Aircraft skin cutting device

Abstract

The present application relates to the field of manufacturing and assembly technology, and in particular to an aircraft skin cutting device, comprising a frame body, the frame body being rotatably connected to two main steering wheels, and the frame body being connected to a cutting line, the cutting line sequentially passing around the two main steering wheels, and the cutting line being connected to a power structure for driving the cutting line to move back and forth, thereby achieving the effect of reducing the noise generated when cutting the aircraft skin.

Description

Technical Field

[0001] The present application relates to the technical field of manufacturing and assembly, and in particular to an aircraft skin cutting device. Background Art

[0002] Aircraft skin refers to a dimensional component that surrounds the aircraft frame structure and is fixed to the frame with adhesives or rivets to form the aircraft's aerodynamic shape. The skin structure composed of the aircraft skin and the frame has a large bearing capacity and rigidity, but is very light in weight, and plays a role in bearing and transmitting aerodynamic loads.

[0003] During the aircraft damage repair process, the aircraft skin is cut using a milling tool. When the aircraft skin is cut using a milling tool, more than 80 decibels of noise will be generated, requiring operators to wear noise-canceling headphones during operation, causing inconvenience to operators when cutting the skin. Summary of the invention

[0004] In order to reduce the noise generated when cutting aircraft skin, the present application provides an aircraft skin cutting device.

[0005] The above technical objectives of this application are achieved through the following technical solutions:

[0006] An aircraft skin cutting device comprises a frame body, which is rotatably connected to two main steering wheels, and is connected to a cutting line, which passes around the two main steering wheels in sequence, and is connected to a power structure for driving the cutting line to move back and forth.

[0007] By adopting the above solution, when it is necessary to cut the aircraft skin, the cutting line between the two main steering wheels can be aligned with the part of the aircraft skin that needs to be cut, and then the power structure drives the cutting line to reciprocate, thereby cutting the aircraft skin. Compared with the milling tool, the cutting line is used to cut the aircraft skin, and the processing force is very small and there is basically no vibration, thereby solving the previous problem of processing noise.

[0008] Optionally, the frame is connected with a flange for connecting to a robotic arm.

[0009] By adopting the above solution, the flange is connected to the mechanical arm, so that the mechanical arm drives the cutting device to move, thereby making the aircraft skin cutting more accurate.

[0010] Optionally, the frame is connected to a visual positioning camera for observing the cutting position.

[0011] By adopting the above solution, the position of the aircraft skin cutting is observed through a visual positioning camera, so that the state of the aircraft skin can be judged more accurately during the cutting process, and the control system of the robotic arm can observe the position of the aircraft skin in real time, thereby planning the aircraft skin cutting position and making the aircraft skin cutting more accurate.

[0012] Optionally, the frame is connected to a coded light source for illuminating the cutting position.

[0013] By adopting the above solution, the visual positioning camera can observe the state of the aircraft skin more clearly, thereby making the cutting of the aircraft skin more accurate.

[0014] Optionally, the power structure includes a driving motor, a frame slidably connected to a rectangular frame, and gear teeth are arranged on opposite sides of the inner side of the rectangular frame, the output shaft of the driving motor is fixedly connected to a toothless gear, the toothless gear is located inside the rectangular frame, and the toothless gear is meshed with the gear teeth inside the rectangular frame, and both ends of the cutting line are connected to the rectangular frame.

[0015] By adopting the above scheme, when the aircraft skin is cut, the driving motor rotates, thereby driving the toothless gear to rotate, and the toothless gear drives the rectangular frame to slide, so that the rectangular frame drives the cutting line to move until the toothless gear reaches one side of the rectangular frame. At this time, the toothless gear is separated from the gear teeth on one side of the rectangular frame, and then the toothless gear is engaged with the gear teeth on the other side of the rectangular frame, thereby driving the rectangular frame to move in the opposite direction, thereby driving the cutting line to move in the opposite direction, and so on and so forth, thereby realizing the back and forth movement of the cutting line, so that the cutting line can cut the aircraft skin.

