A device for machining a plate-like aircraft structural component

Abstract

The utility model provides a kind of processing device of plate-shaped aircraft structural member, it is related to processing device technical field. Including base, processing table and moving assembly, the base is rectangular solid structure, the bottom of processing table is fixedly connected with the top of base, the moving assembly is set in the top of processing table, the moving assembly includes L-shaped plate, the L-shaped plate is fixedly connected with one side of processing table, first hydraulic telescopic rod is mounted to the side of L-shaped plate, by setting moving assembly, first hydraulic telescopic rod drives U-shaped frame horizontal motion, so that U-shaped frame can be separated from processing table, cooperate overturning assembly simultaneously, so that the inner wall rotation of placing plate in U-shaped frame, and then the plate-shaped aircraft structural member on placing plate is guided, so that plate-shaped aircraft structural member slides along the inclination angle of placing plate, meanwhile, the debris on placing plate can be poured out, avoid affecting the following processing.

Description

Technical Field

[0001] This utility model relates to the field of processing equipment technology, and in particular to a processing equipment for plate-shaped aircraft structural parts. Background Technology

[0002] Plate-shaped aircraft structural components are among the most important structural components in aircraft structures. They are made of materials with very high strength and hardness and are often used to compose the exterior surfaces of aircraft. Plate-shaped aircraft structural components require the use of machining equipment for auxiliary processing.

[0003] In practical work, the existing processing equipment has a relatively complete structure and function, which can meet basic usage requirements, but the following problems still exist:

[0004] In practical applications, after the plate-shaped aircraft parts are processed, they need to be removed manually. This can lead to operator injury from processing debris on the plate-shaped aircraft parts. Furthermore, the plate-shaped aircraft structural parts on the exterior surface of the aircraft are usually curved. During the clamping process, conventional clamping components can only clamp flat structures and cannot perfectly adapt to the clamping of curved surfaces, which makes the aircraft structural parts prone to positional displacement during processing.

[0005] Therefore, this utility model provides a processing device for plate-shaped aircraft structural parts. Utility Model Content

[0006] The purpose of this invention is to overcome the shortcomings of the existing technology and provide a processing device for plate-shaped aircraft structural parts.

[0007] To achieve the above objectives, this utility model adopts the following technical solution: a processing device for plate-shaped aircraft structural parts, comprising:

[0008] The base is rectangular in shape.

[0009] A processing table, the bottom of which is fixedly connected to the top of the base;

[0010] A movable component is disposed on the top of the processing table. The movable component includes an L-shaped plate, which is fixedly connected to one side of the processing table. A first hydraulic telescopic rod is installed on one side of the L-shaped plate, and a U-shaped frame is fixedly connected to the output end of the first hydraulic telescopic rod.

[0011] A flipping assembly is disposed inside a U-shaped frame. The flipping assembly includes a drive motor, which is fixedly installed on one side of the U-shaped frame. A rotating rod is fixedly connected to the output end of the drive motor, and a placement plate is fixedly connected to the outer surface of the rotating rod.

[0012] A fixing component is installed on the top of the U-shaped frame. The fixing component includes a mounting block. A plurality of mounting slots are opened on one side of the mounting block. A fourth hydraulic telescopic rod is installed on the inner wall of the mounting slot. A pressure block is fixedly connected to the output end of the fourth hydraulic telescopic rod.

[0013] A plate-shaped aircraft structural component, which is placed on top of a placement plate.

[0014] The moving component drives the flipping component to move, so that after the plate-shaped aircraft structural parts are processed, the plate-shaped aircraft structural parts placed on the plate can be tilted and guided to a designated position for further processing. The entire process does not require manual handling, thus avoiding accidental damage.

[0015] Optionally, the top of the processing table is provided with a first rectangular groove, and the bottom of the U-shaped frame is fixedly connected with a first rectangular block, which is slidably disposed on the inner wall of the first rectangular groove.

[0016] The first rectangular block slides along the inner wall of the first rectangular groove, thereby guiding the machining table during its movement.

