Fixing device for internal parts of aviation equipment, aviation equipment and method

Abstract

The invention discloses an aviation equipment internal part fixing device, aviation equipment and a method, the aviation equipment internal part fixing device comprises a first long shaft, the interior of the first long shaft is of a hollow structure, and a through hole is formed in the first long shaft; the second long shaft is mounted in the first long shaft in a pluggable manner; the positioning piece is mounted in the through hole and is used for positioning the second long shaft; wherein when the part is fixed in the deep hole in the shell, the part is installed at the end of the first long shaft, the second long shaft is knocked to enable the part to be installed in the deep hole in the shell, and the distance between the top of the end, close to the first long shaft, of the part and the end face of the deep hole ranges from 1.3 mm to 1.5 mm. A part can be accurately and smoothly placed in a deep hole in an aviation equipment shell through guiding of the first long shaft, the second long shaft is knocked, the part is separated from the first long shaft, meanwhile, the distance between the end face of the part and the end face of the deep hole meets the installation requirement, the installation precision is improved, and the problems that labor intensity is large, and cost is low are solved. The installation period is long; and the cost is high.

Description

Technical Field

[0001] The invention belongs to the technical field of aviation equipment assembly, and in particular relates to an aviation equipment internal parts fixing device, aviation equipment and a method. Background Art

[0002] During the assembly process of aviation equipment, due to the particularity of aviation equipment, its internal parts are numerous, small in size, and difficult to install. During daily assembly operations, since the opening space for installing parts in the aviation equipment shell is small, the installer's arms cannot reach deep into it to install the parts in the deep holes inside the aviation equipment shell; therefore, during the installation process, the installer generally uses slender tweezers or other similar clamping tools to replace the arms to enter and install the parts.

[0003] However, during the installation process, due to the influence of the length of the tweezers and the structure of the clamping end of the tweezers, the clamping force of the tweezers is reduced when the part is pressed down and inserted into the deep hole for fixation, causing friction between the part and the inner wall of the tweezers, resulting in the separation of the tweezers clamping end from the part and collision and damage with the shell. At this time, new tweezers need to be replaced and reinstalled. The installation process is labor-intensive, and the installation cycle is long and the cost is high. Summary of the invention

[0004] The purpose of the present invention is to provide an aviation equipment internal parts fixing device, aviation equipment and method, so as to solve the technical defects in the prior art of using clamping tools such as tweezers to install aviation equipment parts, which have high labor intensity, long installation period and high cost.

[0005] To achieve the above object, the present invention adopts the following scheme: In a first aspect, a device for fixing internal parts of aviation equipment is provided, comprising: A first long axis, the interior of which is a hollow structure, and a through hole is opened on the first long axis; A second long shaft, pluggably installed in the first long shaft; A positioning member, installed in the through hole, for positioning the second long axis; When fixing the part in the deep hole inside the shell, the part is installed at the end of the first long axis, and the second long axis is knocked to install the part in the deep hole inside the shell, and the distance between the top of one end of the part close to the first long axis and the end face of the deep hole is 1.3mm~1.5mm.

[0006] Further, the positioning member is a top screw; or the positioning member is a screw.

[0007] Furthermore, there is a gap between the first long axis inner wall and the second long axis outer wall.

[0008] In a second aspect, an aviation device is provided, comprising a shell, wherein a deep hole is opened in the shell, and a part is installed in the deep hole. The part is installed using the fixing device as described above.

[0009] In a third aspect, a method for processing an internal part fixture of aviation equipment is provided, comprising: Selecting a long shaft, and performing turning processing on the long shaft; The long shaft after turning is quenched, and the hardness of the long shaft after quenching is HRC33-38; The two end faces of the quenched long shaft are turned flat, and the center holes and grinding holes are machined on the two end faces of the long shaft; Taking the top hole after grinding the long shaft as the reference, clamp one end of the long shaft, use the male top to support the top hole at the other end, and grind the outer circle; Taking the outer circle as a reference, fix the long axis on the coordinate boring table, and drill a hole at the right end of the long axis; Taking the opening as a reference, using a grinding core rod to make the opening coaxial with the outer circle; Taking the ground outer circle as the reference, a small top hole is opened at the left end of the long shaft.

[0010] Furthermore, the material of the long shaft is alloy carburized steel.

