Quickly-assembled lathe for machining aeronautical parts

Abstract

The utility model provides a quick-assembly lathe for aviation part processing, which comprises a pedestal, a groove is arranged at the top of the pedestal, guide rails are symmetrically fixed at the top of the pedestal and on two sides of the groove, moving blocks are slidably mounted on the two guide rails along the length direction of the pedestal, and vertical telescopic rods are fixed at the tops of the moving blocks. A moving frame is fixed to the tops of the two telescopic rods, and a first electric cylinder connected with the moving frame is fixedly installed on the moving block. When aviation parts are cut, the two groups of positioning mechanisms are matched with the driving mechanism, so that the mode that the positioning of the positioning mechanisms on the machined aviation parts is canceled firstly, and then the next aviation part to be cut is mounted and positioned is replaced; the time for mounting and dismounting the aviation parts is saved, the effect of quickly mounting the aviation parts to be machined is achieved, and therefore the machining efficiency of the aviation parts is improved.

Description

Technical Field

[0001] This utility model relates to the technical field of aerospace parts processing equipment, specifically to a quick-assembly lathe for aerospace parts processing. Background Technology

[0002] An aircraft is any machine that takes off and flies by aerodynamically through the relative motion of its fuselage and the air; including balloons, airships, airplanes, helicopters, tiltrotor aircraft, etc.; aircraft manufacturing refers to the process of manufacturing aircraft according to the design requirements of different types of aircraft. Aircraft fuselage manufacturing involves processes such as process preparation, manufacturing of process equipment, preparation of blanks, machining of parts, assembly, and inspection; in the process of spacecraft component machining, some aircraft components need to be machined using a lathe.

[0003] Currently, when machining aerospace parts on existing lathes, the positioning mechanism on the lathe is typically used to position the part to be machined. Then, the cutting tool on the lathe is moved to contact the part, causing the positioning mechanism to rotate, which in turn rotates the part, achieving the machining effect. This method is simple to operate. However, in actual use, the following drawbacks still exist:

[0004] During the machining of aerospace parts, after the aerospace parts positioned on the positioning mechanism have been machined, it is necessary to first remove the positioning mechanism from the machined aerospace parts before installing and positioning the next aerospace parts to be machined, so that the machining end of the aerospace parts is facing the cutting tool for subsequent machining. This results in a significant waste of time in installing and removing aerospace parts, thereby reducing the machining efficiency of aerospace parts.

[0005] Therefore, this application proposes a quick-assembly lathe for machining aerospace parts. Utility Model Content

[0006] To address the shortcomings of existing technologies, this utility model provides a quick-assembly lathe for machining aerospace parts, solving the problems mentioned in the background art.

[0007] To achieve the above objectives, this utility model provides the following technical solution:

[0008] A quick-release lathe for machining aerospace parts includes a base with a groove on its top. Guide rails are symmetrically fixed on the top of the base and on both sides of the groove. Moving blocks are slidably mounted on each guide rail along the length of the base. Vertical telescopic rods are fixed to the top of each moving block. A moving frame is fixed to the top of each telescopic rod. An electric cylinder connected to the moving frame is fixedly mounted on each moving block. A driving mechanism acting on the moving block is mounted on one of the guide rails, used to make the moving block slide or stop sliding on the guide rail. A slider is slidably mounted on the top of the moving frame in a horizontal direction. An electric cylinder connected to the slider is fixedly mounted on the moving frame. A mounting seat is fixedly mounted on one side of the slider. A mounting groove is formed on the side of the mounting seat away from the moving frame. A cutting tool is inserted into the mounting seat and engaged with the mounting seat. The bottom end of the cutting tool extends to the bottom of the moving frame. The cutting tool is fixed to the mounting seat by screws.

[0009] A mounting block is fixedly mounted on the platform at the end of the mounting base away from the slider. The top of the mounting block extends above the platform. A horizontal rotating shaft is rotatably mounted on the mounting block. A motor for driving the rotating shaft to rotate is fixedly mounted on the mounting block.