[0016] Optionally, the frame is connected to a wheel-connecting rod, two wheel-connecting rods are provided, and the two wheel-connecting rods are cross-arranged, and a rotating shaft is provided at the intersection of the two wheel-connecting rods, the two wheel-connecting rods are rotatably connected to the frame body through the rotating shaft, and the two wheel-connecting rods are rotatably connected to the rotating shaft, and the two main steering wheels are respectively rotatably connected to the ends of the two wheel-connecting rods, and the main steering wheel is provided at the end of the wheel-connecting rod away from the frame, and the wheel-connecting rod is connected to a rotating rod structure that drives the wheel-connecting rod to rotate around the rotating shaft.

[0017] By adopting the above scheme, the connecting wheel rod is driven to rotate by the rotating rod structure, so as to adjust the distance between the two main steering wheels. The jitter of the cutting line can be reduced by reducing the distance between the two main steering wheels, so that the aircraft skin can be cut more accurately. The distance between the two main steering wheels can also be increased to cut thicker skin. At the same time, the distance between the two main steering wheels and the frame is also adjusted, so that the cutting line can cut the aircraft skin deeper.

[0018] Optionally, the rotating rod structure includes a threaded rod, which is rotatably connected to the frame, the threaded rod is threadedly connected to a threaded sleeve, the threaded sleeve is connected to a connecting rod, the threaded sleeve is hinged at one end of the connecting rod, the end of the connecting rod facing away from the threaded sleeve is hinged to the wheel connecting rod, and the connecting rod and the wheel connecting rod are hinged at a point close to the end of the wheel connecting rod facing away from the main steering wheel.

[0019] By adopting the above solution, the operator can rotate the threaded rod to drive the threaded sleeve to move along the threaded rod, thereby driving the connecting rod to move, thereby driving the connecting wheel rod to rotate, thereby achieving the purpose of driving the connecting wheel rod to rotate.

[0020] Optionally, the end of the connecting wheel rod facing away from the main steering wheel is connected to a tensioning wheel for tensioning the cutting line, and the cutting line passes around the tensioning wheel.

[0021] By adopting the above scheme, the operator can adjust the position of the tensioning wheel while adjusting the distance between the main steering wheels, so that the cutting line is always in a tensioned state, so that the cutting line can cut the aircraft skin more smoothly, and at the same time reduce the jitter of the cutting line, so that the cutting of the aircraft skin is more accurate.

[0022] Optionally, the connecting wheel rod is rotatably connected to an internal threaded ring at one end away from the main steering wheel, the tensioning wheel is connected to a fine-tuning rod, the fine-tuning rod has an external thread at one end away from the tensioning wheel, and the fine-tuning rod has an external thread at one end threadedly connected to the internal threaded ring.

[0023] By adopting the above technical solution, the operator can rotate the internal thread ring to drive the fine-tuning rod to screw out or in, thereby achieving fine-tuning of the tensioning wheel, so that the operator can adjust the tension of the cutting line individually.

[0024] Optionally, the fine-tuning rod has one end with an external thread fixedly connected to a rectangular rod, and the connecting wheel rod has one end connected to the internal thread ring with a rectangular groove, and the rectangular rod is slidably connected in the rectangular groove.

[0025] By adopting the above technical solution, the rectangular rod is placed in the rectangular groove, which limits the rotation of the fine-tuning rod, thereby preventing the fine-tuning rod from rotating with the internal thread ring.

[0026] In summary, this application has the following technical effects:

[0027] By setting a cutting line and a power structure, the power structure drives the cutting line to move back and forth, thereby driving the cutting line to cut the aircraft skin, so that the cutting noise of the aircraft skin is reduced;

[0028] The aircraft skin cutting is made more accurate by setting up a visual positioning camera;

[0029] The turning rod structure is provided to enable the operator to adjust the distance between the two main steering wheels. BRIEF DESCRIPTION OF THE DRAWINGS

[0030] Figure 1 It is a schematic diagram of the overall structure of this application;

[0031] Figure 2 This is a schematic diagram of a portion of the structure of the camera where the visual positioning is emphasized in this application;

[0032] Figure 3 This is a partial structural diagram of the application intended to emphasize the power structure;

[0033] Figure 4 This is a schematic diagram of a part of the structure of the threaded rod that this application intends to emphasize;

[0034] Figure 5 This application intends to emphasize the partial structural cross-section diagram of the fine-tuning rod.