[0017] Optionally, a second rectangular groove is symmetrically provided on both sides of the first rectangular groove, and a second rectangular block is symmetrically fixedly connected to both sides of the first rectangular block, and the second rectangular block is slidably disposed on the inner wall of the second rectangular groove.

[0018] The second rectangular block slides along the inner wall of the second rectangular groove, and can also guide the first rectangular block during its movement.

[0019] Optionally, a U-shaped plate is fixedly connected to one side of the U-shaped frame, and a second hydraulic telescopic rod is installed on one side of the U-shaped plate.

[0020] The U-shaped plate can provide an installation platform for the second hydraulic telescopic rod, allowing it to work in conjunction with other components.

[0021] Optionally, a connecting circular plate is fixedly connected to the output end of the second hydraulic telescopic rod, and a circular clamping rod is fixedly connected to one side of the connecting circular plate.

[0022] The second hydraulic telescopic rod drives the connecting circular plate and the circular locking rod to move, so that the circular locking rod cooperates with other components to be fixed.

[0023] Optionally, a circular locking hole is provided on one side of the placement plate, and the circular locking rod passes through the U-shaped frame and engages with the inner wall of the circular locking hole.

[0024] The round clamp rod is inserted into the round clamp hole, which makes the placement plate and the U-shaped frame securely fixed.

[0025] Optionally, an L-shaped bracket is fixedly connected to the top of the U-shaped frame, and a third hydraulic telescopic rod is installed on the top of the L-shaped bracket. The output end of the third hydraulic telescopic rod is fixedly connected to the mounting block.

[0026] The third hydraulic telescopic rod drives the mounting block to move up and down, so that the mounting block, together with the fourth hydraulic telescopic rod and other components such as the pressure block, can fix the plate-shaped aircraft structural component.

[0027] Compared with the prior art, the advantages and positive effects of this utility model are as follows:

[0028] By setting up a moving component, the first hydraulic telescopic rod drives the U-shaped frame to move horizontally, allowing the U-shaped frame to separate from the processing table. At the same time, in conjunction with the flipping component, the placement plate rotates on the inner wall of the U-shaped frame, thereby guiding the plate-shaped aircraft structural parts on the placement plate. This allows the plate-shaped aircraft structural parts to slide down along the tilt angle of the placement plate, while also emptying the debris on the placement plate to avoid affecting subsequent processing.

[0029] By setting up a fixed component, the third hydraulic telescopic rod drives the installation block and other components to move. At the same time, the fourth hydraulic telescopic rod causes each pressure block to move a different distance, thus allowing the pressure block to fit and fix itself according to the shape of the plate-shaped aircraft structure. Attached Figure Description

[0030] Figure 1 A schematic diagram of a processing device for a plate-shaped aircraft structural component provided by this utility model;

[0031] Figure 2 A schematic diagram of the processing table structure of a processing device for a plate-shaped aircraft structural component provided by this utility model;

[0032] Figure 3 A schematic diagram of the structure of the placement plate of the processing device for a plate-shaped aircraft structural component provided by this utility model;

[0033] Figure 4 A schematic diagram of the first rectangular block of a processing device for a plate-shaped aircraft structural component provided by this utility model;

[0034] Figure 5 A schematic diagram of the mounting block of a processing device for a plate-shaped aircraft structural component provided by this utility model.

[0035] Legend:

[0036] 1. Base; 2. Processing table;

[0037] 3. Moving component; 31. L-shaped plate; 32. First hydraulic telescopic rod; 33. U-shaped frame; 34. First rectangular groove; 35. Second rectangular groove; 36. First rectangular block; 37. Second rectangular block;

[0038] 4. Flipping assembly; 41. Drive motor; 42. Rotating rod; 43. Placement plate; 44. U-shaped plate; 45. Second hydraulic telescopic rod; 46. Connecting circular plate; 47. Circular locking rod; 48. Circular locking hole;

[0039] 5. Fixing components; 51. L-shaped bracket; 52. Third hydraulic telescopic rod; 53. Mounting block; 54. Mounting groove; 55. Fourth hydraulic telescopic rod; 56. Pressure block;

[0040] 6. Plate-shaped aircraft structural components. Detailed Implementation

[0041] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the protection scope of the present utility model.