[0010] A vertically oriented rotating shaft is rotatably mounted on the mounting block. A connecting frame is fixed to the top of the rotating shaft. A drive mechanism acting on the rotating shaft is mounted on the mounting block to make the rotating shaft rotate on the mounting block. Horizontally oriented rotating rods are rotatably mounted at both ends of the connecting frame. The two rotating rods are located in the same axial direction. Positioning mechanisms for positioning aerospace parts are installed at the ends of the two rotating rods that are far apart from each other. A snap-fit ​​component is installed at the end of the rotating shaft near the moving frame. When the rotating rod and the rotating shaft are in the same axial direction, the rotating rod near the moving frame can be snapped into the rotating shaft through the snap-fit ​​component.

[0011] Furthermore: the driving mechanism includes a threaded column that is horizontally rotatably mounted on a guide rail, the threaded column being threadedly connected to a moving block, and an electric motor for driving the threaded column to rotate is fixedly mounted on the guide rail.

[0012] Furthermore: the drive mechanism includes a second electric motor fixedly mounted on the top of the mounting block, and the output shaft of the second electric motor is connected to the rotating shaft through a bevel gear assembly.

[0013] Furthermore: the snap-fit ​​component includes a snap-fit ​​block fixedly installed at the end of the rotating shaft, and snap-fit ​​grooves are provided on the sides of the two rotating rods that are close to each other. The snap-fit ​​block can be inserted into the snap-fit ​​groove and snap-fit ​​with the rotating rod.

[0014] Furthermore: the positioning mechanism includes a positioning block fixedly installed at the end of the rotating rod. A receiving cavity is provided on the side of the positioning block away from the rotating rod. Clamping blocks are symmetrically slidably installed on the positioning block and within the receiving cavity. Clamping grooves with a V-shaped longitudinal section are provided on the side of the two clamping blocks that are close to each other. A bidirectional threaded rod is rotatably installed on the positioning block. The bidirectional threaded rod is threadedly connected to both clamping blocks.

[0015] Furthermore, protrusions are fixed in an equidistant array on the inner wall of the clamping groove.

[0016] Furthermore: a slot with an internal groove is provided on one side of the platform, and a collection box with an open top is inserted on the platform and in the slot. The collection box extends into the groove and fits against the inner side wall of the groove. A limiting member is installed on the platform to limit the collection box inserted into the slot.

[0017] Furthermore, the limiting member includes a limiting rod hinged to the base and located above the slot, the end of which may abut against the collection box inserted into the slot.

[0018] This utility model provides a quick-assembly lathe for machining aerospace parts. Compared with the prior art, it has the following advantages:

[0019] 1. When machining aerospace parts, the combination of two sets of positioning mechanisms and drive mechanisms replaces the method of first canceling the positioning mechanism to position the machined aerospace parts and then installing and positioning the next aerospace parts to be machined. This saves the time of installing and disassembling aerospace parts, achieves the effect of rapid installation of aerospace parts to be machined, and thus improves the machining efficiency of aerospace parts.

[0020] 2. By setting protrusions, when the aerospace parts are clamped by two clamping blocks, multiple protrusions on the inner side of the clamping groove abut against the aerospace parts, which replaces the method of the smooth surface of the inner sidewall of the clamping groove abutting against the aerospace parts, thereby increasing the friction between the clamping blocks and the aerospace parts and improving the positioning effect of the aerospace parts;

[0021] 3. By setting up a collection box, the waste generated during the cutting and processing of aerospace parts by this equipment can fall into the collection box under its own gravity, thereby achieving the cleaning effect of waste generated during the processing of aerospace parts and facilitating the cleaning of waste generated during the processing of aerospace parts; by setting up a limiting component, the collection box inserted into the slot can be limited. Attached Figure Description

[0022] To more clearly illustrate the technical solutions in the embodiments of this utility model or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this utility model. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0023] Figure 1 A three-dimensional structural schematic diagram of the present invention is shown;

[0024] Figure 2 A schematic diagram of the installation structure of the driving mechanism of this utility model is shown;