[0035] In the figure, 1. frame; 2. main steering wheel; 3. cutting line; 4. flange; 5. visual positioning camera; 6. coded light source; 7. power structure; 71. drive motor; 711. toothless gear; 72. rectangular frame; 73. auxiliary steering wheel; 8. connecting wheel rod; 81. internal threaded ring; 82. rectangular groove; 9. threaded rod; 91. threaded sleeve; 92. connecting rod; 10. tensioning wheel; 101. fine-tuning rod; 102. rectangular rod. DETAILED DESCRIPTION

[0036] The present application is further described in detail below with reference to the accompanying drawings.

[0037] Reference Figure 1 , an aircraft skin cutting device, including a frame 1, the frame 1 is rotatably connected to two main steering wheels 2, and the frame 1 is connected to a cutting line 3, the cutting line 3 passes around the two main steering wheels 2 in sequence, and the cutting line 3 is connected to a power structure 7 for driving the cutting line 3 to move back and forth. When it is necessary to cut the aircraft skin, the cutting line 3 between the two main steering wheels 2 can be aligned with the aircraft skin to be cut, and then the power structure 7 drives the cutting line 3 to reciprocate, so as to cut the aircraft skin. Compared with milling tools, the cutting line 3 has a very small processing force and basically no vibration, thereby solving the problem of previous processing noise.

[0038] Reference Figure 1 The cutting wire 3 is a high-strength wear-resistant wire body made of diamond particles and a wire base body. The wire diameter of the cutting wire 3 is usually 0.4-0.8mm, and the contact area with the skin is very small. The contact processing type with the skin is similar to grinding. Therefore, the processing force is very small and there is no vibration, so the sound during the processing is less than 50 decibels.

[0039] Reference Figure 1 and Figure 2The frame 1 is connected to a flange 4 for connecting to a robot arm. The flange 4 is connected to the robot arm so that the robot arm drives the cutting device to move, thereby making the aircraft skin cutting more accurate. The frame 1 is connected to a visual positioning camera 5 for observing the cutting position. The visual positioning camera 5 locates the object through two different viewing directions. The position of the aircraft skin cutting is observed through the visual positioning camera 5, so that the state of the aircraft skin can be judged more accurately during the cutting process, so that the control system of the robot arm can observe the position of the aircraft skin in real time, thereby planning the aircraft skin cutting position, and making the aircraft skin cutting more accurate. The frame 1 is connected to a coded light source 6 for illuminating the cutting position, so that the visual positioning camera 5 can observe the state of the aircraft skin more clearly, thereby making the aircraft skin cutting more accurate.

[0040] Reference Figure 2 and Figure 3 The power structure 7 includes a driving motor 71, a frame 1 is slidably connected to a rectangular frame 72, a slide groove is arranged on the surface of the frame 1, the rectangular frame 72 slides in the slide groove, and gear teeth are arranged on opposite sides of the inner side of the rectangular frame 72, the output shaft of the driving motor 71 is fixedly connected to a toothless gear 711, the toothless gear 711 is located inside the rectangular frame 72, and the toothless gear 711 is meshed with the gear teeth inside the rectangular frame 72, and both ends of the cutting line 3 are connected to the rectangular frame 72, and auxiliary steering wheels 73 are arranged on opposite sides close to the rectangular frame 72, and the cutting line 3 is connected to the rectangular frame 72 after bypassing the auxiliary steering wheel 73. When cutting the aircraft skin, the driving motor 71 rotates, thereby driving the toothless gear 711 to rotate, and the toothless gear 711 drives the rectangular frame 72 to slide, so that the rectangular frame 72 drives the cutting line 3 to move until the toothless gear 711 reaches one side of the rectangular frame 72. At this time, the toothless gear 711 is separated from the gear teeth on one side of the rectangular frame 72, and then the toothless gear 711 is engaged with the gear teeth on the other side of the rectangular frame 72, thereby driving the rectangular frame 72 to move in the opposite direction, thereby driving the cutting line 3 to move in the opposite direction, and so on. The cutting line 3 moves back and forth, so that the cutting line 3 can cut the aircraft skin.

