Aircraft rotor wing polishing equipment

Abstract

The utility model discloses aircraft rotor wing polishing equipment which comprises a workbench, a box body is arranged on the workbench, and the interior of the box body is divided into a left box chamber and a right box chamber through a longitudinally-arranged partition plate. A first Z-axis translation mechanism arranged in the front-back direction of the workbench is arranged at the bottom in the left box chamber, a first mold is arranged on the first Z-axis translation mechanism, and a first special-shaped groove matched with the outline of the upper surface of the aircraft rotor wing is formed in the upper surface of the first mold; a first polishing mechanism is arranged at the top in the left box chamber; a second Z-axis translation mechanism arranged in the front-back direction of the workbench is arranged at the bottom in the right box chamber, a second mold is arranged on the second Z-axis translation mechanism, and a second special-shaped groove matched with the profile of the lower surface of the aircraft rotor wing is formed in the upper surface of the second mold; a second polishing mechanism is arranged on the top in the right box. The polishing device is high in polishing efficiency, the aircraft rotor wing can be prevented from shaking during polishing, and the polishing effect is guaranteed.

Description

Technical Field

[0001] This utility model relates to the field of polishing equipment technology, specifically to an aircraft rotor polishing device. Background Technology

[0002] The rotor is a crucial component of an aircraft. During flight, the rotor generates both lift and thrust. Furthermore, it functions similarly to ailerons and elevators. Polishing is a necessary step in machining the rotor's surface.

[0003] Polishing the surface of an aircraft rotor requires a polishing machine. The polishing discs on the machine rotate to smooth the rotor surface, making it smooth and glossy. However, aircraft rotors are often irregularly shaped structures with a certain rotation angle, such as... Figure 1 As shown, existing polishing machines often have poor clamping properties, causing shaking during polishing and resulting in poor polishing effects. Utility Model Content

[0004] The technical problem to be solved by this utility model is to provide an aircraft rotor polishing device to solve the problems mentioned in the background art.

[0005] To solve the above-mentioned technical problems, the technical solution adopted by this utility model is as follows.

[0006] A rotor polishing device for aircraft includes a worktable, wherein a housing is mounted on the worktable, and an industrial control board for controlling the device is mounted on the front panel of the housing. The interior of the housing is divided into a left chamber and a right chamber by a longitudinally arranged partition. A first Z-axis translation mechanism is mounted at the bottom of the left chamber, which is arranged along the front-rear direction of the worktable. A first mold is mounted on the first Z-axis translation mechanism. The upper surface of the first mold has a first irregularly shaped groove that is adapted to the contour of the upper surface of the aircraft rotor and is used to fit against the upper surface and sides of the aircraft rotor to support and limit the aircraft rotor. A top part of the left chamber is provided with... A first polishing mechanism is located above the first mold; a second Z-axis translation mechanism is provided at the bottom of the right chamber along the front-back direction of the worktable, and a second mold is provided on the second Z-axis translation mechanism. The upper surface of the second mold has a second irregular groove that is adapted to the contour of the lower surface of the aircraft rotor and is used to fit against the lower surface and side of the aircraft rotor to support and limit the aircraft rotor; a second polishing mechanism is provided at the top of the right chamber above the second mold; the output end of the industrial control board is connected to the controlled ends of the first Z-axis translation mechanism, the first polishing mechanism, the second Z-axis translation mechanism, and the second polishing mechanism, respectively.

[0007] Preferably, the first Z-axis translation mechanism includes a Z-axis lead screw rotatably disposed at the bottom of the left chamber along the front-rear direction of the worktable. A Z-axis slide rail is disposed on each side of the Z-axis lead screw, parallel to the Z-axis lead screw and fixedly connected to the bottom of the left chamber. The bottom of the first mold is threadedly connected to the Z-axis lead screw and slidably fitted to the Z-axis slide rail. A Z-axis translation drive motor, disposed at the bottom of the left chamber and used to drive the Z-axis lead screw to rotate, thereby moving the first mold along the front-rear direction of the worktable, is connected to the rear end of the Z-axis lead screw. The controlled end of the Z-axis translation drive motor is connected to the output end of the industrial control board.

[0008] Preferably, the structure of the second Z-axis translation mechanism is the same as that of the first Z-axis translation mechanism, and the connection method between the second Z-axis translation mechanism and the second mold is the same as that between the first Z-axis translation mechanism and the first mold.

