CN117047523A - Large-stroke aircraft tail wing processing machine tool - Google Patents
Large-stroke aircraft tail wing processing machine tool Download PDFInfo
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- CN117047523A CN117047523A CN202311140845.6A CN202311140845A CN117047523A CN 117047523 A CN117047523 A CN 117047523A CN 202311140845 A CN202311140845 A CN 202311140845A CN 117047523 A CN117047523 A CN 117047523A
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- 238000003754 machining Methods 0.000 claims abstract description 12
- 230000007306 turnover Effects 0.000 claims abstract description 8
- 238000007514 turning Methods 0.000 claims description 16
- 230000008878 coupling Effects 0.000 claims description 10
- 238000010168 coupling process Methods 0.000 claims description 10
- 238000005859 coupling reaction Methods 0.000 claims description 10
- 125000006850 spacer group Chemical group 0.000 claims description 9
- 230000005540 biological transmission Effects 0.000 claims description 7
- 238000006073 displacement reaction Methods 0.000 description 9
- 238000000034 method Methods 0.000 description 8
- 230000008569 process Effects 0.000 description 5
- 230000001360 synchronised effect Effects 0.000 description 4
- 238000004519 manufacturing process Methods 0.000 description 3
- 230000007246 mechanism Effects 0.000 description 3
- 238000010586 diagram Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000005520 cutting process Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 230000004044 response Effects 0.000 description 1
- 230000003068 static effect Effects 0.000 description 1
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23Q—DETAILS, COMPONENTS, OR ACCESSORIES FOR MACHINE TOOLS, e.g. ARRANGEMENTS FOR COPYING OR CONTROLLING; MACHINE TOOLS IN GENERAL CHARACTERISED BY THE CONSTRUCTION OF PARTICULAR DETAILS OR COMPONENTS; COMBINATIONS OR ASSOCIATIONS OF METAL-WORKING MACHINES, NOT DIRECTED TO A PARTICULAR RESULT
- B23Q3/00—Devices holding, supporting, or positioning work or tools, of a kind normally removable from the machine
- B23Q3/02—Devices holding, supporting, or positioning work or tools, of a kind normally removable from the machine for mounting on a work-table, tool-slide, or analogous part
- B23Q3/06—Work-clamping means
- B23Q3/08—Work-clamping means other than mechanically-actuated
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23Q—DETAILS, COMPONENTS, OR ACCESSORIES FOR MACHINE TOOLS, e.g. ARRANGEMENTS FOR COPYING OR CONTROLLING; MACHINE TOOLS IN GENERAL CHARACTERISED BY THE CONSTRUCTION OF PARTICULAR DETAILS OR COMPONENTS; COMBINATIONS OR ASSOCIATIONS OF METAL-WORKING MACHINES, NOT DIRECTED TO A PARTICULAR RESULT
- B23Q1/00—Members which are comprised in the general build-up of a form of machine, particularly relatively large fixed members
- B23Q1/01—Frames, beds, pillars or like members; Arrangement of ways
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23Q—DETAILS, COMPONENTS, OR ACCESSORIES FOR MACHINE TOOLS, e.g. ARRANGEMENTS FOR COPYING OR CONTROLLING; MACHINE TOOLS IN GENERAL CHARACTERISED BY THE CONSTRUCTION OF PARTICULAR DETAILS OR COMPONENTS; COMBINATIONS OR ASSOCIATIONS OF METAL-WORKING MACHINES, NOT DIRECTED TO A PARTICULAR RESULT
- B23Q1/00—Members which are comprised in the general build-up of a form of machine, particularly relatively large fixed members
- B23Q1/01—Frames, beds, pillars or like members; Arrangement of ways
- B23Q1/017—Arrangements of ways
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23Q—DETAILS, COMPONENTS, OR ACCESSORIES FOR MACHINE TOOLS, e.g. ARRANGEMENTS FOR COPYING OR CONTROLLING; MACHINE TOOLS IN GENERAL CHARACTERISED BY THE CONSTRUCTION OF PARTICULAR DETAILS OR COMPONENTS; COMBINATIONS OR ASSOCIATIONS OF METAL-WORKING MACHINES, NOT DIRECTED TO A PARTICULAR RESULT
- B23Q1/00—Members which are comprised in the general build-up of a form of machine, particularly relatively large fixed members
- B23Q1/25—Movable or adjustable work or tool supports
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23Q—DETAILS, COMPONENTS, OR ACCESSORIES FOR MACHINE TOOLS, e.g. ARRANGEMENTS FOR COPYING OR CONTROLLING; MACHINE TOOLS IN GENERAL CHARACTERISED BY THE CONSTRUCTION OF PARTICULAR DETAILS OR COMPONENTS; COMBINATIONS OR ASSOCIATIONS OF METAL-WORKING MACHINES, NOT DIRECTED TO A PARTICULAR RESULT