[0042] This embodiment provides a technical solution: such as Figures 1-5As shown, this embodiment of the present invention provides a processing device for a plate-shaped aircraft structural component, comprising a base 1, a processing table 2, a moving component 3, a flipping component 4, a fixing component 5, a plate-shaped aircraft structural component 6, a distance sensor, and an external control cabinet. The base 1 has a rectangular structure and provides overall support. Its top is provided with a positioning plane for positioning and connecting with the processing table 2. The bottom of the processing table 2 is fixedly connected to the top positioning plane of the base 1 by bolts. The fit error of the connection surface is no more than 0.1mm, forming a stable bearing foundation for the device. The moving component 3 is disposed on the top of the processing table 2 and includes an L-shaped plate. 31. The horizontal section of the L-shaped plate 31 is detachably fixed to one side of the processing table 2 by countersunk bolts, with a bolt connection depth of not less than 15mm. The vertical section of the L-shaped plate 31 facing the processing table 2 is fixedly connected to the first hydraulic telescopic rod 32 by a flange. A sealing gasket is provided on the flange contact surface. The output end of the first hydraulic telescopic rod 32 extends along the length direction of the processing table 2 and is fixedly connected to the side wall of the U-shaped frame 33 by welding, with a welding strength of not less than 500MPa. The flipping assembly 4 is set inside the U-shaped frame 33. The flipping assembly 4 includes a drive motor 41, which is connected to the U-shaped frame 33 by a motor base. The frame 33 is fixedly connected to one side of the outer wall. A shock-absorbing pad is provided between the motor base and the U-shaped frame 33. The output end of the drive motor 41 passes through the side wall of the U-shaped frame 33 and is fixedly connected to the rotating rod 42 by a key. The keyway clearance is 0.02-0.05mm. The outer surface of the rotating rod 42 is coaxially fixedly connected to the placement plate 43 for supporting the workpiece by an interference fit. The interference amount is 0.01-0.03mm. The fixing component 5 is installed on the top of the U-shaped frame 33. The fixing component 5 includes a mounting block 53. The mounting block 53 has several horizontally evenly distributed mounting slots on the side facing the placement plate 43. 54. The inner wall of each mounting slot 54 is fixedly connected to the fourth hydraulic telescopic rod 55 by a threaded connection. The thread engagement depth is not less than 10mm. The output end of the fourth hydraulic telescopic rod 55 extends toward the placement plate 43 and is detachably fixedly connected to the pressure block 56 used to clamp the workpiece by a thread. The pressure block 56 is equipped with a distance sensor (not shown in the figure) and is used in conjunction with the external control cabinet (not shown in the figure). The plate-shaped aircraft structure 6 is detachably placed on the top of the placement plate 43 and forms a clamping and fixing engagement with the placement plate 43 through the pressure block 56 of the fixing component 5. The clamping force can be adjusted within a range of 500-2000N.

[0043] The moving component 3 drives the U-shaped frame 33 to move, which in turn drives the flipping component 4 to move. Under the action of the flipping component 4, the plate-shaped aircraft structure 6 is guided and unloaded. The fixing component 5 fixes the plate-shaped aircraft structure 6 during processing.

[0044] like Figure 2As shown, a first rectangular groove 34 is provided on the top of the processing table 2 along the length direction. The groove wall roughness is Ra1.6μm. A first rectangular block 36 is fixedly connected to the bottom of the U-shaped frame 33 by welding to the position corresponding to the first rectangular groove 34. The first rectangular block 36 and the first rectangular groove 34 form a sliding fit with a fit clearance of 0.05-0.1mm. The outer wall of the first rectangular block 36 is fully fitted with the inner wall of the first rectangular groove 34.