[0041] Reference Figure 4The frame 1 is connected with a wheel link 8, and the wheel link 8 is provided with two wheels, and the two wheel link 8 are cross-arranged, and a rotating shaft is arranged at the intersection of the two wheel link 8, and the two wheel link 8 is rotationally connected to the frame 1 through the rotating shaft, and the two wheel link 8 are rotationally connected to the rotating shaft, and the two main steering wheels 2 are rotationally connected to the ends of the two wheel link 8 respectively, and the two main steering wheels 2 are located in the same plane, and the main steering wheel 2 is arranged at the end of the wheel link 8 away from the frame 1, and the wheel link 8 is connected with a rotating rod structure that drives the wheel link 8 to rotate around the rotating shaft. The rotating rod structure drives the wheel link 8 to rotate, thereby adjusting the distance between the two main steering wheels 2, and the jitter of the cutting line 3 can be reduced by reducing the distance between the two main steering wheels 2, so that the cutting of the aircraft skin is more accurate, and the distance between the two main steering wheels 2 can also be increased to cut the skin with a larger thickness. At the same time, the distance between the two main steering wheels 2 and the frame 1 is also adjusted, so that the cutting line 3 can cut the aircraft skin to a deeper depth.

[0042] Reference Figure 4 The rotating rod structure includes a threaded rod 9, which is rotatably connected to the frame 1. The threaded rod 9 is threadedly connected to a threaded sleeve 91, which is connected to a connecting rod 92. The threaded sleeve 91 is hinged at one end of the connecting rod 92. The end of the connecting rod 92 away from the threaded sleeve 91 is hinged to the connecting wheel rod 8, and the hinged part of the connecting rod 92 and the connecting wheel rod 8 is located near the end of the connecting wheel rod 8 away from the main steering wheel 2. The operator can rotate the threaded rod 9 to drive the threaded sleeve 91 to move along the threaded rod 9, thereby driving the connecting rod 92 to move, thereby driving the connecting wheel rod 8 to rotate, thereby achieving the purpose of driving the connecting wheel rod 8 to rotate.

[0043] Reference Figure 4 and Figure 5 The end of the connecting wheel rod 8 away from the main steering wheel 2 is connected with a tensioning wheel 10 for tensioning the cutting line 3, and the cutting line 3 passes around the tensioning wheel 10. When the operator adjusts the distance between the main steering wheels 2, the position of the tensioning wheel 10 is adjusted at the same time, so that the cutting line 3 is always in a tensioned state, so that the cutting line 3 can cut the aircraft skin more smoothly, and at the same time reduce the shaking of the cutting line 3, so that the aircraft skin is cut more accurately.

[0044] Reference Figure 5The end of the connecting wheel rod 8 away from the main steering wheel 2 is rotatably connected to the internal thread ring 81, and the tension wheel 10 is connected to the fine-tuning rod 101. The end of the fine-tuning rod 101 away from the tension wheel 10 is provided with an external thread, and the end of the fine-tuning rod 101 with an external thread is threadedly connected to the internal thread ring 81. The fine-tuning rod 101 is fixedly connected to a rectangular rod 102 at one end with an external thread, and a rectangular groove 82 is provided at one end of the connecting wheel rod 8 connected to the internal thread ring 81, and the rectangular rod 102 is slidably connected in the rectangular groove 82. The operator can rotate the internal thread ring 81 to drive the fine-tuning rod 101 to rotate out or in, thereby realizing fine-tuning of the tension wheel 10, so that the operator can adjust the tension of the cutting line 3 separately. The rectangular rod 102 is in the rectangular groove 82, limiting the rotation of the fine-tuning rod 101, thereby preventing the fine-tuning rod 101 from rotating with the internal thread ring 81.

[0045] The specific implementation principle of the present application is: when it is necessary to cut the aircraft skin, the drive motor 71 rotates, thereby driving the toothless gear 711 to rotate, and the toothless gear 711 drives the rectangular frame 72 to slide, so that the rectangular frame 72 drives the cutting line 3 to move, until the toothless gear 711 reaches one side of the rectangular frame 72, at this time, the toothless gear 711 is separated from the gear teeth on one side of the rectangular frame 72, and then the toothless gear 711 is engaged with the gear teeth on the other side of the rectangular frame 72, thereby driving the rectangular frame 72 to move in the opposite direction, thereby driving the cutting line 3 to move in the opposite direction, and so on, so as to achieve the back and forth movement of the cutting line 3, so that the cutting line 3 can cut the aircraft skin. In addition, the operator can drive the threaded sleeve 91 to move along the threaded rod 9 by rotating the threaded rod 9, thereby adjusting the distance between the two main steering wheels 2. The present application uses the cutting line 3 to cut the aircraft skin, which generates less noise than the existing aircraft skin cutting.