- B23Q3/00—Devices holding, supporting, or positioning work or tools, of a kind normally removable from the machine
- B23Q3/02—Devices holding, supporting, or positioning work or tools, of a kind normally removable from the machine for mounting on a work-table, tool-slide, or analogous part
- B23Q3/06—Work-clamping means
- B23Q3/08—Work-clamping means other than mechanically-actuated
- B23Q3/088—Work-clamping means other than mechanically-actuated using vacuum means
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Machine Tool Units (AREA)
Abstract
The application discloses a large-stroke aircraft tail wing processing machine tool, which relates to the technical field of machining and comprises a workbench and a turnover assembly. According to the application, the aircraft tail wing is adsorbed on the wire harness frame through the first sucker array and the second sucker array, suction force is distributed by the vacuum generator and the pipelines are bound on two sides of the wire harness frame through the first sucker array and the second sucker array, so that a blank processing area in the wire harness frame is created, the second sucker array can be used for adjusting the position and the distance in the adjusting groove through the I-shaped sliding block so as to adapt to the curved surface of the height fluctuation of the aircraft tail wing, when the aircraft tail wing is used, the driving motor drives the overturning shaft to rotate through the shaft rod, the limiting plates coaxially fixed at the root of the shaft rod are matched with the limiting plates at two ends of the stroke, so that the overturning stroke of the overturning shaft is controlled, and the aircraft tail wing can realize overturning adjustment of the processing surfaces on the front side and the back side without repeated clamping, so that on one hand, positioning errors caused by repeated clamping can be reduced, and on the other hand, and downtime caused by repeated clamping is saved.
Description
Technical Field
The application relates to the technical field of machining, in particular to a large-stroke aircraft tail wing machining machine tool.
Background
In the field of machining, along with the increasing complexity of the design of modern mechanical parts, space freeform surface parts are widely applied to various key fields such as aerospace, automobiles and the like, higher requirements are put forward on modern machining processes and manufacturing and machining equipment, and in order to meet the above functional configuration, a series-parallel machine tool combining the advantages of a series machine tool and a parallel machine tool is widely applied in industry, and the machine tool has the advantages of large working space of the series machine tool, good dynamic response characteristic, easiness in realizing high-speed movement and the like, and is more suitable for high-speed cutting machining of the space freeform surface parts.
At present, most five-degree-of-freedom parallel machine tools adopt a four-degree-of-freedom parallel mechanism to connect in series a single-degree-of-freedom rotary part, such as a rotary processing head connected in series with a movable platform of the four-degree-of-freedom parallel mechanism or a rotary disk connected in series with a static platform, although the working space of the five-degree-of-freedom parallel machine tools is increased compared with that of the parallel machine tools, only one four-degree-of-freedom parallel mechanism is connected in series with a single-degree-of-freedom part, the processing surface of the single-degree-of-freedom parallel machine tools is a small-range characteristic curved surface such as a spherical surface or a cylindrical surface, and the like, and the single-degree-of-freedom parallel machine tools are not suitable for processing long-axis workpieces and large-area workpieces, in addition, although the five-axis linkage processing center can realize all-dimensional processing of workpieces, the workpiece clamping on a working table surface is not processed, however, the plane tail wing needs to be processed, and the plane tail wing needs to be disassembled from the clamping position and turned over for re-clamping when the plane tail wing is processed, and the processing precision of the tail wing cannot be influenced by repeated clamping.