[0025] Figure 3 A schematic diagram of the mounting structure of the slider of this utility model is shown;

[0026] Figure 4 A schematic diagram of the installation structure of the snap-fit ​​component of this utility model is shown;

[0027] Figure 5 A schematic diagram of the installation structure of the clamping block of this utility model is shown;

[0028] Figure 6 This utility model illustrates Figure 5 Enlarged view of point A in the middle;

[0029] The figure shows: 1. Base; 11. Groove; 12. Guide rail; 13. Moving block; 131. Electric cylinder one; 14. Telescopic rod; 15. Moving frame; 151. Electric cylinder two; 16. Drive mechanism; 161. Threaded column; 162. Electric motor one; 17. Slider; 18. Mounting seat; 181. Mounting groove; 19. Lathe tool; 2. Mounting block; 21. Rotating shaft; 22. Motor; 23. Rotating shaft; 24. Connecting frame; 3. Drive mechanism; 31. Electric motor two; 32. Bevel gear assembly; 4. Positioning mechanism; 41. Positioning block; 411. Receiving cavity; 42. Clamping block; 421. Clamping groove; 422. Protrusion; 43. Bidirectional threaded rod; 5. Snap-fit ​​component; 51. Snap-fit ​​block; 6. Rotating rod; 61. Snap-fit ​​groove; 7. Collection box; 8. Limiting component; 81. Limiting rod. Detailed Implementation

[0030] To make the objectives, technical solutions, and advantages of the embodiments of this utility model clearer, the technical solutions in the embodiments of this utility model are described clearly and completely. Obviously, the described embodiments are only some embodiments of this utility model, not all embodiments. Based on the embodiments of this utility model, all other embodiments obtained by those skilled in the art without creative effort are within the protection scope of this utility model.

[0031] Example 1

[0032] To address the technical problems in the background section, the following quick-assembly lathe for machining aerospace parts is provided:

[0033] Combination Figures 1-6 As shown, the quick-assembly lathe for machining aerospace parts provided by this utility model includes a base 1. A groove 11 is formed on the top of the base 1. Guide rails 12 are symmetrically fixed on the top of the base 1 and on both sides of the groove 11. Moving blocks 13 are slidably mounted on each of the two guide rails 12 along the length of the base 1. Vertical telescopic rods 14 are fixed to the top of each moving block 13. Moving frames 15 are fixed to the top of the two telescopic rods 14. An electric cylinder 131 connected to the moving frame 15 is fixedly mounted on each moving block 13. A driving mechanism 1 that acts on the moving block 13 is mounted on one of the guide rails 12. 6. It is used to make the moving block 13 slide or stop sliding on the guide rail 12. The top of the moving frame 15 is slidably mounted with a slider 17 in a horizontal direction. An electric cylinder 151 connected to the slider 17 is fixedly mounted on the moving frame 15. A mounting seat 18 is fixedly mounted on one side of the slider 17. A mounting groove 181 is opened on the side of the mounting seat 18 away from the moving frame 15. A cutting tool 19 is inserted on the mounting seat 18 and located in the mounting groove 181, which is engaged with the mounting seat 18. The bottom end of the cutting tool 19 extends to the bottom of the moving frame 15. The cutting tool 19 and the mounting seat 18 are fixed by screws.

[0034] A mounting block 2 is fixedly mounted on the base 1 at the end of the mounting base 18 away from the slider 17. The top of the mounting block 2 extends above the base 1. A horizontal rotating shaft 21 is rotatably mounted on the mounting block 2. A motor 22 for driving the rotating shaft 21 to rotate is fixedly mounted on the mounting block 2.