[0046] This specific embodiment is merely an explanation of the present application and is not a limitation of the present application. After reading this specification, those skilled in the art may make modifications to the present embodiment without any creative contribution as needed, but such modifications are protected by the patent law as long as they are within the scope of the claims of the present application.

Claims

1. An aircraft skin cutting device, characterized in that: The machine comprises a frame (1), the frame (1) is rotatably connected to two main steering wheels (2), the frame (1) is connected to a cutting line (3), the cutting line (3) passes around the two main steering wheels (2) in sequence, and the cutting line (3) is connected to a power structure (7) for driving the cutting line (3) to move back and forth; The frame (1) is connected to a wheel connecting rod (8), two wheel connecting rods (8) are provided, and the two wheel connecting rods (8) are cross-arranged, and a rotating shaft is provided at the intersection of the two wheel connecting rods (8), the two wheel connecting rods (8) are rotationally connected to the frame (1) through the rotating shaft, and the two wheel connecting rods (8) are rotationally connected to the rotating shaft, and the two main steering wheels (2) are rotationally connected to the ends of the two wheel connecting rods (8), respectively, and the main steering wheel (2) is provided at one end of the wheel connecting rod (8) away from the frame (1), and the wheel connecting rod (8) is connected to a rotating rod structure that drives the wheel connecting rod (8) to rotate around the rotating shaft; The rotating rod structure comprises a threaded rod (9), the threaded rod (9) is rotatably connected to the frame (1), the threaded rod (9) is threadedly connected to a threaded sleeve (91), the threaded sleeve (91) is connected to a connecting rod (92), the threaded sleeve (91) is hinged to one end of the connecting rod (92), the end of the connecting rod (92) facing away from the threaded sleeve (91) is hinged to the connecting wheel rod (8), and the hinged portion between the connecting rod (92) and the connecting wheel rod (8) is located near the end of the connecting wheel rod (8) facing away from the main steering wheel (2); The end of the connecting wheel rod (8) facing away from the main steering wheel (2) is connected to a tensioning wheel (10) for tensioning the cutting line (3), and the cutting line (3) passes around the tensioning wheel (10); The end of the connecting wheel rod (8) away from the main steering wheel (2) is rotatably connected to an internal thread ring (81), the tension wheel (10) is connected to a fine-tuning rod (101), the end of the fine-tuning rod (101) away from the tension wheel (10) is provided with an external thread, and the end of the fine-tuning rod (101) provided with an external thread is threadedly connected to the internal thread ring (81).

2. The aircraft skin cutting device according to claim 1, characterized in that: The frame (1) is connected to a flange (4) for connecting to a mechanical arm.

3. The aircraft skin cutting device according to claim 2, characterized in that: The frame (1) is connected to a visual positioning camera (5) for observing the cutting position.

4. The aircraft skin cutting device according to claim 3, characterized in that: The frame (1) is connected to a coded light source (6) for illuminating the cutting position.

5. The aircraft skin cutting device according to claim 1, characterized in that: The power structure (7) comprises a driving motor (71), a frame (1) being slidably connected to a rectangular frame (72), and gear teeth are arranged on two opposite sides of the inner side of the rectangular frame (72), an output shaft of the driving motor (71) being fixedly connected to a toothless gear (711), the toothless gear (711) being located inside the rectangular frame (72), and the toothless gear (711) is meshed with gear teeth inside the rectangular frame (72), and both ends of the cutting line (3) are connected to the rectangular frame (72).

6. The aircraft skin cutting device according to claim 1, characterized in that: The fine-tuning rod (101) has one end with an external thread fixedly connected to a rectangular rod (102), and the connecting wheel rod (8) has one end connected to the internal thread ring (81) with a rectangular groove (82), and the rectangular rod (102) is slidably connected in the rectangular groove (82).

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