In view of the above, an improvement is made in view of the existing structural shortcomings, and a long-stroke aircraft tail processing machine tool is proposed.
Disclosure of Invention
The application aims to provide a large-stroke aircraft tail wing processing machine tool to solve the problems in the background technology.
In order to achieve the above purpose, the present application provides the following technical solutions: the utility model provides a large-stroke aircraft fin machine tool, includes workstation and upset subassembly, the chamber of dodging has been seted up at the workstation middle part, upset subassembly fixed mounting is in the workstation right-hand member, upset subassembly includes motor mounting panel, driving motor, axostylus axostyle, limiting plate, spacer pin, shaft coupling, trip shaft, sucking disc array one, vacuum generator, wire harness frame and adjustment tank, motor mounting panel right-hand member fixed mounting has driving motor, and driving motor left side output fixedly connected with axostylus axostyle, the coaxial limiting plate that is fixed with of axostylus axostyle root, and the corresponding spacer pin that is equipped with in spacer pin stroke both ends to the spacer pin is fixed in dodges chamber opening right-hand member, the terminal fixedly connected with shaft coupling of axostylus axostyle, and the axostylus axostyle has the trip shaft through the coaxial transmission of shaft coupling, the trip shaft upper plane is equipped with sucking disc array one, and the lower plane fixed mounting of trip shaft has vacuum generator, trip shaft side integral type is fixed with wire harness frame, and the wire harness frame end has seted up the adjustment tank along its extending direction.
Further, the H-shaped sliding block is slidably mounted in the adjusting groove, a threaded hole is formed in the middle of the H-shaped sliding block, the sucker array II is connected with the middle of the threaded hole in a threaded mode, and the sucker array II and the sucker array I are communicated with the vacuum generator through a pipeline.
Further, the boss is integrally fixed with the rear end of the workbench, and the electric transverse rail is fixedly arranged at the top end of the boss.
Further, the top of the electric transverse rail is slidably provided with an X-axis sliding block along the extending direction of the electric transverse rail, and the top of the X-axis sliding block is fixedly provided with an electric longitudinal rail.
Further, the middle part of the electric vertical rail is provided with a Y-axis sliding block in a sliding manner along the extending direction of the electric vertical rail, the middle part of the Y-axis sliding block is fixedly provided with an electric vertical rail, and the front surface of the electric vertical rail is provided with a Z-axis sliding block in a sliding manner along the extending direction of the electric vertical rail.
Further, the output angle adjusting component is arranged inside the bottom end of the Z-axis sliding block and comprises an upper plate, an input shaft, a turning gear set and a first motor, the middle part of the straight end of the upper plate is rotatably provided with the input shaft, the top of the input shaft is coaxially connected with the turning gear set, and the side surface of the turning gear set is coaxially connected with the first motor.
Further, the output angle adjusting assembly further comprises a double-cross universal joint, a spline shaft and an output shaft, the bottom of the input shaft is in transmission connection with the double-cross universal joint, the spline shaft is slidably mounted in the middle of the double-cross universal joint, and the bottom of the double-cross universal joint is in transmission connection with the output shaft.
Further, the output angle adjusting assembly further comprises a second motor and a rocker, the second motor is fixedly arranged on the left side of the vertical end of the upper plate, and the rocker is fixedly connected with the output end of the second motor.
Further, the output angle adjusting assembly further comprises a lower plate and a synchronous gear set, the output end of the rocker is fixedly connected with the lower plate, and the output end of the rocker is coaxially connected with the synchronous gear set.
