sides; the debris produced by cutting falls to the lower part along the shape of the metal filter 22; and a return pipe 23 is fixedly connected between the water trough 19 and the water jet cutting head 7.

[0053] It should be noted that a pump body is installed on the return pipe 23 to play a pressure-boosting role, so that the water in the water tank 19 can be pumped into the water jet cutting head 7 again.

[0054] The water sprayed by the water jet cutting head 7 falls into the water tank 19 , is filtered by the metal filter 22 for residue, and then returns to the water jet cutting head 7 through the reflux pipe 23 .

[0055] See Figure 6 Furthermore, a chute 1901 is provided on the inner wall of the water trough 19, a sliding pin 2201 is fixedly installed on the metal filter 22, and a third spring 2202 is fixedly connected between the sliding pin 2201 and the bottom surface of the chute 1901; a slag outlet 1902 is provided on the inner wall of the water trough 19.

[0056] Since the debris generated by cutting falls to the lower part and is concentrated according to the shape of the metal filter 22, when the second metal rod 12 rises under the influence of the magnetic force, the metal filter 22 also rises following the attraction of the second metal rod 12, pushing the collected residue into the slag outlet 1902.

[0057] See Figure 1 In order to effectively prevent the metal filter 22 from being blocked by debris, the aircraft titanium alloy skin cutting tool in this embodiment further includes: a base plate 24 fixedly mounted on the roller frame 1, a pry bar 25 rotatably mounted on the base plate 24, and the pry bar 25 is rotatably connected to the water tank 19; a first motor 32 fixedly mounted on the base plate 24, the output end of the first motor 32 is connected to a first connecting shaft 26, a cam 27 fixedly mounted on the first connecting shaft 26, and the cam 27 abuts against the pry bar 25.

[0058] During the operation of the first motor 32, the output end of the first motor 32 drives the cam 27 to rotate, causing the cam 27 to intermittently lift the pry bar 25, causing the water tank 19 to slide up and down under the roller frame 1. The generated vibration effectively prevents the residue from clogging the metal filter 22 and causes the residue to slide quickly to a lower position.

[0059] See Figure 1 and Figure 7The aircraft titanium alloy skin cutting tool in this embodiment also includes: a second connecting shaft 28 rotatably installed in the water tank 19, the second connecting shaft 28 is connected to the first connecting shaft 26 via a belt drive, two eccentric blocks 29 are fixedly installed on the second connecting shaft 28, a push rod 30 is rotatably connected between the two eccentric blocks 29, and a piston block 31 is rotatably installed on the push rod 30; a sleeve 1903 is fixedly installed in the water tank 19, and the piston block 31 is slidably installed in the sleeve 1903.

[0060] During the rotation of the first connecting shaft 26, the second connecting shaft 28 is driven to rotate by the belt. The rotating second connecting shaft 28 drives the two eccentric blocks 29 to rotate so that the two eccentric blocks 29 convert the rotational motion into the linear motion of the piston block 31 in the sleeve 1903 through the push rod 30. Under the impact of the piston block 31, the water in the sleeve 1903 will be agitated upward to form a water column, which will flush the cutting area and reduce manual labor.

[0061] A method for cutting aircraft titanium alloy skins, the operating steps are as follows:

[0062] Step 1: Place the titanium alloy plate 2 on the roller frame 1;

[0063] Step 2: Turn on the second motor 502. The output end of the second motor 502 controls the sprocket unit 6, so that the sprocket unit 6 drives the pulley seat 4 to move linearly on the slide rail 3 to cut the titanium alloy plate 2.

[0064] Step 3: During movement, the roller 401 presses down the first metal rod 9, causing the first metal rod 9 to separate from the center position of the coil 11 and attract the second metal rod 12 in the horizontal axis 8, causing the second metal rod 12 to move upward, thereby fixing the titanium alloy plate 2 on both sides to prevent shaking;

[0065] Step 4: As the roller 401 continues to move, the pressure of the roller 401 is lost, and the first metal rod 9 is re-absorbed to the center position of the coil 11. The second metal rod 12 is pulled back by the first spring 13. During the process of the first metal rod 9 being re-absorbed, the first limit block 10 below the first metal rod 9 pushes the pull rod 16, so that the pull rod 16 pushes the piston plate 15, and the air in the air box 14 is quickly ejected from the air nozzle 1401, thereby cleaning the residue generated by cutting and effectively reducing manual labor.

[0066] Step 5: The water sprayed by the water jet cutting head 7 falls into the water tank 19, is filtered by the metal filter 22, and then returns to the water jet cutting head 7 through the return pipe 23;

[0067] Step 6: As the debris generated by cutting falls to the lower part of the metal filter 22 and is concentrated, when the second metal rod 12 is lifted up by the magnetic force, the metal filter 22 also rises up with the attraction of the second metal rod 12, pushing the collected debris into the slag outlet 1902;

[0068] Step 7: The output end of the first motor 32 drives the cam 27 to rotate, causing the cam 27 to intermittently lift the pry bar 25, causing the water tank 19 to slide up and down below the roller frame 1. The generated vibration effectively prevents the residue from clogging the metal filter 22 and causes the residue to slide quickly to the bottom.

[0069] Step 8: The rotating second connecting shaft 28 drives the two eccentric blocks 29 to rotate so that the two eccentric blocks 29 convert the rotational motion into linear motion of the piston block 31 in the sleeve 1903 through the push rod 30. Under the impact of the piston block 31, the water in the sleeve 1903 will surge upward to form a water column, flushing the cutting area and reducing manual labor.