[0035] A vertically oriented rotating shaft 23 is rotatably mounted on the mounting block 2. A connecting frame 24 is fixed to the top of the rotating shaft 23. A driving mechanism 3 that acts on the rotating shaft 23 is mounted on the mounting block 2, which is used to make the rotating shaft 23 rotate on the mounting block 2. Horizontally oriented rotating rods 6 are rotatably mounted at both ends of the connecting frame 24. The two rotating rods 6 are located in the same axial direction. Positioning mechanisms 4 for positioning aerospace parts are installed at the ends of the two rotating rods 6 that are far apart from each other. A snap-fit ​​component 5 is installed at the end of the rotating shaft 21 that is close to the moving frame 15. When the rotating rod 6 and the rotating shaft 21 are in the same axial direction, the rotating rod 6 that is close to the moving frame 15 can be snapped into the rotating shaft 21 through the snap-fit ​​component 5.

[0036] When machining aerospace parts, the aerospace parts to be machined are placed on the positioning mechanism 4 near the cutting tool 19. The positioning mechanism 4 positions the aerospace parts to be machined. The driving mechanism 16 causes the moving block 13 to slide on the guide rail 12 towards the positioning mechanism 4. During this process, the electric cylinder 131 causes the moving frame 15 to slide along the telescopic rod 14 to adjust the height of the moving frame 15. Then, with the cooperation of the electric cylinder 151, the slider 17 slides on the moving frame 15, thereby adjusting the position of the cutting tool 19 so that the cutting tool 19 contacts the aerospace parts to be machined. The control motor 22 causes the rotating shaft 21 to rotate on the mounting block 2, which in turn drives the rotating rod 6 to rotate on the connecting frame 24 through the snap-fit ​​5. This causes the positioning mechanism 4 to rotate the aerospace parts to be machined. With the cooperation of the driving mechanism 16 causing the moving block 13 to slide on the guide rail 12 towards the positioning mechanism 4, the machining of the aerospace parts can be achieved. During the cutting process, the next aerospace component to be cut can be placed on the positioning mechanism 4 for fixation. After the aerospace component on the positioning mechanism 4 near the moving frame 15 has been cut, the drive mechanism 3 causes the rotating shaft 23 to rotate on the mounting block 2, driving the connecting frame 24 to rotate around the rotating shaft 23, thus exchanging the positions of the two positioning mechanisms 4. This allows the next aerospace component to be cut to be close to the cutting tool 19. At this time, with the cooperation of the motor 22 and the drive mechanism 16, the next aerospace component to be cut can be cut. Thus, by cooperating with the two sets of positioning mechanisms 4 and the drive mechanism 3, the method of first canceling the positioning mechanism 4 to position the completed aerospace component and then installing and positioning the next aerospace component to be cut is replaced, saving the time of installing and disassembling aerospace components and achieving a rapid installation effect for aerospace components to be cut, thereby improving the processing efficiency of aerospace components.

[0037] Example 2

[0038] like Figures 1-6 As shown, based on the above embodiments, this embodiment further provides the following:

[0039] In this embodiment, the driving mechanism 16 includes a threaded post 161 that is horizontally rotatably mounted on the guide rail 12. The threaded post 161 is threadedly connected to the moving block 13. A motor 162 for driving the threaded post 161 to rotate is fixedly mounted on the guide rail 12. In use, the motor 162 is turned on to make the threaded post 161 rotate on the guide rail 12, thereby allowing the moving block 13 to slide on the guide rail 12, which is convenient for control.

[0040] In this embodiment, the drive mechanism 3 includes a second electric motor 31 fixedly mounted on the top of the mounting block 2. The output shaft of the second electric motor 31 is connected to the rotating shaft 23 through a bevel gear assembly 32. Specifically, the bevel gear assembly 32 includes two meshing bevel gears. One bevel gear is coaxially fixed to the rotating shaft 23, and the other bevel gear is coaxially fixed to the output shaft of the second electric motor 31. In use, the second electric motor 31 is turned on, and the output shaft of the second electric motor 31 rotates, which drives the rotating shaft 23 to rotate on the mounting block 2 through the bevel gear assembly 32, making it easy to control.