Further, the output angle adjusting assembly further comprises an electric cylinder and an angle adjusting slide block, the electric cylinder is fixedly arranged on the left side of the vertical end of the lower plate, the angle adjusting slide block is fixedly connected with the output end of the electric cylinder, the angle adjusting slide block is slidably mounted inside the straight end of the lower plate, and an output shaft is rotatably mounted inside the angle adjusting slide block.
The application provides a long-stroke aircraft tail wing processing machine tool, which has the following beneficial effects:
1. in the use process, the aircraft tail wing is adsorbed on the wire harness frame through the first sucker array and the second sucker array, suction force is distributed by the vacuum generator and pipelines are bound on two sides of the wire harness frame through the first sucker array and the second sucker array, so that a blank processing area in the wire harness frame is created, the second sucker array can be used for adjusting the position and the distance in the adjusting groove through the I-shaped sliding block so as to adapt to the curved surface of the height fluctuation of the aircraft tail wing, when the aircraft tail wing is used, the driving motor drives the overturning shaft to rotate through the shaft rod, the limiting plates coaxially fixed at the root of the shaft rod are matched with the limiting plates at the two ends of the stroke to realize the control of the overturning stroke of the overturning shaft, and the aircraft tail wing can realize the overturning adjustment of the processing surfaces at the front side and the back side without repeated clamping.
2. In the use process, the workbench of the application has no A shaft which can rotate around the X shaft on the traditional lathe bed and no C shaft of the traditional rotary table due to the overturning processing requirement of the tail wing of the airplane, so the application meets the full-aspect processing requirement of a workpiece through the output angle adjusting component.
3. In the use process of the application, the X-axis sliding block realizes the displacement adjustment in the X-axis direction by the movement in the extending direction of the electric transverse rail, the Y-axis sliding block realizes the displacement adjustment in the Y-axis direction by the movement in the extending direction of the electric longitudinal rail, and the Z-axis sliding block realizes the displacement adjustment in the Z-axis direction by the movement in the extending direction of the electric vertical rail, and the travel of the machine tool is increased by increasing the completable relative movement distance of the five-axis machine tool, so that the five-axis machine tool can adapt to the processing requirements of long-axis workpieces and large-area workpieces.
Drawings
FIG. 1 is a schematic overall elevational view of the present application;
FIG. 2 is a schematic elevational view of the flip assembly of the present application;
FIG. 3 is an enlarged schematic view of the structure of FIG. 2A according to the present application;
FIG. 4 is a schematic diagram of the front view of the H-shaped slider of the present application;
FIG. 5 is a schematic view of the whole part structure of the present application;
fig. 6 is a schematic diagram showing the internal structure of the output angle adjusting assembly according to the present application.
In the figure: 1. a work table; 2. an avoidance cavity; 3. a flip assembly; 301. a motor mounting plate; 302. a driving motor; 303. a shaft lever; 304. a limiting plate; 305. a limiting pin; 306. a coupling; 307. a turnover shaft; 308. a sucker array I; 309. a vacuum generator; 310. a wire harness frame; 311. an adjustment tank; 4. an I-shaped sliding block; 5. a threaded hole; 6. a second sucker array; 7. a boss; 8. an electric transverse rail; 9. an X-axis sliding block; 10. an electric longitudinal rail; 11. a Y-axis slider; 12. electric vertical rail; 13. a Z-axis slider; 14. an output angle adjustment assembly; 1401. an upper plate; 1402. an input shaft; 1403. a turning gear set; 1404. a first motor; 1405. double cross universal joints; 1406. a spline shaft; 1407. an output shaft; 1408. a second motor; 1409. a rocker; 1410. a lower plate; 1411. a synchronizing gear set; 1412. an electric cylinder; 1413. an angle adjusting slide block.