[0045] like Figure 2 and Figure 4 As shown, the two sides of the first rectangular groove 34 are symmetrically provided with second rectangular grooves 35 along the length direction. The second rectangular grooves 35 are perpendicularly connected to the first rectangular groove 34. The two sides of the first rectangular block 36 are fixedly connected with second rectangular blocks 37 by bolts to the positions of the second rectangular grooves 35. The second rectangular blocks 37 and the second rectangular grooves 35 correspond one-to-one and form a sliding fit with a fit clearance of 0.03-0.08mm. The outer wall of the second rectangular block 37 is fitted to the inner wall of the second rectangular groove 35, and the length of the second rectangular block 37 is the same as the length of the first rectangular block 36, which together restrict the vertical displacement of the U-shaped frame 33.

[0046] like Figure 3 As shown, a U-shaped plate 44 is fixedly connected to the outer wall of the U-shaped frame 33 away from the drive motor 41 by welding. The welding joint adopts a fillet weld with a weld leg height of not less than 8mm. The opening of the U-shaped plate 44 faces the U-shaped frame 33, and the vertical section of the U-shaped plate 44 is fixedly connected to the second hydraulic telescopic rod 45 by bolts. There are no less than 2 bolts, which are symmetrically distributed. The output end of the second hydraulic telescopic rod 45 extends horizontally toward the U-shaped frame 33 and remains parallel to the side wall of the U-shaped frame 33.

[0047] like Figure 3 As shown, the output end of the second hydraulic telescopic rod 45 is fixedly connected to the connecting circular plate 46 by a thread, the thread engagement length is not less than 12mm, and the side of the connecting circular plate 46 facing the U-shaped frame 33 is fixedly connected to the circular clamp rod 47 coaxially by welding. The axis of the circular clamp rod 47 coincides with the axis of the output shaft of the second hydraulic telescopic rod 45, and the coaxiality error is not greater than 0.02mm.

[0048] like Figure 3 As shown, a circular locking hole 48 is provided on one side wall of the placement plate 43 corresponding to the position of the circular locking rod 47. The axis of the circular locking hole 48 intersects perpendicularly with the axis of the rotating rod 42. The diameter of the circular locking hole 48 is clearance-fitted with the outer diameter of the circular locking rod 47, with a clearance of 0.01-0.03mm. After the circular locking rod 47 passes through the side wall of the U-shaped frame 33, it forms a detachable locking engagement with the inner wall of the circular locking hole 48. The locking depth is not less than 1 / 2 of the length of the circular locking rod 47, so as to achieve positioning and fixation of the placement plate 43 after flipping and prevent rotation.

[0049] like Figure 3 and Figure 5 As shown, an L-shaped bracket 51 is fixedly connected to the top crossbeam of the U-shaped frame 33 by bolts. The bolts are locked with anti-loosening nuts. The horizontal section of the L-shaped bracket 51 extends along the width direction of the U-shaped frame 33, and the top of the horizontal section of the L-shaped bracket 51 is fixedly connected to the third hydraulic telescopic rod 52 to ensure that the output end of the third hydraulic telescopic rod 52 extends vertically. The output end of the third hydraulic telescopic rod 52 extends downward vertically and is fixedly connected to the top of the mounting block 53 by threads. Anti-loosening glue is provided at the threaded connection to drive the mounting block 53 to rise and fall stably in the vertical direction. The verticality error of the rise and fall is not greater than 0.05mm / m.

[0050] Working principle:

[0051] like Figure 1-5 As shown:

[0052] In use, the plate-shaped aircraft structure 6 is placed on the placement plate 43. At this time, the third hydraulic telescopic rod 52 is activated to move the mounting block 53 to the appropriate position. Then, the fourth hydraulic telescopic rod 55 is activated to press the pressure block 56 to secure the plate-shaped aircraft structure 6.

[0053] At this time, the first hydraulic telescopic rod 32 is activated, so that the U-shaped frame 33 can drive the first rectangular block 36 to slide on the inner wall of the first rectangular groove 34, and at the same time drive the second rectangular block 37 to slide on the inner wall of the second rectangular groove 35, so that the U-shaped frame 33 moves to the appropriate position.