[0041] In this embodiment, the snap-fit ​​component 5 includes a snap-fit ​​block 51 fixedly installed at the end of the rotating shaft 21. Each of the two rotating rods 6 has a snap-fit ​​groove 61 on the side that is close to each other. The snap-fit ​​block 51 can be inserted into the snap-fit ​​groove 61 and snap-fit ​​with the rotating rod 6. In use, when the connecting frame 24 rotates around the rotating shaft 23, it drives the rotating rod 6 to rotate around the rotating shaft 23, so that the rotating rod 6 and the rotating shaft 21 are located in the same axial direction. The snap-fit ​​block 51 at the end of the rotating shaft 21 is inserted into the snap-fit ​​groove 61 and snap-fit ​​with the rotating rod 6, thereby realizing the snap-fit ​​effect between the rotating shaft 21 and the rotating rod 6.

[0042] Example 3

[0043] like Figures 1-6 As shown, based on the above embodiments, this embodiment further provides the following:

[0044] In this embodiment, the positioning mechanism 4 includes a positioning block 41 fixedly installed at the end of the rotating rod 6. A receiving cavity 411 is provided on the side of the positioning block 41 away from the rotating rod 6. Clamping blocks 42 are symmetrically slidably installed on the positioning block 41 and within the receiving cavity 411. Each clamping block 42 has a clamping groove 421 with a V-shaped longitudinal section on the side where the two clamping blocks 42 are close to each other. A bidirectional threaded rod 43 is rotatably installed on the positioning block 41. The bidirectional threaded rod 43 is threadedly connected to both clamping blocks 42. When positioning aerospace parts, the aerospace parts are inserted into the receiving cavity 411 and located inside the clamping grooves 421 on the two clamping blocks 42. The bidirectional threaded rod 43 is rotated to make the two clamping blocks 42 slide in opposite directions and approach each other within the receiving cavity 411. This allows both clamping blocks 42 to come into contact with the aerospace parts, thus achieving the positioning effect of the aerospace parts. The operation is simple.

[0045] In this embodiment, protrusions 422 are fixed at equal intervals on the inner wall of the clamping groove 421. By setting the protrusions 422, when the aerospace parts are clamped by the two clamping blocks 42, the multiple protrusions 422 on the inner side of the clamping groove 421 abut against the aerospace parts, which replaces the way that the smooth surface of the inner wall of the clamping groove 421 abuts against the aerospace parts, thereby increasing the friction between the clamping blocks 42 and the aerospace parts and improving the positioning effect of the aerospace parts.

[0046] In this embodiment, a slot with an internal groove 11 is provided on one side of the platform 1. A collection box 7 with an open top is inserted on the platform 1 and in the slot. The collection box 7 extends into the groove 11 and fits against the inner side wall of the groove 11. By setting the collection box 7, the waste generated during the cutting and processing of aerospace parts by this equipment can fall into the collection box 7 under its own gravity, thereby achieving the effect of cleaning up the waste generated during the processing of aerospace parts. The platform 1 is equipped with a limiting member 8 that acts on the collection box 7, which is used to limit the collection box 7 inserted into the slot. By setting the limiting member 8, the effect of limiting the collection box 7 inserted into the slot is achieved.

[0047] In this embodiment, the limiting member 8 includes a limiting rod 81 hinged to the base 1 and located above the slot. The end of the limiting rod 81 can abut against the collection box 7 inserted into the slot. When in use, when the collection box 7 is inserted into the slot, the limiting rod 81 is rotated so that its end abuts against the collection box 7 inserted into the slot, thereby achieving the limiting effect on the collection box 7.

[0048] It should be noted that, in this document, relational terms such as "first" and "second" are used only to distinguish one entity or operation from another, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Furthermore, the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such a process, method, article, or apparatus. Without further limitations, an element defined by the phrase "comprising one..." does not exclude the presence of other identical elements in the process, method, article, or apparatus that includes said element.

[0049] The above embodiments are only used to illustrate the technical solutions of this utility model, and are not intended to limit it. Although this utility model has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some of the technical features. Such modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the spirit and scope of the technical solutions of the embodiments of this utility model.