Detailed Description
Embodiments of the present application are described in further detail below with reference to the accompanying drawings and examples. The following examples are illustrative of the application but are not intended to limit the scope of the application
Referring to fig. 1 to 4, the present application provides a technical solution: the utility model provides a large-stroke aircraft fin machine tool, including workstation 1 and upset subassembly 3, dodge chamber 2 has been seted up at workstation 1 middle part, upset subassembly 3 fixed mounting is in workstation 1 right-hand member, upset subassembly 3 includes motor mounting panel 301, driving motor 302, axostylus axostyle 303, limiting plate 304, spacer pin 305, shaft coupling 306, upset axle 307, sucking disc array one 308, vacuum generator 309, wire harness frame 310 and adjustment tank 311, motor mounting panel 301 right-hand member fixed mounting has driving motor 302, and driving motor 302 left side output fixedly connected with axostylus axostyle 303, limiting plate 304 is fixed with on the root coaxial, and limiting plate 304 stroke both ends correspond to be equipped with spacer pin 305, and spacer pin 305 is fixed in dodge chamber 2 opening right-hand member, axostylus axostyle 303 end fixedly connected with shaft coupling 306, and axostylus axostyle 303 pass through the coaxial transmission of coupling 306 have upset axle 307, the upper plane of upset axle 307 is equipped with sucking disc array one 308, and the lower plane of upset axle 307 is fixedly mounted with vacuum generator 309, wire harness frame 310 is integrally fixed with on the side of side, and wire harness frame 310 end along its extending direction has adjustment tank 311, adjustment tank 311 is opened at the end, and two end slider shape of the end of the axial end is equipped with 5 sliding block in the middle part of the axial direction of rotation device 6 and sucking disc array 6, threaded hole array 6 is connected with sucking disc array 5, threaded hole 6 is formed in the shape of sucking disc array 6 and has been connected with the sucking disc array 6;
the method comprises the specific operations that the tail wing is adsorbed on the wire harness frame 310 through the first sucker array 308 and the second sucker array 6, suction force is distributed by the first sucker array 308 and the second sucker array 6 through the vacuum generator 309, and pipelines are bound on two sides of the wire harness frame 310, so that a blank processing area in the wire harness frame 310 is created, the second sucker array 6 can be further adjusted to be positioned in the adjusting groove 311 through the I-shaped sliding block 4 so as to adapt to the curved surface of the height fluctuation of the tail wing of the aircraft, when the method is used, the driving motor 302 drives the turning shaft 307 to rotate through the shaft rod 303, the limiting plate 304 coaxially fixed at the root of the shaft rod 303 is matched with the limiting plates 304 at two ends of a stroke, so that the turning stroke of the turning shaft 307 is controlled, and the turning adjustment of the processing surfaces on the front side and the back sides of the tail wing of the aircraft can be realized without repeated clamping, on one hand, positioning errors caused by repeated clamping can be reduced, on the other hand, the downtime caused by repeated clamping is saved, the machining efficiency of the tail wing of the aircraft is improved, and the production time is shortened;
referring to fig. 5, a boss 7 is integrally fixed at the rear end of the workbench 1, an electric transverse rail 8 is fixedly mounted at the top end of the boss 7, an X-axis sliding block 9 is slidably mounted at the top of the electric transverse rail 8 along the extending direction of the electric transverse rail, an electric longitudinal rail 10 is fixedly mounted at the top of the X-axis sliding block 9, a Y-axis sliding block 11 is slidably mounted at the middle part of the electric longitudinal rail 10 along the extending direction of the electric longitudinal rail, an electric vertical rail 12 is fixedly mounted at the middle part of the Y-axis sliding block 11, and a Z-axis sliding block 13 is slidably mounted at the front surface of the electric vertical rail 12 along the extending direction of the electric vertical rail;