[0009] Preferably, the first polishing mechanism includes an X-axis lead screw rotatably mounted on the top of the left chamber along the left-right direction of the worktable. Above the X-axis lead screw is an X-axis slide rail parallel to the Z-axis lead screw and fixedly connected to the top wall of the left chamber. A mounting seat is threaded onto the X-axis lead screw and slidably assembled with the X-axis slide rail. The left end of the X-axis lead screw extends out of the left chamber and is connected to an X-axis translation drive motor mounted on the housing via a transmission assembly. This motor drives the X-axis lead screw to rotate, thereby moving the mounting seat left and right. An electric cylinder is mounted on the mounting seat. The extension rod of the electric cylinder is downwardly positioned and fixedly connected to a polishing drive motor. The rotation shaft of the polishing drive motor is downwardly positioned and fixedly connected to a polishing disc for polishing the aircraft rotor under the drive of the polishing drive motor. The controlled ends of the polishing drive motor and the electric cylinder are respectively connected to the output ends of the industrial control board.

[0010] Preferably, the structure of the second polishing mechanism is the same as that of the first polishing mechanism.

[0011] Preferably, the bottom of the front panel of the housing is provided with two downward-opening doors for taking out and putting in the aircraft rotor. The lower end of the door is pivotally connected to the housing via a hinge, and the upper end of the door is connected to the housing via a latch.

[0012] The technological advancements achieved by this utility model are as follows, due to the adoption of the above technical solutions.

[0013] This invention, by setting up a first Z-axis translation mechanism, a first mold, and a first polishing mechanism in the left chamber and the left chamber, and a second Z-axis translation mechanism, a second mold, and a second polishing mechanism in the right chamber and the right chamber, not only achieves high polishing efficiency but also avoids shaking during aircraft rotor polishing, ensuring polishing effect. Attached Figure Description

[0014] Figure 1 A schematic diagram of an existing aircraft rotor structure;

[0015] Figure 2 This is a schematic diagram of the structure of this utility model;

[0016] Figure 3 This is a schematic diagram of the front panel of the present invention with the box body removed.

[0017] The components are: 1. Workbench, 2. Housing, 21. Housing door, 3. First Z-axis translation mechanism, 31. Z-axis lead screw, 32. Z-axis slide rail, 33. Z-axis translation drive motor, 4. First mold, 5. First polishing mechanism, 51. X-axis lead screw, 52. X-axis slide rail, 53. Driven gear, 54. Drive gear, 55. X-axis translation drive motor, 56. Mounting base, 57. Electric cylinder, 58. Polishing drive motor, 59. Polishing disc, 6. Second Z-axis translation mechanism, 7. Second mold, 8. Second polishing mechanism, 9. Industrial control board. Detailed Implementation

[0018] The present invention will now be described in further detail with reference to the accompanying drawings and specific embodiments.

[0019] An aircraft rotor polishing device, combined with Figures 2 to 3 As shown, the device includes a workbench 1, a housing 2 on the workbench 1, and an industrial control board 9 on the front panel of the housing 2. The industrial control board 9 is used to control the device.

[0020] The interior of housing 2 is divided into a left chamber and a right chamber by a longitudinally arranged partition. A first Z-axis translation mechanism 3 is located at the bottom of the left chamber, and is positioned along the front-rear direction of the worktable 1. This mechanism includes a Z-axis lead screw 31 rotatably mounted at the bottom of the left chamber along the front-rear direction of the worktable 1. A Z-axis slide rail 32, parallel to the Z-axis lead screw 31, is located on each side of the lead screw 31 and is fixedly connected to the bottom of the left chamber. A Z-axis translation drive motor 33 is connected to the rear end of the Z-axis lead screw 31 and is located at the bottom of the left chamber.

[0021] A first mold 4 is mounted on the first Z-axis translation mechanism 3. Specifically, the bottom of the first mold 4 is threadedly connected to the Z-axis lead screw 31 and slidably fitted onto the Z-axis slide rail 32. By driving the Z-axis lead screw 31 to rotate through the Z-axis translation drive motor 33, the first mold 4 can slide on the Z-axis lead screw 31 and the Z-axis slide rail 32, thereby enabling the first mold 4 to move along the front-back direction of the worktable 1 under the drive of the first Z-axis translation mechanism 3.

[0022] The upper surface of the first mold 4 is provided with a first irregular groove. The first irregular groove is adapted to the upper surface contour of the aircraft rotor. The first irregular groove is used to fit against the upper surface and side of the aircraft rotor, thereby supporting and limiting the aircraft rotor and preventing the aircraft rotor from shaking during polishing.