Claims

1. A quick-assembly lathe for machining aerospace parts, characterized in that: The device includes a base with a groove on its top. Guide rails are symmetrically fixed on the top of the base and on both sides of the groove. Moving blocks are slidably mounted on each guide rail along the length of the base. A vertical telescopic rod is fixed to the top of each moving block. A moving frame is fixed to the top of each telescopic rod. An electric cylinder connected to the moving frame is fixedly mounted on each moving block. A driving mechanism acting on the moving block is mounted on one of the guide rails, used to make the moving block slide or stop sliding on the guide rail. A slider is slidably mounted on the top of the moving frame in a horizontal direction. An electric cylinder connected to the slider is fixedly mounted on the moving frame. A mounting seat is fixedly mounted on one side of the slider. A mounting groove is formed on the side of the mounting seat away from the moving frame. A cutting tool is inserted into the mounting seat and engaged with the mounting seat. The bottom end of the cutting tool extends to the bottom of the moving frame. The cutting tool is fixed to the mounting seat by screws. A mounting block is fixedly mounted on the platform at the end of the mounting base away from the slider. The top of the mounting block extends above the platform. A horizontal rotating shaft is rotatably mounted on the mounting block. A motor for driving the rotating shaft to rotate is fixedly mounted on the mounting block. A vertically oriented rotating shaft is rotatably mounted on the mounting block. A connecting frame is fixed to the top of the rotating shaft. A drive mechanism acting on the rotating shaft is mounted on the mounting block to make the rotating shaft rotate on the mounting block. Horizontally oriented rotating rods are rotatably mounted at both ends of the connecting frame. The two rotating rods are located in the same axial direction. Positioning mechanisms for positioning aerospace parts are installed at the ends of the two rotating rods that are far apart from each other. A snap-fit ​​component is installed at the end of the rotating shaft near the moving frame. When the rotating rod and the rotating shaft are in the same axial direction, the rotating rod near the moving frame can be snapped into the rotating shaft through the snap-fit ​​component.

2. The quick-assembly lathe for machining aerospace parts according to claim 1, characterized in that: The driving mechanism includes a threaded column that is horizontally rotatably mounted on a guide rail. The threaded column is threadedly connected to a moving block. An electric motor for driving the threaded column to rotate is fixedly mounted on the guide rail.

3. The quick-assembly lathe for machining aerospace parts according to claim 1, characterized in that: The drive mechanism includes a second electric motor fixedly mounted on the top of the mounting block, and the output shaft of the second electric motor is connected to the rotating shaft through a bevel gear assembly.

4. The quick-assembly lathe for machining aerospace parts according to claim 1, characterized in that: The snap-fit ​​component includes a snap-fit ​​block fixedly installed at the end of the rotating shaft. Snap-fit ​​grooves are provided on the sides of the two rotating rods that are close to each other. The snap-fit ​​block can be inserted into the snap-fit ​​groove and snap-fit ​​with the rotating rod.

5. The quick-assembly lathe for machining aerospace parts according to claim 1, characterized in that: The positioning mechanism includes a positioning block fixedly installed at the end of the rotating rod. A receiving cavity is opened on the side of the positioning block away from the rotating rod. Clamping blocks are symmetrically slidably installed on the positioning block and in the receiving cavity. Clamping grooves with a V-shaped longitudinal section are opened on the side of the two clamping blocks that are close to each other. A bidirectional threaded rod is rotatably installed on the positioning block. The bidirectional threaded rod is threadedly connected to both clamping blocks.

6. The quick-assembly lathe for machining aerospace parts according to claim 5, characterized in that: The inner wall of the clamping groove is fixed with protrusions arranged in an equidistant array.

7. The quick-assembly lathe for machining aerospace parts according to claim 1, characterized in that: The platform has a slot with a groove on one side that is connected to the groove. A collection box with an open top is inserted into the slot on the platform. The collection box extends into the groove and fits against the inner side wall of the groove. A limiting member is installed on the platform to limit the collection box inserted into the slot.

8. The quick-assembly lathe for machining aerospace parts according to claim 7, characterized in that: The limiting member includes a limiting rod hinged to the base and located above the slot, the end of which can abut against the collection box inserted into the slot.

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