[0011] Further, the long shaft is subjected to turning processing, specifically comprising: All outer circles of the long shaft are machined according to the through circle, and the left end of the long shaft is lengthened by 5~7mm.

[0012] Further, taking the top hole after grinding the long shaft as a reference, clamp one end of the long shaft, use a positive top to support the top hole at the other end, and grind the outer circle, specifically including: Taking the top hole after grinding the long shaft as the reference, clamp the outer circle of one end of the long shaft with a clamp, support the top hole with a positive center at the other end of the long shaft, and use a corundum grinding wheel to grind the outer circle of the long shaft to make the outer circle coaxial with the top hole.

[0013] Further, the outer circle is used as a reference, the long axis is fixed on a coordinate boring table, and a hole is drilled at the right end of the long axis, specifically including: Taking the outer circle of the long axis as a reference, the long axis is fixed on a coordinate boring table, and the coordinate boring table is rotated 90 degrees so that the long axis is in the same direction as the coordinate boring spindle; The long axis was drilled using a cobalt-containing drill bit with a hole depth of 148 mm.

[0014] Furthermore, it also includes: Use the grinding core rod to support the small top hole on the left end of the long shaft, and use the white corundum grinding wheel to feed the tool longitudinally; Fix the long axis on the coordinate boring table and use a boring tool to process the right end of the long axis; Use CNC lathe to cut off the extended part at the left end of the long shaft and align the outer circle.

[0015] Compared with the prior art, the present invention has the following beneficial effects: 1. By installing the part at the end of the first long axis, the part can be accurately and smoothly placed in the deep hole in the shell of the aviation equipment by using the guidance of the first long axis. Secondly, the second long axis is installed inside the first long axis, and then the second long axis is knocked so that the part is separated from the first long axis while the distance between the end face of the part and the end face of the deep hole meets the installation requirements. This not only improves the installation accuracy, but also improves the installation efficiency, and solves the technical defects of high labor intensity, long installation cycle and high cost caused by the current installation using tweezers.

[0016] 2. Using a top screw or a screw as a positioning piece can ensure that the second long axis will not be offset during the process of striking the second long axis to displace it, thereby improving the reliability of the parts installation operation.

[0017] 3. The existence of the gap reduces the direct contact between the first long axis and the second long axis during relative motion, thereby reducing friction and wear, helping to extend the service life of the device and reducing heat and noise generated by friction.

[0018] 4. When assembling parts of aviation equipment, the use of this fixture can greatly simplify the installation and disassembly process of the parts. Through simple plugging and tapping actions, the parts can be accurately installed; similarly, the disassembly process is also relatively simple and quick, which reduces maintenance costs and improves work efficiency. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings required for use in the embodiments are briefly introduced below. It should be understood that the following drawings only show certain embodiments of the present invention and therefore should not be regarded as limiting the scope. For ordinary technicians in this field, other related drawings can be obtained based on these drawings without creative work.

[0020] Figure 1 A schematic diagram of the operation of the internal parts fixing device for aviation equipment provided by the present invention; Figure 2 A schematic diagram of the first long axis structure in the method for processing the internal parts fixing device of aviation equipment provided by the present invention; Figure 3 A schematic diagram of a top hole formed on the first long axis in the method for processing the internal parts fixing device of aviation equipment provided by the present invention; Figure 4A schematic diagram of the outer cylindrical grinding of the first long axis in the method for machining the internal parts fixture of aviation equipment provided by the present invention; Figure 5 A schematic diagram of opening a hole at the right end of the first long axis in the method for processing the internal parts fixing device of aviation equipment provided by the present invention; Figure 6 A three-dimensional diagram of a hole opened at the right end of the first long axis in the method for processing the internal parts fixing device of aviation equipment provided by the present invention; Figure 7 This is a schematic diagram of a hole being opened at the right end of the first long axis in the method for processing the internal parts fixing device of aviation equipment provided by the present invention; Figure 8 A schematic diagram of a drill bit in a method for processing a fixing device for internal parts of aviation equipment provided by the present invention; Fig. 9 A schematic diagram of the coaxiality of the opening and the outer circle in the method for processing the internal parts fixing device of aviation equipment provided by the present invention; Fig.10 A schematic diagram of the outer circle turning in the method for machining the internal parts fixing device of aviation equipment provided by the present invention; Fig.11 A schematic diagram of grinding an outer circle in a method for machining a fixing device for internal parts of aviation equipment provided by the present invention; Fig.12 A schematic diagram of coordinate boring processing in the processing method of the internal parts fixing device of aviation equipment provided by the present invention; Fig.13 A schematic diagram of fine grinding of an outer circle in a method for machining a fixture for internal parts of aviation equipment provided by the present invention; Fig.14 A schematic diagram of a long-axis CNC lathe processing method for a fixing device for internal parts of aviation equipment provided by the present invention; Fig.15 A first schematic diagram of the long-axis small hole opening in the method for processing the internal parts fixing device of aviation equipment provided by the present invention; Fig.16 A second schematic diagram of the long-axis small hole in the method for processing the internal parts fixing device of aviation equipment provided by the present invention; Fig.17 A schematic diagram of a first long axis product in the method for processing the internal parts fixture of aviation equipment provided by the present invention; Fig.18 A flow chart of a method for processing a fixing device for internal parts of aviation equipment provided by the present invention; Among them: 1. first long axis; 101, through hole; 2. second long axis; 3. shell; 4. parts; 5. clamp; 6. yang center; 7. workbench; 8. V-block; 9. drill bit; 10. core rod. DETAILED DESCRIPTION

