A method for machining cast aluminum blank parts for aerospace

Abstract

The application discloses a machining method for cast aluminum blank parts for aviation, and belongs to the technical field of machining clamp devices; it comprises the following steps: S1, first clamping; installing a part to be machined on a clamp one, and then installing the clamp one and the part to be machined on a rotating indexing head of a numerical control milling machine; S2, completing machining of an outer side end plane around the part to be machined; S3, second clamping; taking down the part to be machined from the clamp one, cleaning, then installing the part to be machined on a clamp two, and then installing the clamp two and the part to be machined on the rotating indexing head of the numerical control milling machine; S4, completing machining of remaining end faces, holes and inner cavities of the part to be machined; and S5, taking down the formed part after completing machining and cleaning; the application effectively solves the problems of large accumulated error, low good product rate of parts, high machining cost and low production efficiency caused by the current need of clamping and machining on multiple machine tools for multiple times.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of machining fixture device, in particular to a machining method for cast aluminum blank parts used in aviation. BACKGROUND

[0002] Figure 1 is a schematic diagram of a cast aluminum part blank used in aviation; Figures 2 to 4 is a schematic diagram of the finished part, wherein the holes on the a end face, b end face, c end face, d end face, e end face, f face and g inner cavity window all have machining precision requirements, under conventional machining means, multiple different fixtures need to be used on multiple machine tools for machining, obviously, such machining means has the problems of large accumulated error of multiple clamping, multiple equipment and personnel occupation, and further easily leads to the problems of unguaranteed machining size and position precision of the product, and low production efficiency. SUMMARY

[0003] The technical problem to be solved by the present application is to provide a machining method for cast aluminum blank parts used in aviation, so as to solve the problems of large accumulated error of multiple clamping machining, low good product rate of parts, high machining cost and low production efficiency.

[0004] To solve the above problems, the present application provides the following technical scheme:

[0005] A machining method for cast aluminum blank parts used in aviation;It comprises the following steps:

[0006] S1, first clamping;The part to be machined is installed on fixture one, and then the fixture one and the part to be machined are installed on the rotary indexing head of the numerical control milling machine together;

[0007] The fixture one includes a main shaft one in the form of a stepped shaft;The small diameter end of the main shaft one is detachably installed on the rotary indexing head of the numerical control milling machine;A base and a movable support are installed on the other end side plane of the main shaft one;The shape specification of the outer circumferential side of the base is consistent with the shape specification of the inner cavity circumferential side of the part to be machined;The part to be machined is set in reverse on the base;A pressing plate is installed on the movable support;The pressing plate is pressed on the upper top end face of the part to be machined;

[0008] S2, complete the machining of the four peripheral end faces of the part to be machined;First, the a face on the part to be machined is milled;After the a face is machined, the fixture one is rotated by 90° by the rotary indexing head to realize the machining of the b face;After that, the fixture one is rotated by 90° by the rotary indexing head every time a side end face is machined, and the a face, b face, c face and d face are gradually machined;

[0009] S3, second clamping; the part to be processed is taken off from the fixture one, cleaned, and then installed on the fixture two, and then the fixture two and the part to be processed are installed on the rotary indexing head of the numerical control milling machine;

[0010] The fixture two comprises a main shaft two in the shape of a stepped shaft; the small-diameter end of the main shaft two is detachably installed on the rotary indexing head of the numerical control milling machine; a left vertical plate and a right vertical plate are installed on the other end side plane of the main shaft two; a side pressing plate is installed on the left vertical plate; the part to be processed is clamped between the two end planes opposite to each other of the side pressing plate and the right vertical plate, and the processed d surface of the part to be processed is attached to the side pressing plate, and the c surface is attached to the right vertical plate; a pair of positioning pins are arranged on the right vertical plate; the positioning pins are detachably inserted into the two round holes arranged on the c surface of the part to be processed;

[0011] S4, the processing of the remaining end surface, hole and inner cavity of the part to be processed is completed; the e surface and the g inner cavity window of the part to be processed are first milled; then the fixture two is rotated by 90° through the rotary indexing head to realize the processing of the f surface;

[0012] S5, the finished part is taken off and cleaned.

[0013] Preferably, a backing plate is further installed on the upper top of the base; the shape and specification of the backing plate are consistent with those of the inner cavity bottom groove of the part to be processed; and a round hole is further opened on the backing plate at a position opposite to the circular table structure of the inner cavity bottom groove of the part to be processed; the diameter of the round hole is larger than the outer diameter of the circular table.