[0070] The above description is only a preferred specific embodiment of the present invention, but the scope of protection of the present invention is not limited thereto. Any technician familiar with the technical field, within the technical scope disclosed by the present invention, who makes equivalent replacements or changes based on the technical solution and inventive concept of the present invention, should be covered by the scope of protection of the present invention.

Claims

1. A tool for cutting aircraft titanium alloy skins, comprising a roller frame (1), a titanium alloy plate (2) being placed on the roller frame (1), and characterized in that: Also includes: Two symmetrically arranged slide rails (3) are fixedly mounted on a rotating roller frame (1); a cutting device is slidably mounted between the two slide rails (3); the cutting device is used for reciprocatingly cutting the titanium alloy plate (2); the cutting device comprises a pulley seat (4) rotatably mounted on the slide rails (3); a stand (5) is fixedly mounted on the pulley seat (4); the stand (5) and the pulley seat (4) are connected to each other by a sprocket unit (6); a water jet cutting head (7) is mounted on the stand (5); Two symmetrically arranged transverse shafts (8) are fixedly installed in the roller frame (1), and the transverse shafts (8) and the upper slide rails (3) are both provided with clamping members arranged opposite to each other; The pulley seat (4) comprises two parts, one is a rectangular frame (402), and the other is rollers (401) rotatably mounted at the four corners of the rectangular frame (402); The roller (401) presses the clamping piece in the slide rail (3) to clamp the titanium alloy plate (2) at the cutting position; The clamping member comprises: A first metal rod (9) is slidably mounted in the slide rail (3), with first limit blocks (10) fixedly mounted on both ends of the first metal rod (9); a coil (11) fixedly mounted on a side of the slide rail (3) close to the titanium alloy plate (2), wherein the first metal rod (9) is mounted inside the coil (11); a second metal rod (12) slidably mounted in the transverse shaft (8), wherein a first spring (13) is fixedly connected between the second metal rod (12) and the transverse shaft (8); Also includes: An air box (14) is fixedly mounted on the slide rail (3), a piston plate (15) is slidably mounted in the air box (14), and a pull rod (16) is fixedly connected between the piston plate (15) and the first limit block (10) at the lower end; An air nozzle (1401) is fixedly mounted on the air box (14), and a working surface of the air nozzle (1401) faces the titanium alloy plate (2); Also includes: A slide rod (18) is slidably mounted in the roller frame (1), the lower end of the slide rod (18) passes through the roller frame (1) and is fixedly mounted with a water tank (19), the upper end of the slide rod (18) passes through the roller frame (1) and is fixedly mounted with a second limit block (20), and a second spring (21) is fixedly connected between the second limit block (20) and the roller frame (1); A metal filter (22) is slidably installed in the water tank (19); A return pipe (23) is fixedly connected between the water tank (19) and the water jet cutting head (7).

2. The aircraft titanium alloy skin cutting tool according to claim 1, characterized in that: A metal block (17) is fixedly mounted on the pulley seat (4), and the metal block (17) and the first metal rod (9) that is energized attract each other.

3. The aircraft titanium alloy skin cutting tool according to claim 2, characterized in that: The metal filter (22) is in a mountainous shape with a high center and low sides, and debris generated by cutting falls to a lower position along the shape of the metal filter (22).

4. The aircraft titanium alloy skin cutting tool according to claim 3, characterized in that: The inner wall of the water trough (19) is provided with a slide groove (1901), a slide pin (2201) is fixedly mounted on the metal filter (22), and a third spring (2202) is fixedly connected between the slide pin (2201) and the bottom surface of the slide groove (1901); A slag outlet (1902) is provided on the inner wall of the water tank (19).

5. The aircraft titanium alloy skin cutting tool according to claim 4, characterized in that: Also includes: A bottom plate (24) is fixedly mounted on the roller frame (1), a pry bar (25) is rotatably mounted on the bottom plate (24), and the pry bar (25) is rotatably connected to the water tank (19); A first motor (32) is fixedly mounted on the base plate (24); an output end of the first motor (32) is connected to a first connecting shaft (26); a cam (27) is fixedly mounted on the first connecting shaft (26); and the cam (27) abuts against the pry bar (25).

6. The aircraft titanium alloy skin cutting tool according to claim 5, characterized in that: Also includes: A second connecting shaft (28) is rotatably mounted in the water tank (19), the second connecting shaft (28) is connected to the first connecting shaft (26) via a belt transmission, two eccentric blocks (29) are fixedly mounted on the second connecting shaft (28), a push rod (30) is rotatably connected between the two eccentric blocks (29), and a piston block (31) is rotatably mounted on the push rod (30); A sleeve (1903) is fixedly installed in the water tank (19), and the piston block (31) is slidably installed in the sleeve (1903).

7. A method for cutting aircraft titanium alloy skins, using the aircraft titanium alloy skin cutting tool according to claim 6, characterized in that: The steps are as follows: Step 1: Place the titanium alloy plate (2) at the location to be cut; Step 2: Cut the titanium alloy plate (2) with a water jet and fix it on both sides of the cut to avoid cracks caused by tension; Step 3: Recycle water during water jet cutting to avoid waste; Step 4: Rinse the cut area with wastewater generated during cutting to effectively reduce the amount of residue.

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