[0023] A first polishing mechanism 5 is installed at the top of the left chamber, located above the first mold 4. The first polishing mechanism 5 includes an X-axis lead screw 51 rotatably mounted at the top of the left chamber along the left-right direction of the worktable 1. Above the X-axis lead screw 51 is an X-axis slide rail 52 parallel to the Z-axis lead screw 31, which is fixedly connected to the top wall of the left chamber. A mounting base 56 is threaded onto the X-axis lead screw 51, and the mounting base 56 is also slidably assembled with the X-axis slide rail 52. The left end of the X-axis lead screw 51 extends out of the left chamber and is connected to an X-axis translation drive motor 55 via a transmission assembly. Specifically, the transmission assembly includes a driven gear 53 and a driving gear 54. The X-axis translation drive motor 55 is mounted on the housing 2, the driving gear 54 is mounted on the output shaft of the X-axis translation drive motor 55, and the driven gear 53 is located at the left end of the X-axis lead screw 51 and meshes with the driving gear 54. In use, the X-axis translation drive motor 55 drives the drive gear 54 to rotate, the drive gear 54 rotates and drives the driven gear 53 to rotate, the driven gear 53 rotates and drives the X-axis lead screw 51 to rotate, and the X-axis lead screw 51 rotates and drives the mounting base 56 to move left and right.

[0024] An electric cylinder 57 is mounted on the mounting base 56. The telescopic rod of the electric cylinder 57 is positioned downwards and fixedly connected to a polishing drive motor 58. The rotating shaft of the polishing drive motor 58 is positioned downwards and fixedly connected to a polishing disc 59. In use, the telescopic rod of the electric cylinder 57 extends and retracts to raise and lower the polishing disc 59, thereby moving it away from and closer to the aircraft rotor. The mounting base 56 moves left and right, causing the polishing disc 59 to move left and right. The polishing drive motor 58 drives the polishing disc 59 to rotate, thereby enabling the polishing disc 59 to polish the aircraft rotor on the first mold 4.

[0025] The bottom of the right chamber is provided with a second Z-axis translation mechanism 6 arranged along the front and back direction of the worktable 1. The structure of the second Z-axis translation mechanism 6 is the same as that of the first Z-axis translation mechanism 3. A second mold 7 is provided on the second Z-axis translation mechanism 6. The connection method between the second Z-axis translation mechanism 6 and the second mold 7 is the same as the connection method between the first Z-axis translation mechanism 3 and the first mold 4.

[0026] The upper surface of the second mold 7 is provided with a second irregular groove, which is adapted to the contour of the lower surface of the aircraft rotor. The second irregular groove is used to fit against the lower surface and side of the aircraft rotor, thereby supporting and limiting the aircraft rotor and preventing the aircraft rotor from shaking during polishing.

[0027] A second polishing mechanism 8 is provided at the top of the right chamber. The second polishing mechanism 8 is located above the second mold 7. Specifically, the structure of the second polishing mechanism 8 is the same as that of the first polishing mechanism 5.

[0028] The bottom of the front panel of the housing 2 is provided with two doors 21. The lower end of the doors 21 is pivotally connected to the housing 2 via hinges, and the upper end of the doors 21 is connected to the housing 2 via a latch, thereby enabling the doors 21 to be opened downwards for easy access to the aircraft rotor.

[0029] The output terminals of the industrial control board 9 are respectively connected to the controlled terminals of the first Z-axis translation mechanism 3, the first polishing mechanism 5, the second Z-axis translation mechanism 6, and the second polishing mechanism 8, specifically to the controlled terminals of the Z-axis translation drive motor 33, the polishing drive motor 58, and the electric cylinder 57. The industrial control board 9 controls the Z-axis translation drive motor 33, the polishing drive motor 58, and the electric cylinder 57 to realize the movement of the aircraft rotors on the first mold 4 and the second mold 7, as well as the movement and rotation of the polishing disc 59, thereby achieving automatic polishing of the aircraft rotors. The industrial control board 9 is equipped with a display screen and buttons for human-machine interaction.

[0030] In use, this invention involves opening the housing door 21, placing one aircraft rotor on the first mold 4 with its upper surface facing down and in contact with the mold 4; placing the other aircraft rotor on the second mold 7 with its lower surface facing down and in contact with the mold 7; closing the housing door 21, and starting the equipment via the industrial control board 9 to complete the automatic polishing of the aircraft rotors. The support and limiting effect of the first mold 4 and the second mold 7 prevents the aircraft rotors from shaking during polishing, thus ensuring the polishing effect. After one polishing operation, the housing door 21 is opened, and the aircraft rotors on the first mold 4 and the second mold 7 are interchanged for a second polishing, thus completing the polishing of both sides of the two aircraft rotors with high efficiency.