[0014] Preferably, the movable support is arranged opposite to the cylindrical cabin on the part to be processed; the movable support is a vertical column structure, and a through hole is opened on the movable support in the axial direction; a threaded hole is opened on the main shaft one at a position opposite to the through hole; the movable support is detachably installed on the main shaft one through bolts; a cantilever support is further arranged on the top of the movable support; the top pressing plate is arranged below the cantilever support; a guide threaded hole is opened on the cantilever support, and the top pressing plate is pressed on the part to be processed through the bolts arranged at the guide threaded hole.

[0015] Preferably, a guide through slot is opened on the left vertical plate; a sliding block matched with the guide through slot is arranged on the back of the side pressing plate; a guide threaded hole is opened on the groove bottom of the guide through slot, and the side pressing plate is pressed on the side end surface of the part to be processed through the bolts arranged at the guide threaded hole.

[0016] Preferably, the side pressing plate is an L plate structure, and the two end side surfaces of the included angle position of the L plate structure are respectively attached to the d surface and the f surface of the part to be processed; and the side pressing plate does not interfere with the unprocessed round hole on the f surface.

[0017] Preferably, a C-shaped ring is also provided on the right upright plate; the two protruding ends of the C-shaped ring are respectively fastened to the L-shaped platform structure position where the c-side of the part to be processed is located; a threaded hole is opened in the middle of the C-shaped ring, and a locking bolt is used to lock the C-shaped ring to the part to be processed at the threaded hole.

[0018] Furthermore, the distance between the bottom surface of the C-type ring clamp and the end face of the second spindle is consistent with the thickness of the lower side plate of the L plate at the cylindrical compartment position of the part to be processed; and when the part to be processed is clamped between the side pressure plate and the right vertical plate, its b surface is attached to the end face of the second spindle.

[0019] Preferably, both the left and right vertical plates are integrally connected to the main shaft.

[0020] Beneficial effects of this invention:

[0021] This invention addresses the machining requirements of aerospace cavity parts as described in the background section by designing a machining method that utilizes two fixtures in conjunction with a CNC milling machine. By mounting the fixtures on an automatically rotating indexing head, multiple surfaces can be machined in a single clamping operation, and the parts can be machined at multiple rotational angles. This reduces the number of repeated clamping and positioning operations under conventional machining methods from eight to two, effectively overcoming the problems of numerous machining processes, multiple fixtures, and large accumulated errors from multiple clamping operations. It effectively improves the machining dimensions and positional accuracy, while reducing the need for multiple machine tools and personnel, thereby increasing production efficiency and reducing costs. Attached Figure Description

[0022] Figure 1 This is the blank of the part to be processed in this embodiment;

[0023] Figures 2 to 4 These are three-dimensional structural schematic diagrams of the molded parts in this embodiment;

[0024] Figure 5 This is a three-dimensional structural diagram of the part to be processed mounted on fixture one in this embodiment;

[0025] Figure 6 yes Figure 5 A three-dimensional structural diagram of the device from another perspective;

[0026] Figure 7 yes Figure 5 A three-dimensional structural diagram of the device after the parts to be processed are removed;

[0027] Figure 8 yes Figure 7 A three-dimensional structural diagram of the central device after the movable support and top pressure plate have been removed;

[0028] Figure 9This is a three-dimensional structural diagram of the part to be processed mounted on fixture two in this embodiment;

[0029] Figure 10 yes Figure 9 A three-dimensional structural diagram of the device from another perspective;

[0030] Figure 11 yes Figure 9 A three-dimensional structural diagram of the device after the parts to be processed are removed;

[0031] Figure 12 This is a schematic diagram of the C-shaped retaining ring being connected to the locking bolt in this embodiment;

[0032] Explanation of reference numerals in the attached drawings: 1. Part to be processed; 2. Spindle 1; 3. Base; 4. Movable bracket; 5. Top pressure plate; 6. Pad plate; 7. Spindle 2; 8. Left vertical plate; 9. Right vertical plate; 10. Side pressure plate; 11. Positioning pin; 12. Locking bolt; 13. C-ring clamp. Detailed Implementation

[0033] The present invention will be further described below with reference to the accompanying drawings and specific embodiments:

[0034] Example:

[0035] Reference Figure 1 This embodiment provides a method for machining cast aluminum blank parts for aerospace applications, which includes the following steps:

[0036] S1. First clamping: Install the workpiece 1 onto fixture 1, and then install fixture 1 and the workpiece together onto the rotary indexing head of the CNC milling machine.

[0037] The fixture includes a stepped shaft-shaped spindle 2; the small-diameter end of the spindle 2 is detachably mounted on the rotary indexing head of a CNC milling machine; a base 3 and a movable bracket 4 are mounted on the other end side plane of the spindle 2; the shape and specifications of the outer periphery of the base 3 are consistent with the shape and specifications of the inner periphery of the part to be processed 1; the part to be processed 1 is upside down and set on the base 3; a top pressure plate 5 is mounted on the movable bracket 4; the top pressure plate 5 presses against the upper top surface of the part to be processed 1.