[0021] In order to make the purpose, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are part of the embodiments of the present invention, not all of the embodiments. Generally, the components of the embodiments of the present invention described and shown in the drawings here can be arranged and designed in various different configurations.

[0022] Therefore, the following detailed description of the embodiments of the present invention provided in the accompanying drawings is not intended to limit the scope of the invention claimed for protection, but merely represents selected embodiments of the present invention. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0023] It should be noted that similar reference numerals and letters denote similar items in the following drawings, and therefore, once an item is defined in one drawing, further definition and explanation thereof is not required in subsequent drawings.

[0024] In the description of the embodiments of the present invention, it should be noted that if the terms "upper", "lower", "horizontal", "inner", etc. indicate an orientation or positional relationship based on the orientation or positional relationship shown in the drawings, or the orientation or positional relationship in which the product of the invention is usually placed when in use, it is only for the convenience of describing the present invention and simplifying the description, and does not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on the present invention. In addition, the terms "first", "second", etc. are only used to distinguish the description, and cannot be understood as indicating or implying relative importance.

[0025] In addition, if the term "horizontal" appears, it does not mean that the component must be absolutely horizontal, but can be slightly tilted. For example, "horizontal" only means that its direction is more horizontal than "vertical", which does not mean that the structure must be completely horizontal, but can be slightly tilted.

[0026] During the assembly process of aviation equipment, due to the particularity of aviation equipment, its internal parts are numerous, small in size, and difficult to install. During daily assembly operations, since the opening space for installing parts in the aviation equipment shell is small, the installer's arms cannot reach deep into it to install the parts in the deep holes inside the aviation equipment shell; therefore, during the installation process, the installer generally uses slender tweezers or other similar clamping tools to replace the arms to enter and install the parts.

[0027] However, during the installation process, due to the influence of the length of the tweezers and the structure of the clamping end of the tweezers, the clamping force of the tweezers is reduced when the part is pressed down and inserted into the deep hole for fixation, causing friction between the part and the inner wall of the tweezers, resulting in the separation of the tweezers clamping end from the part and collision and damage with the shell. At this time, new tweezers need to be replaced and reinstalled. The installation process is labor-intensive, and the installation cycle is long and the cost is high.

[0028] In order to solve the above technical defects, the inventor provides an internal parts fixing device of aviation equipment, aviation equipment and method.

[0029] The present invention will be described in further detail below by taking the installation of internal parts of an aviation equipment housing as an example with reference to the accompanying drawings.