Claims

1. An aircraft rotor polishing device, comprising a worktable (1), characterized in that: The workbench (1) is provided with a box (2), and the front panel of the box (2) is provided with an industrial control board (9) for equipment control. The interior of the box (2) is divided into a left box and a right box by a longitudinally arranged partition. The bottom of the left box is provided with a first Z-axis translation mechanism (3) arranged along the front-back direction of the workbench (1). The first Z-axis translation mechanism (3) is provided with a first mold (4). The upper surface of the first mold (4) is provided with a first irregular groove that is adapted to the upper surface contour of the aircraft rotor and is used to fit against the upper surface and side of the aircraft rotor to support and limit the aircraft rotor. The top of the left box is provided with a first polishing machine located above the first mold (4). Structure (5); The bottom of the right chamber is provided with a second Z-axis translation mechanism (6) arranged along the front and rear direction of the worktable (1). The second Z-axis translation mechanism (6) is provided with a second mold (7). The upper surface of the second mold (7) is provided with a second irregular groove that is adapted to the lower surface profile of the aircraft rotor and is used to fit against the lower surface and side of the aircraft rotor to support and limit the aircraft rotor. The top of the right chamber is provided with a second polishing mechanism (8) located above the second mold (7). The output end of the industrial control board (9) is connected to the controlled ends of the first Z-axis translation mechanism (3), the first polishing mechanism (5), the second Z-axis translation mechanism (6), and the second polishing mechanism (8), respectively.

2. The aircraft rotor polishing equipment according to claim 1, characterized in that: The first Z-axis translation mechanism (3) includes a Z-axis lead screw (31) that is rotatably disposed at the bottom of the left chamber along the front-back direction of the worktable (1). A Z-axis slide rail (32) is disposed on each side of the Z-axis lead screw (31) parallel to the Z-axis lead screw (31) and fixedly connected to the bottom of the left chamber. The bottom of the first mold (4) is threadedly connected to the Z-axis lead screw (31) and slidably connected to the Z-axis slide rail (32). The rear end of the Z-axis lead screw (31) is connected to a Z-axis translation drive motor (33) disposed at the bottom of the left chamber for driving the Z-axis lead screw (31) to rotate so that the first mold (4) moves along the front-back direction of the worktable (1). The controlled end of the Z-axis translation drive motor (33) is connected to the output end of the industrial control board (9).

3. The aircraft rotor polishing equipment according to claim 2, characterized in that: The structure of the second Z-axis translation mechanism (6) is the same as that of the first Z-axis translation mechanism (3), and the connection method between the second Z-axis translation mechanism (6) and the second mold (7) is the same as that between the first Z-axis translation mechanism (3) and the first mold (4).

4. The aircraft rotor polishing equipment according to claim 1, characterized in that: The first polishing mechanism (5) includes an X-axis lead screw (51) that is rotatably mounted on the top of the left chamber along the left-right direction of the worktable (1). Above the X-axis lead screw (51) is an X-axis slide rail (52) that is parallel to the Z-axis lead screw (31) and fixedly connected to the top wall of the left chamber. The X-axis lead screw (51) is threaded with a mounting base (56) that is slidably assembled with the X-axis slide rail (52). The left end of the X-axis lead screw (51) extends out of the left chamber and is connected to a transmission assembly mounted on the housing (2) for driving the X-axis lead screw. (51) An X-axis translation drive motor (55) is rotated to move the mounting base (56) left and right; an electric cylinder (57) is provided on the mounting base (56), the telescopic rod of the electric cylinder (57) is set downward and fixedly connected to a polishing drive motor (58), the rotating shaft of the polishing drive motor (58) is set downward and fixedly connected to a polishing disc (59) for polishing the rotor of the aircraft under the drive of the polishing drive motor (58), and the controlled ends of the polishing drive motor (58) and the electric cylinder (57) are respectively connected to the output end of the industrial control board (9).

5. The aircraft rotor polishing equipment according to claim 4, characterized in that: The structure of the second polishing mechanism (8) is the same as that of the first polishing mechanism (5).

6. The aircraft rotor polishing equipment according to claim 1, characterized in that: The bottom of the front panel of the housing (2) is provided with two downward-opening doors (21) for taking out and putting in the aircraft rotor. The lower end of the door (21) is pivotally connected to the housing (2) by a hinge, and the upper end of the door (21) is connected to the housing (2) by a latch.

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