[0038] S2. Complete the machining of the outer end planes around the part to be machined; first, mill the a surface on the part to be machined; after the a surface is machined, rotate the indexing head to drive the fixture to rotate 90° to machine the b surface; thereafter, after each side end surface is machined, rotate the indexing head to drive the fixture to rotate 90°, and gradually machine the a surface, b surface, c surface and d surface.

[0039] S3. Second clamping: After removing the workpiece from fixture one and cleaning it, install the workpiece onto fixture two. Then, install fixture two and the workpiece together onto the rotary indexing head of the CNC milling machine.

[0040] The second fixture includes a stepped shaft-shaped spindle 7; the small-diameter end of the spindle 7 is detachably mounted on the rotary indexing head of a CNC milling machine; a left vertical plate 8 and a right vertical plate 9 are mounted on the other end side plane of the spindle 7; a side pressure plate 10 is mounted on the left vertical plate 8; the workpiece 1 to be processed is clamped between the two opposite end planes of the side pressure plate 10 and the right vertical plate 9, and the machined d-surface of the workpiece 1 is in contact with the side pressure plate 10, and the c-surface is in contact with the right vertical plate 9; a pair of locating pins 11 are provided on the right vertical plate 9; the locating pins 11 are detachably inserted into two round holes on the c-surface of the workpiece 1 to be processed.

[0041] S4. Complete the machining of the remaining end faces, holes and cavities on the part to be machined; first, mill the e-face and g-cavity window on the part to be machined; then, rotate the indexing head to drive the second fixture to rotate 90° to achieve the machining of the f-face;

[0042] S5. Remove the finished molded parts and clean them.

[0043] A pad 6 is also installed on the top of the base 1; the shape and specifications of the pad 6 are consistent with the shape and specifications of the groove at the bottom of the inner cavity of the part to be processed 1; and a round hole is also opened on the pad 6 at the position of the frustum structure on the bottom of the inner cavity of the part to be processed 1; the diameter of the round hole is larger than the outer diameter of the frustum.

[0044] The movable support 4 is positioned opposite the cylindrical compartment on the part to be processed 1. The movable support 4 is a column structure with a through hole along its axis. A threaded hole is located on the spindle 2 directly opposite the through hole. The movable support 4 is detachably mounted on the spindle 2 by bolts. A cantilever support rod is also provided on the top of the movable support 4. A top pressure plate 5 is located below the cantilever support rod. A guide threaded hole is provided on the cantilever support rod, and the top pressure plate 5 is pressed onto the part to be processed 1 by bolts located at the guide threaded hole.

[0045] A guide groove is provided on the left upright plate 8; a slider that cooperates with the guide groove is provided on the back of the side pressure plate 10; a guide thread hole is provided at the bottom of the guide groove, and the side pressure plate 10 is pressed against the side end face of the workpiece 1 to be processed by a bolt provided at the guide thread hole.

[0046] The side pressure plate 10 is an L-plate structure, with its two end sides at the included angle attached to the d-surface and f-surface of the part 1 to be processed, respectively; and the side pressure plate 10 does not interfere with the unprocessed circular hole on the f-surface.

[0047] A C-shaped ring is also provided on the right upright plate 9; the two protruding ends of the C-shaped ring are respectively fastened to the L-shaped platform structure position where the c surface of the part to be processed 1 is located; a threaded hole is opened in the middle of the C-shaped ring, and the locking bolt 12 locks the C-shaped ring to the part to be processed 1 at the threaded hole.

[0048] The distance between the bottom surface of the C-type ring clamp and the end face of the second spindle 7 is the same as the thickness of the lower side plate of the L plate at the cylindrical compartment position of the workpiece 1; and when the workpiece 1 is clamped between the side pressure plate 10 and the right vertical plate 9, its b surface is attached to the end face of the second spindle 7.

[0049] Both the left vertical plate 8 and the right vertical plate 9 are integral structures that are fixedly connected to the main shaft 7.