[0030] like Figure 1 As shown, in the first aspect of an embodiment of the present invention, a device for fixing internal parts of aviation equipment is provided, the fixing device comprising a first long axis 1, the interior of which is a hollow structure, a through hole 101 is opened on the first long axis 1, and the second long axis 2 is plugged and installed in the first long axis 1; a positioning member is installed in the through hole 101, and is used to position the second long axis 2; wherein, when fixing the part 4 to the deep hole inside the shell 3, the part 4 is first installed at the end of the first long axis 1, and the part 4 is transported to the inside of the shell 3 through the first long axis 1, and then, the second long axis 2 is knocked so that the part 4 is installed in the deep hole inside the shell 3, and the distance between the top of one end of the part 3 close to the first long axis 1 and the end face of the deep hole is 1.3mm~1.5mm. During the installation of part 4, by installing part 4 at the end of the first long axis 1, the first long axis 1 is used to guide part 4 to be accurately and smoothly placed in the deep hole in the aviation equipment housing 3. Then, the second long axis 2 is installed inside the first long axis 1, and then the second long axis 2 is knocked so that part 4 is separated from the first long axis 1 while the distance between the end face of part 4 and the end face of the deep hole meets the installation requirements. This not only improves the installation accuracy, but also improves the installation efficiency, and solves the technical defects of high labor intensity, long installation cycle and high cost caused by the current installation with tweezers. Figure 1 As shown, in this solution, in one embodiment, the positioning member is preferably a top screw; in another embodiment, the positioning member is a screw; in the positioning process, by using a top screw or a screw as a positioning member, it can be ensured that the second long axis 2 will not be offset during the process of knocking the second long axis 2 to make it move, thereby improving the reliability of the parts installation operation. At the same time, there is a gap between the inner wall of the first long axis 1 and the outer wall of the second long axis 2. The existence of the gap reduces the direct contact between the first long axis 1 and the second long axis 2 during relative movement, thereby reducing friction and wear, helping to extend the service life of the device, and reducing the heat and noise generated by friction.

[0031] According to a second aspect of an embodiment of the present invention, an aviation equipment is provided, which includes a shell having a deep hole formed therein, in which a part 4 is installed. The part 4 is installed using the fixing device as described above. When assembling the part 4 of the aviation equipment, the fixing device can be used to greatly simplify the installation and disassembly process of the part 4, and the part 4 can be accurately installed by simple plugging and tapping actions. Similarly, the disassembly process is also relatively simple and quick, which reduces maintenance costs and improves work efficiency.

[0032] In a third aspect of the present invention, a method for processing a fixture for internal parts of aviation equipment is provided. Figure 2-Figure 18 As shown, including: S101. Select a long axis and perform turning on the long axis. For example, select a long axis made of 12CrNi3, an alloy carburizing steel, and process all the outer circles of the long axis as through circles. The processing size is 16mm in diameter according to the designed outer circle size, and the single side is enlarged by 5mm (or more than 5mm) to leave enough margin for subsequent processing. In the process of increasing the wall thickness, even if there is a deviation in the subsequent hole processing, the outer circle can be turned by hole positioning. At this time, the hole wall is thicker and the hole will not penetrate the outer circle due to the thin wall. At the same time, since the length of the top hole is 2.5mm, in order to avoid burrs on the hole mouth with a diameter of 1.63mm at the left end of the long axis, the left end of the long axis is lengthened by 5~7mm during turning. Figure 2 shown.

[0033] S102, quenching the long shaft after turning, and making the hardness of the long shaft after quenching HRC33-38; illustratively, quenching the long shaft after turning, making the hardness of the long shaft HRC33-38, to ensure that the long shaft will not break during subsequent processing.

[0034] S103, flattening the two end faces of the quenched long shaft, and machining and grinding the top holes on the two end faces of the long shaft; illustratively, Figure 4 As shown, the two end surfaces of the quenched long shaft are flattened by a lathe, and then the center holes are machined and ground on the two end surfaces of the long shaft.

[0035] S104, using the top hole after grinding the long shaft as a reference, clamp one end of the long shaft, use the male top to support the top hole at the other end, and grind the outer circle; illustratively, as Figure 4 As shown, taking the top hole of the long shaft after grinding in the above steps as the reference, one end of the long shaft is clamped with the outer circle by the clamp 5, the other end of the long shaft is supported against the top hole by the positive center 6, and the outer circle of the long shaft is ground with a white corundum grinding wheel, so that the outer circle diameter of the long shaft is 25.8mm, so that the outer circle and the top hole are coaxial by 0.01mm.