the method comprises the following specific operations that in the using process, the X-axis sliding block 9 realizes displacement adjustment in the X-axis direction through the movement in the extending direction of the electric transverse rail 8, the Y-axis sliding block 11 realizes displacement adjustment in the Y-axis direction through the movement in the extending direction of the electric longitudinal rail 10, and the Z-axis sliding block 13 realizes displacement adjustment in the Z-axis direction through the movement in the extending direction of the electric vertical rail 12, and the stroke of the machine tool is increased by increasing the completable relative movement distance of the five-axis machine tool, so that the five-axis machine tool can adapt to the processing requirements of long-axis workpieces and large-area workpieces;
referring to fig. 6, an output angle adjusting assembly 14 is disposed inside the bottom end of the z-axis slider 13, the output angle adjusting assembly 14 includes an upper plate 1401, an input shaft 1402, a turning gear set 1403 and a motor one 1404, the input shaft 1402 is rotatably mounted in the middle of the flat end of the upper plate 1401, the turning gear set 1403 is coaxially connected to the top of the input shaft 1402, the motor one 1404 is coaxially connected to the side surface of the turning gear set 1403, the output angle adjusting assembly 14 further includes a double cross universal joint 1405, a spline shaft 1406 and an output shaft 1407, the bottom of the input shaft 1402 is in transmission connection with the double cross universal joint 1405, the spline shaft 1406 is slidably mounted in the middle of the double cross universal joint 1405, the output shaft 1407 is in transmission connection with the bottom of the double cross universal joint 1405, the output angle adjusting assembly 14 further comprises a motor II 1408 and a rocker 1409, the motor II 1408 is fixedly arranged on the left side of the vertical end of the upper plate 1401, the rocker 1409 is fixedly connected to the output end of the motor II 1408, the output angle adjusting assembly 14 further comprises a lower plate 1410 and a synchronous gear set 1411, the output end of the rocker 1409 is fixedly connected with the lower plate 1410, the output end of the rocker 1409 is coaxially connected with the synchronous gear set 1411, the output angle adjusting assembly 14 further comprises an electric cylinder 1412 and an angle adjusting slide block 1413, the electric cylinder 1412 is fixedly arranged on the left side of the vertical end of the lower plate 1410, the angle adjusting slide block 1413 is slidably arranged in the straight end of the lower plate 1410, and the output shaft 1407 is rotatably arranged in the angle adjusting slide block 1413;
when the device is used, a motor I1404 rotates and drives an input shaft 1402 through a turning gear set 1403, a further input shaft 1402 rotates and drives an output shaft 1407 through a double-cross universal joint 1405, an angle adjusting sliding block 1413 is driven to slide at the straight end of a lower plate 1410 through an electric cylinder 1412, the output shaft 1407 can be subjected to pitching adjustment through a spline shaft 1406 slidably arranged in the middle of the double-cross universal joint 1405, a motor II 1408 swings the lower plate 1410 through a rocker 1409, and the left and right yaw adjustment can be performed on the output shaft 1407, so that the device is not limited to the single-degree-of-freedom rotary output shaft 1407, the processing angle of the output shaft 1407 is flexible and adjustable, higher degrees of freedom and parallel degree are provided, and the device can adapt to the processing requirements of characteristic curved surfaces of airplane tail wings during processing.