Claims

1. A method for machining cast aluminum blank parts for aerospace applications, characterized in that: It includes the following steps: S1. First clamping: Install the workpiece (1) to be processed onto fixture one, and then install fixture one and the workpiece to be processed together onto the rotary indexing head of the CNC milling machine. The fixture includes a stepped shaft spindle (2); the small-diameter end of the spindle (2) is detachably mounted on the rotary indexing head of the CNC milling machine; a base (3) and a movable bracket (4) are mounted on the other end side plane of the spindle (2); the shape and specifications of the outer periphery of the base (3) are consistent with the shape and specifications of the inner periphery of the part to be processed (1); the part to be processed (1) is upside down on the base (3); a top pressure plate (5) is mounted on the movable bracket (4); the top pressure plate (5) presses on the upper top surface of the part to be processed (1); S2. Complete the machining of the outer end planes around the part to be machined; first, mill the a surface on the part to be machined; after the a surface is machined, rotate the indexing head to drive the fixture to rotate 90° to machine the b surface; thereafter, after each side end surface is machined, rotate the indexing head to drive the fixture to rotate 90°, and gradually machine the a surface, b surface, c surface and d surface. S3. Second clamping: After removing the workpiece from fixture one and cleaning it, install the workpiece onto fixture two. Then, install fixture two and the workpiece together onto the rotary indexing head of the CNC milling machine. The fixture includes a stepped shaft-shaped spindle 2 (7); the small-diameter end of the spindle 2 (7) is detachably mounted on the rotary indexing head of the CNC milling machine; a left vertical plate (8) and a right vertical plate (9) are mounted on the other end side plane of the spindle 2 (7); a side pressure plate (10) is mounted on the left vertical plate (8); the workpiece (1) to be processed is clamped between the two end planes opposite to the side pressure plate (10) and the right vertical plate (9), and the machined d surface of the workpiece (1) is in contact with the side pressure plate (10), and the c surface is in contact with the right vertical plate (9); a pair of locating pins (11) are provided on the right vertical plate (9); the locating pins (11) are detachably inserted into two round holes on the c surface of the workpiece (1); S4. Complete the machining of the remaining end faces, holes and cavities on the part to be machined; first, mill the e-face and g-cavity window on the part to be machined; then, rotate the indexing head to drive the second fixture to rotate 90° to achieve the machining of the f-face; S5. Remove the finished molded parts and clean them.

2. The method for machining cast aluminum blank parts for aerospace applications according to claim 1, characterized in that: A pad (6) is also installed on the top of the base (1); the shape and specifications of the pad (6) are consistent with the shape and specifications of the groove at the bottom of the inner cavity of the part to be processed (1); and a round hole is also opened on the pad (6) at the position of the frustum structure at the bottom of the inner cavity of the part to be processed (1); the diameter of the round hole is larger than the outer diameter of the frustum.

3. The method for machining cast aluminum blank parts for aviation as described in claim 1, characterized in that: The movable bracket (4) is positioned opposite to the cylindrical compartment on the workpiece (1); the movable bracket (4) is a column structure with a through hole in the axial direction of the movable bracket (4); a threaded hole is opened on the main shaft (2) at the position corresponding to the through hole; the movable bracket (4) is detachably installed on the main shaft (2) by bolts; a cantilever support rod is also provided on the top of the movable bracket (4); a top pressure plate (5) is set below the cantilever support rod; a guide threaded hole is opened on the cantilever support rod, and the top pressure plate (5) is pressed onto the workpiece (1) by bolts set at the guide threaded hole.

4. The method for machining cast aluminum blank parts for aviation as described in claim 1, characterized in that: A guide groove is provided on the left upright plate (8); a slider that cooperates with the guide groove is provided on the back of the side pressure plate (10); a guide thread hole is provided at the bottom of the guide groove, and the side pressure plate (10) is pressed on the side end face of the workpiece (1) by a bolt provided at the guide thread hole.

5. A method for machining cast aluminum blank parts for aviation as described in claim 1, characterized in that: The side pressure plate (10) is an L-plate structure, with its two end sides at the included angle attached to the d-plane and f-plane of the part to be processed (1), respectively; and the side pressure plate (10) does not interfere with the unprocessed circular hole on the f-plane.

6. A method for machining cast aluminum blank parts for aviation as described in claim 1, characterized in that: A C-shaped ring clamp (13) is also provided on the right upright plate (9); the two protruding ends of the C-shaped ring clamp (13) are respectively fastened to the L-shaped platform structure position where the c surface of the part to be processed (1) is located; a threaded hole is opened in the middle of the C-shaped ring clamp (13), and the locking bolt (12) locks the C-shaped ring clamp (13) and the part to be processed (1) at the threaded hole.

7. A method for machining cast aluminum blank parts for aerospace applications according to claim 6, characterized in that: The distance between the bottom surface of the C-type ring clamp (13) and the end face of the second spindle (7) is consistent with the thickness of the lower side plate of the L plate at the cylindrical compartment position of the part to be processed (1); and when the part to be processed (1) is sandwiched between the side pressure plate (10) and the right vertical plate (9), its b surface is attached to the end face of the second spindle (7).

8. A method for machining cast aluminum blank parts for aerospace applications according to claim 1, characterized in that: Both the left vertical plate (8) and the right vertical plate (9) are integral structures that are fixedly connected to the main shaft (7).

Images