[0036] S105, fixing the long axis on a coordinate boring table with the outer circle as a reference, and drilling a hole at the right end of the long axis; illustratively, Figure 5-Figure 8 As shown, with the outer circle of the above steps as the reference, the long axis (first long axis 1) is fixed on the V-block 8, and then the long axis and the V-block 8 are fixed on the coordinate boring table 7, and the coordinate boring table 7 is rotated ninety degrees to make the axial direction of the long axis consistent with the coordinate boring spindle direction; it is worth noting that the cobalt-containing drill bit 9 is used to drill a φ4.1mm hole and 60°, the depth is processed according to 148mm, and the coaxial 0.02mm, the cobalt-containing drill bit 9 is φ4.1mm×210mm. By using the cobalt-containing drill bit 9, the cutting force is more stable, and higher processing accuracy and processing efficiency can be obtained. When processing a φ4.1mm hole, each feed is about 4mm-5mm. As the depth of the processed hole increases, each feed is reduced to about 2mm, and the iron chips are taken out with the drill bit 9 (when the depth is close to 148mm, if the iron chips are really difficult to discharge, the coordinate boring machine disc can be rotated 180°, and the hole mouth can be downward to discharge the iron chips).

[0037] S106. Using the opening as a reference, use a grinding core rod to make the opening coaxial with the outer circle; illustratively, using the φ4.1mm hole in the above step as a reference, use a grinding core rod to grind the outer circle against the top hole of the core rod, grind the right end of the long axis by 60mm to enlarge the outer circle, and ensure that the hole is coaxial with the outer circle by 0.01mm.

[0038] S107, using the outer circle after grinding as a reference, opening a small top hole at the left end of the long shaft; illustratively, as Fig.10 As shown, take the outer circle ground in the above steps as the reference, clamp the outer circle on the right end, turn the left end 2.5mm to lengthen (make sure there is no original top hole), and then make a φ1 small top hole. Use the tool holder to semi-finish the outer circle of Φ7 and Φ16 on the lathe, leave 0.2mm on one side, and grind 0.1mm on the outer circle of Φ7 and Φ16 to ensure coaxial 0.01mm longitudinal feed, each time the longitudinal feed is 0.1mm~0.15mm, grind 0.1mm on the outer circle of Φ7 and Φ16 to ensure coaxial 0.01mm, as shown. Fig.11 shown.

[0039] like Fig.12 As shown, the long axis is fixed on the coordinate boring table 7, and the right end of the long axis is processed by a boring tool; the processed outer circle is used as the process reference, the part is fixed on the V-block by the coordinate boring, the machine tool disc is rotated 90°, and the φ6 hole on the right end is processed by a boring tool to ensure that the hole is coaxial with the outer circle by 0.02mm; Figure 3 As shown, the outer circle is ground, the right end of the φ6mm hole is equipped with a core rod 10, and the outer circle of Φ7 and Φ16 is finely ground with a white corundum grinding wheel to meet the tolerance of the figure, ensuring the coaxiality of 0.01mm. Fig.14 As shown, the extended part of the left end of the long shaft is cut off by CNC lathe, and the outer circle is aligned with the dial indicator. The outer circle is aligned after lathe is 15°±30′ to the drawing. Fig.15 As shown, take the outer circle after grinding as the process reference, fix the long axis on the V-block 8, rotate the workbench 7 by 90°, select the φ1.35mm drill bit 9 reamer to make the φ1.63mm hole at the left end according to φ1.35mm, and make it coaxial with the outer circle by 0.01mm, as shown in the figure. Figure 16-Figure 17 As shown, the coordinate grinder is positioned with a φ6mm hole (the φ6mm hole is equipped with a CrWMn material core rod 10 for clamping), and a φ1.2mm diamond grinding wheel is used to grind a φ1.63mm hole to achieve the hole diameter tolerance, with a run-out of 0.02mm. Finally, a dial indicator is used to align the outer circle, and an end mill is used to mill R7.5mm and 15°, with a tolerance of 4.35mm to achieve the tolerance. A drill is used to drill an M4 bottom hole, and then an M4 tap is used to tap the thread, and an M4 threaded hole is machined to remove burrs. Through the above steps, the processing of the first long axis 1 is completed. In the process of machining the first long shaft 1, the long blind hole and thin-walled features of the slender shaft are fully considered during rough machining, the outer circle allowance is increased, the wall thickness is increased, and the small hole end is lengthened, which effectively avoids the problems of the long blind hole being inclined through the outer circle and the top hole burr of the small hole mouth during the subsequent fine machining, thereby improving the machining qualification rate of the part; secondly, the coordinate boring machine is used to select the cobalt-containing drill 9 to machine the long blind hole, which not only ensures the precision requirements of the long blind hole, but also ensures the machining quality of the long blind hole, thereby improving the machining efficiency; then, the coordinate grinding is used to grind the small hole, which effectively ensures the geometric tolerance accuracy requirements of the small hole and the right end hole; the machining method provided by the present invention effectively improves the machining efficiency of such thin-walled slender shaft parts with blind holes, and at the same time increases the qualification rate from the original 5% to the current 95%. At the same time, it can be widely used in the machining of various slender thin-walled shaft parts with blind holes.

