Machining treatment method for supporting disc structural part of military industry aircraft

Abstract

The invention discloses a machining method for a supporting disc structural part of a military aircraft, which comprises the following specific steps: firstly, selecting a metal raw material, and carrying out hot forging forming by using a forging press; and during rough machining, the blank is clamped on a numerical control lathe for rough turning and then transferred to a five-axis linkage machining center to process a complex structure. And a central structure processing link: processing a screw through hole in the outer ring by using a numerical control drilling machine with a high-precision positioning system, and processing a bearing hole in the inner ring by using a high-precision boring machine. And in the finish machining stage, the workpiece is sequentially subjected to three times of flat grinding and multiple CNC machining, and then the inner ring bearing hole is ground through a high-precision internal grinding machine. According to the method, by means of multiple fine procedures and advanced equipment, the dimensional precision and form and location tolerance of all parts of the supporting disc are effectively guaranteed, and the high-end mechanical assembly requirement is met. Meanwhile, the machining and turnover time is shortened through the reasonable process and the numerical control technology, production efficiency is improved, and cost is reduced.

Description

Technical Field

[0001] The present invention belongs to the technical field of machining of support disk structural parts, and relates to a machining method for support disk structural parts of military aircraft. Background Art

[0002] In the field of mechanical manufacturing, the support disk, as a key basic component in many mechanical devices, is mainly used to carry and support relevant rotating or moving components, and its machining quality directly affects the stability, precision and service life of mechanical devices. The existing support disk machining processes have problems such as insufficient machining accuracy, poor surface quality and low production efficiency, and it is difficult to meet the requirements of high-precision and high-performance of parts in the high-end equipment manufacturing industry. In addition, the traditional process has a low utilization rate of raw materials during machining, resulting in a certain degree of waste, and the environmental protection issues during machining have gradually attracted attention. Summary of the Invention

[0003] In order to solve the above technical problems, the present invention adopts the following technical solutions:

[0004] A machining method for support disk structural parts of military aircraft, the specific steps include:

[0005] Blank pretreatment step: The selected metal raw material is subjected to hot forging forming operation by a forging press, and undergoes multiple upsetting and drawing processes to obtain a blank formed part;

[0006] Rough machining step: First, the above-mentioned blank formed part is clamped on a CNC lathe for rough turning, leaving corresponding allowances for subsequent finish machining, and then transferred to a five-axis linkage machining center for machining operations on complex structures;

[0007] Central structure machining step: A CNC drill with a high-precision positioning system is used to machine screw through holes on the outer ring of the support disk, and then a high-precision boring machine is used to machine the bearing holes on the inner ring of the support disk;

[0008] Finish machining step: For the workpiece after central structure machining, three surface grinding processes and multiple CNC machining processes are carried out in sequence, and then a high-precision internal grinding machine is used to grind the inner ring bearing holes;

[0009] Post-treatment step: The machined support disk is successively subjected to processes such as cleaning, chamfering, marking, fitter treatment and inspection. After passing the inspection, anti-rust packaging is carried out and stored in the warehouse.

[0010] As a further solution of the present invention: The metal raw material is medium carbon alloy steel with a carbon content in the range of 0.3% to 0.5%.

[0011] As a further solution of the present invention: in the rough turning process of the CNC lathe, a three-jaw chuck or a four-jaw chuck is used for clamping operation.

[0012] As a further solution of the present invention: the high-precision positioning system of the CNC drilling machine can ensure that the drilling position accuracy is controlled within ±0.05 mm.

[0013] As a further solution of the present invention: for the first surface grinding process, a brown fused alumina grinding wheel with a grit size of 46# is selected; for the second time, a white fused alumina grinding wheel with a grit size of 80# is selected; for the third time, a green silicon carbide grinding wheel with a grit size of 120# is selected.

[0014] As a further solution of the present invention: the CNC machining process uses an artificial intelligence-based CNC programming optimization technology to optimize the tool path and cutting parameters.

[0015] As a further solution of the present invention: the cleaning process is carried out by means of an ultrasonic cleaning device equipped with a circulating filtration system, using an environmentally friendly water-based cleaning agent that is biodegradable.

[0016] The beneficial effects of the present invention: Through multiple fine machining processes and advanced processing equipment, it can effectively ensure the dimensional accuracy and geometric tolerances of each part of the support disk, meeting the assembly requirements of high-end mechanical equipment. The reasonably optimized process flow and advanced CNC machining technology reduce the machining time and the turnover time between processes, improve production efficiency, and reduce production costs. Brief Description of the Drawings

[0017] Figure 1 It is a schematic structural diagram of the support disk structural part to be machined in the present invention. Detailed Embodiments

[0018] Next, the technical solutions in the embodiments of the present application will be clearly and completely described in conjunction with the drawings in the embodiments of the present application. Obviously, the described embodiments are only a part of the embodiments of the present application, rather than all the embodiments. It should be understood that the present application is not limited by the exemplary embodiments disclosed herein. Based on the embodiments in the present application, all other embodiments obtained by those of ordinary skill in the art without creative efforts fall within the scope of protection of the present application.