In summary, a large-stroke aircraft tail wing processing machine tool is provided, the aircraft tail wing is adsorbed on a wire harness frame 310 through a first sucker array 308 and a second sucker array 6, the first sucker array 308 and the second sucker array 6 distribute suction force by a vacuum generator 309 and tie pipes on two sides of the wire harness frame 310, thereby creating a blank processing area in the wire harness frame 310, the second sucker array 6 can also be adjusted to be positioned in an adjusting groove 311 through a H-shaped sliding block 4 so as to adapt to the height fluctuation curved surface of the aircraft tail wing, when in use, a driving motor 302 drives a turnover shaft 307 to rotate through a shaft 303, a limiting plate 304 coaxially fixed at the root of the shaft 303 is matched with limiting plates 304 at two ends of the stroke to realize control of the turnover stroke of the turnover shaft 307, so that the turnover adjustment of the processing surfaces on two sides of the aircraft tail wing can be realized without repeated clamping, on one hand, positioning errors caused by repeated clamping can be reduced, on the other hand, the machine processing efficiency of the airplane tail fin is improved, the production time is shortened because the downtime caused by repeated clamping is saved, in the use process, the X-axis sliding block 9 realizes the displacement adjustment in the X-axis direction through the movement in the extending direction of the electric transverse rail 8, the Y-axis sliding block 11 realizes the displacement adjustment in the Y-axis direction through the movement in the extending direction of the electric longitudinal rail 10, the Z-axis sliding block 13 realizes the displacement adjustment in the Z-axis direction through the movement in the extending direction of the electric vertical rail 12, the travel of the machine tool is increased by increasing the relative movement distance which can be completed by the five-axis machine tool, so that the five-axis machine tool can adapt to the processing requirements of long-axis workpieces and large-area workpieces, in addition, the workbench 1 does not have the traditional A axis capable of rotating around the X axis on the machine body due to the overturning processing requirements of the airplane tail fin, and the C shaft of the traditional rotary table, therefore, in the application, the full-scale machining requirement of a workpiece is met through the output angle adjusting component 14, when the rotary table is used, the motor I1404 rotates and drives the input shaft 1402 to rotate and drive the output shaft 1407 through the turning gear set 1403, the further input shaft 1402 rotates and drives the angle adjusting slide block 1413 to slide at the flat end of the lower plate 1410 through the electric cylinder 1412, the output shaft 1407 can be subjected to pitching adjustment through the spline shaft 1406 arranged in the middle of the double-cross universal joint 1405 in a sliding manner, and the motor II 1408 swings the lower plate 1410 through the rocker 1409, so that the yaw adjustment can be performed on the output shaft 1407 left and right, therefore, the rotary table is not limited to the rotary output shaft 1407 with single degree of freedom, but the machining angle of the output shaft 1407 is flexible and adjustable, has higher degree of freedom and parallelism, and can adapt to the characteristic shape curved surface machining requirement when an airplane tail wing is machined.
The embodiments of the application have been presented for purposes of illustration and description, and are not intended to be exhaustive or limited to the application in the form disclosed. Many modifications and variations will be apparent to those of ordinary skill in the art. The embodiments were chosen and described in order to best explain the principles of the application and the practical application, and to enable others of ordinary skill in the art to understand the application for various embodiments with various modifications as are suited to the particular use contemplated.
Claims (10)
1. The utility model provides a large-stroke aircraft fin machine tool, its characterized in that includes workstation (1) and upset subassembly (3), dodge chamber (2) has been seted up at workstation (1) middle part, upset subassembly (3) fixed mounting is in workstation (1) right-hand member, upset subassembly (3) include motor mounting panel (301), driving motor (302), axostylus axostyle (303), limiting plate (304), spacer pin (305), shaft coupling (306), tilting shaft (307), sucking disc array one (308), vacuum generator (309), wire frame (310) and adjustment tank (311), driving motor (302) right-hand member fixed mounting has driving motor (302), and driving motor (302) left side output fixedly connected with axostylus axostyle (303), axostyle (303) root coaxial fixed with limiting plate (304), and limiting plate (304) stroke both ends correspond and are equipped with spacer pin (305) to dodge chamber (2) open end, axostylus axostyle (303) end fixedly connected with shaft coupling (306), and axostylus axostyle (303) have coaxial sucking disc array (307) on the coaxial shaft (307) through transmission coupling (307), and a vacuum generator (309) is fixedly arranged on the lower plane of the turnover shaft (307), a wire harness frame (310) is integrally fixed on the side face of the turnover shaft (307), and an adjusting groove (311) is formed in the tail end of the wire harness frame (310) along the extending direction of the wire harness frame.