[0040] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention rather than to limit its protection scope. Although the present invention has been described in detail with reference to the above embodiments, ordinary technicians in the field should understand that after reading the present invention, those skilled in the art can still make various changes, modifications or equivalent substitutions to the specific implementation methods of the invention, but these changes, modifications or equivalent substitutions are all within the protection scope of the pending claims of the invention.

Claims

1. A device for fixing internal parts of aviation equipment, characterized in that: include: A first long shaft (1) having a hollow structure inside, and a through hole (101) is provided on the first long shaft (1); A second long shaft (2) pluggably installed in the first long shaft (1); A positioning member, installed in the through hole (101) and used for positioning the second long axis (2); When fixing the part (4) to the inner deep hole of the shell (3), the part (4) is installed at the end of the first long axis (1), and the second long axis (2) is struck so that the part (4) is installed in the inner deep hole of the shell (3), and the distance between the top of one end of the part (3) close to the first long axis (1) and the end face of the deep hole is 1.3 mm to 1.5 mm.

2. The fixing device according to claim 1, characterized in that: The positioning member is a top screw; or the positioning member is a screw.

3. The fixing device according to claim 1, characterized in that: There is a gap between the inner wall of the first long axis (1) and the outer wall of the second long axis (2).

4. An aviation device, comprising a housing, a deep hole is provided in the housing, and a part is installed in the deep hole, wherein: The parts are installed using the fixing device described in any one of claims 1-3.

5. A method for processing a fixture for internal parts of aviation equipment, characterized in that: include: Selecting a long shaft, and performing turning processing on the long shaft; The long shaft after turning is quenched, and the hardness of the long shaft after quenching is HRC33-38; The two end faces of the quenched long shaft are turned flat, and the center holes and grinding holes are machined on the two end faces of the long shaft; Taking the top hole after grinding the long shaft as the reference, clamp one end of the long shaft, use the male top to support the top hole at the other end, and grind the outer circle; Taking the outer circle as a reference, fix the long axis on the coordinate boring table, and drill a hole at the right end of the long axis; Taking the opening as a reference, using a grinding core rod to make the opening coaxial with the outer circle; Taking the ground outer circle as the reference, a small top hole is opened at the left end of the long shaft.

6. The processing method according to claim 4, characterized in that: The material of the long shaft is alloy carburizing steel.

7. The processing method according to claim 4, characterized in that: The long shaft is subjected to turning processing, specifically comprising: All outer circles of the long shaft are machined according to the through circle, and the left end of the long shaft is lengthened by 5~7mm.

8. The processing method according to claim 4, characterized in that: Taking the top hole after grinding the long shaft as the reference, clamp one end of the long shaft, use the male top to support the top hole at the other end, and grind the outer circle, specifically including: Taking the top hole after grinding the long shaft as the reference, clamp the outer circle of one end of the long shaft with a clamp, support the top hole with a positive center at the other end of the long shaft, and use a corundum grinding wheel to grind the outer circle of the long shaft to make the outer circle coaxial with the top hole.

9. The processing method according to claim 4, characterized in that: Taking the outer circle as a reference, the long axis is fixed on a coordinate boring table, and a hole is drilled at the right end of the long axis, specifically including: Taking the outer circle of the long axis as a reference, the long axis is fixed on a coordinate boring table, and the coordinate boring table is rotated 90 degrees so that the long axis is in the same direction as the coordinate boring spindle; The long axis was drilled using a cobalt-containing drill bit with a hole depth of 148 mm.

10. The processing method according to claim 4, characterized in that: Also includes: Use the grinding core rod to support the small top hole on the left end of the long shaft, and use the white corundum grinding wheel to feed the tool longitudinally; Fix the long axis on the coordinate boring table and use a boring tool to process the right end of the long axis; Use CNC lathe to cut off the extended part at the left end of the long shaft and align the outer circle.

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