[0054] At this time, the second hydraulic telescopic rod 45 is activated, causing the round locking rod 47 to separate from the round locking hole 48. The drive motor 41 is activated, causing the rotating rod 42 to drive the placement plate 43 to rotate, causing the plate-shaped aircraft structural component 6 on the placement plate 43 to separate from the placement plate 43.

[0055] The above description is merely a preferred embodiment of the present utility model and is not intended to limit the present utility model in any other way. Any person skilled in the art may make changes or modifications to the above-disclosed technical content to create equivalent embodiments for application in other fields. However, any simple modifications, equivalent changes, and modifications made to the above embodiments based on the technical essence of the present utility model without departing from the technical solution of the present utility model shall still fall within the protection scope of the technical solution of the present utility model.

Claims

1. A processing apparatus for plate-shaped aircraft structural components, characterized in that, include: The base (1) has a rectangular structure; A processing table (2), the bottom of which is fixedly connected to the top of the base (1); The moving component (3) is set on the top of the processing table (2). The moving component (3) includes an L-shaped plate (31). The L-shaped plate (31) is fixedly connected to one side of the processing table (2). A first hydraulic telescopic rod (32) is installed on one side of the L-shaped plate (31). A U-shaped frame (33) is fixedly connected to the output end of the first hydraulic telescopic rod (32). A flipping assembly (4) is disposed inside a U-shaped frame (33). The flipping assembly (4) includes a drive motor (41). The drive motor (41) is fixedly installed on one side of the U-shaped frame (33). A rotating rod (42) is fixedly connected to the output end of the drive motor (41). A placement plate (43) is fixedly connected to the outer surface of the rotating rod (42). A fixing component (5) is installed on the top of the U-shaped frame (33). The fixing component (5) includes a mounting block (53). A plurality of mounting slots (54) are provided on one side of the mounting block (53). A fourth hydraulic telescopic rod (55) is installed on the inner wall of the mounting slot (54). A pressure block (56) is fixedly connected to the output end of the fourth hydraulic telescopic rod (55). A plate-shaped aircraft structural component (6) is placed on top of a placement plate (43).

2. The processing apparatus for plate-shaped aircraft structural components according to claim 1, characterized in that: The top of the processing table (2) is provided with a first rectangular groove (34), and the bottom of the U-shaped frame (33) is fixedly connected with a first rectangular block (36), which is slidably disposed on the inner wall of the first rectangular groove (34).

3. The processing apparatus for plate-shaped aircraft structural components according to claim 2, characterized in that: The first rectangular groove (34) has a second rectangular groove (35) symmetrically opened on both sides, and the first rectangular block (36) has a second rectangular block (37) symmetrically fixedly connected on both sides. The second rectangular block (37) is slidably disposed on the inner wall of the second rectangular groove (35).

4. The processing apparatus for plate-shaped aircraft structural components according to claim 1, characterized in that: A U-shaped plate (44) is fixedly connected to one side of the U-shaped frame (33), and a second hydraulic telescopic rod (45) is installed on one side of the U-shaped plate (44).

5. The processing apparatus for plate-shaped aircraft structural components according to claim 4, characterized in that: The output end of the second hydraulic telescopic rod (45) is fixedly connected to a connecting circular plate (46), and a circular clamp rod (47) is fixedly connected to one side of the connecting circular plate (46).

6. The processing apparatus for plate-shaped aircraft structural components according to claim 5, characterized in that: A circular locking hole (48) is provided on one side of the placement plate (43), and the circular locking rod (47) passes through the U-shaped frame (33) and is engaged with the inner wall of the circular locking hole (48).

7. The processing apparatus for plate-shaped aircraft structural components according to claim 1, characterized in that: The top of the U-shaped frame (33) is fixedly connected to an L-shaped bracket (51), and a third hydraulic telescopic rod (52) is installed on the top of the L-shaped bracket (51). The output end of the third hydraulic telescopic rod (52) is fixedly connected to the mounting block (53).

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