2. The large-stroke aircraft tail wing machining tool according to claim 1, wherein the adjusting groove (311) is internally provided with an I-shaped sliding block (4) in a sliding manner, the middle part of the I-shaped sliding block (4) is provided with a threaded hole (5), the middle part of the threaded hole (5) is in threaded connection with a sucker array II (6), and the sucker array II (6) and a sucker array I (308) are communicated with a vacuum generator (309) through a pipeline.
3. The large-stroke aircraft tail processing machine tool according to claim 1, wherein a boss (7) is integrally fixed at the rear end of the workbench (1), and an electric transverse rail (8) is fixedly arranged at the top end of the boss (7).
4. A long-stroke aircraft tail processing machine according to claim 3, characterized in that the top of the electric transverse rail (8) is slidably provided with an X-axis slide block (9) along the extending direction thereof, and the top of the X-axis slide block (9) is fixedly provided with an electric longitudinal rail (10).
5. The large-stroke aircraft tail processing machine tool as claimed in claim 4 wherein a Y-axis sliding block (11) is slidably mounted in the middle of the electric longitudinal rail (10) along the extending direction of the electric longitudinal rail, an electric vertical rail (12) is fixedly mounted in the middle of the Y-axis sliding block (11), and a Z-axis sliding block (13) is slidably mounted in the front of the electric vertical rail (12) along the extending direction of the electric vertical rail.
6. The large-stroke aircraft tail processing machine tool according to claim 5, wherein an output angle adjusting assembly (14) is arranged inside the bottom end of the Z-axis sliding block (13), the output angle adjusting assembly (14) comprises an upper plate (1401), an input shaft (1402), a turning gear set (1403) and a motor I (1404), the input shaft (1402) is rotatably arranged in the middle of the straight end of the upper plate (1401), the turning gear set (1403) is coaxially connected to the top of the input shaft (1402), and the motor I (1404) is coaxially connected to the side surface of the turning gear set (1403).
7. The high travel aircraft tail processing machine of claim 6, wherein the output angle adjustment assembly (14) further includes a double cross universal joint (1405), a spline shaft (1406) and an output shaft (1407), the bottom of the input shaft (1402) is drivingly connected with the double cross universal joint (1405), the spline shaft (1406) is slidably mounted in the middle of the double cross universal joint (1405), and the bottom of the double cross universal joint (1405) is drivingly connected with the output shaft (1407).
8. The large-stroke aircraft tail processing machine as claimed in claim 6 wherein said output angle adjusting assembly (14) further comprises a second motor (1408) and a rocker (1409), said second motor (1408) is fixedly mounted on the left side of the vertical end of said upper plate (1401), and the output end of said second motor (1408) is fixedly connected with said rocker (1409).
9. The high-travel aircraft tail processing machine of claim 8, wherein the output angle adjustment assembly (14) further comprises a lower plate (1410) and a synchronizing gear set (1411), the output end of the rocker (1409) is fixedly connected with the lower plate (1410), and the output end of the rocker (1409) is coaxially connected with the synchronizing gear set (1411).
10. The large-stroke aircraft tail processing machine as claimed in claim 9 wherein said output angle adjusting assembly (14) further comprises an electric cylinder (1412) and an angle adjusting slide block (1413), said lower plate (1410) is fixedly mounted with the electric cylinder (1412) on the left side of the vertical end, and the output end of the electric cylinder (1412) is fixedly connected with the angle adjusting slide block (1413), said angle adjusting slide block (1413) is slidably mounted inside the flat end of the lower plate (1410), and the output shaft (1407) is rotatably mounted inside the angle adjusting slide block (1413).
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| CN202311140845.6A CN117047523A (en) | 2023-09-06 | 2023-09-06 | Large-stroke aircraft tail wing processing machine tool |
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| CN202311140845.6A CN117047523A (en) | 2023-09-06 | 2023-09-06 | Large-stroke aircraft tail wing processing machine tool |
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| CN202311140845.6A Pending CN117047523A (en) | 2023-09-06 | 2023-09-06 | Large-stroke aircraft tail wing processing machine tool |
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