[0019] In the embodiments of the present invention, unless otherwise clearly defined and limited, terms such as "installation", "connection", "linkage", "fixation" shall be understood in a broad sense. For example, it can be a fixed connection, a detachable connection, or integrated; it can be a mechanical connection or an electrical connection; it can be directly connected or indirectly connected through an intermediate medium, and it can be the internal communication of two components or the interaction relationship between two components. For those of ordinary skill in the art, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0020] In the embodiments of the present invention, a processing method for a support disk structural part of a military aircraft is used for the preparation work of the support disk structural part (please refer to Figure 1 ). The specific steps are as follows:

[0021] Pretreatment of the blank: The selected metal raw material is subjected to flaw detection to ensure no internal cracks, sand holes and other defects. The selected metal material is medium carbon alloy steel with a carbon content of 0.3%-0.5%. Subsequently, a forging press is used for hot forging at a temperature range of 1050°C-1150°C. During the hot forging process, at least 4 alternate operations of upsetting and drawing are carried out, and the deformation amounts of each upsetting and drawing are respectively controlled between 35%-45% and 25%-35% to refine the grains and improve the internal organizational structure, and finally a forged blank is obtained;

[0022] Rough machining stage: First, the forged blank is accurately clamped on a numerically controlled lathe equipped with a high-precision rotary table, and rough turning is carried out using a coated carbide tool according to the pre-compiled machining program to remove most of the machining allowance; then the rough-turned workpiece is transferred to a five-axis linkage machining center, and the five-axis linkage technology is used to machine complex curved surfaces and special structures. At the same time, a cutting force monitoring system is used to adjust the cutting parameters in real time to ensure that the dimensional accuracy and geometric tolerances of each part meet the requirements of the drawing;

[0023] Center structure machining: Using a numerically controlled drill equipped with a high-precision positioning system, a minimum quantity lubrication drilling process is adopted to evenly machine 18 screw through-holes with a diameter of 8.5 mm on the outer ring of the product. During the drilling process, the drilling position and hole diameter size are monitored in real time through a vision detection system; a combination of a high-precision internal grinding machine and a boring machine with an error compensation function is used to finely machine 17 combined hole positions with a diameter of 32 mm on the inner ring of the product;

[0024] Finishing machining stage: The workpiece after center structure machining is subjected to at least three surface grinding operations successively. For the first surface grinding, a brown fused alumina grinding wheel with a grit size of 46# is used to quickly remove the large machining marks on the workpiece surface and ensure that the flatness is within the range of 0.05 mm;

[0025] For the second surface grinding, a white fused alumina grinding wheel with a grit size of 80# is used to further improve the surface finish of the plane;

[0026] For the third surface grinding, a green silicon carbide grinding wheel with a grit size of 120# is used to make the flatness of the upper and lower surfaces of the support disk within 0.01 mm;

[0027] Then, through multiple CNC machining processes again, fine machining and dimensional correction are carried out on various parts of the support disk; finally, a high-precision internal grinding machine is used to finely grind the inner ring bearing hole, and a superhard abrasive grinding wheel is used during the grinding process;

[0028] Post-treatment stage:

[0029] Cleaning: The processed support disk is placed in an ultrasonic cleaning device equipped with a circulating filtration system, and a biodegradable and environmentally friendly water-based cleaning agent is used. The cleaning time is 18 - 22 minutes to remove impurities such as oil stains and iron filings on the surface;

[0030] Chamfering: An automated chamfering device is used to chamfer and deburr all sharp edges of the support disk;

[0031] Marking: A high-resolution laser marking device is used to mark the product model, specifications, production date, production batch, and QR code traceability information on the surface of the support disk;

[0032] Fitter treatment: By means of manual inspection and repair, possible minor defects are removed; comprehensive inspections are carried out on various dimensional accuracies, geometric tolerances, surface roughness, etc. of the support disk, and statistical process control (SPC) methods are used for data analysis and quality monitoring during the inspection process; the qualified support disks are subjected to vapor phase rust prevention treatment and then packaged according to the customized anti-static and anti-collision packaging requirements, and then stored in the warehouse.

[0033] It should also be noted that in this article, relational terms such as first and second are only used to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any actual relationship or order between these entities or operations. Moreover, the term "including", "comprising" or any other variant thereof is intended to cover non-exclusive inclusion, so that a process, method, article or device including a series of elements not only includes those elements, but also includes other elements not expressly listed, or further includes elements inherent to such process, method, article or device. Without further limitation, an element defined by the statement "including a..." does not exclude the existence of additional identical elements in the process, method, article or device including the said element.

[0034] The foregoing description of the disclosed embodiments enables those skilled in the art to practice or use the present application. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the general principles defined herein may be implemented in other embodiments without departing from the spirit or scope of the present application. Thus, the present application is not intended to be limited to the embodiments shown herein but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.

Claims

1. A processing method for a support disk structural part of a military aircraft, characterized in that, The specific steps include: Blank pre-treatment step: The selected metal raw material is subjected to hot forging forming operation by a forging press and undergoes multiple upsetting and drawing processes to obtain a blank formed workpiece. Rough machining step: First, the aforementioned blank formed workpiece is clamped on a CNC lathe for rough turning, and then transferred to a five-axis linkage machining center for machining operations on complex structures. Central structure machining step: A high-precision CNC drill is used to machine screw through holes on the outer ring of the support disk, and then a high-precision boring machine is used to machine the bearing holes on the inner ring of the support disk. Finish machining step: For the workpiece after central structure machining, three surface grinding processes and multiple CNC machining processes are carried out in sequence, and then a high-precision internal grinding machine is used to grind the inner ring bearing holes. Post-treatment step: The completed support disk is successively subjected to processes such as cleaning, chamfering, marking, fitter work, and inspection. After passing the inspection, anti-rust packaging is carried out and stored in the warehouse.

2. The machining process of the support disk according to claim 1, characterized in that, The metal raw material is medium carbon alloy steel with a carbon content in the range of 0.3% to 0.5%.

3. The machining process of the support disk according to claim 1, characterized in that, The high-precision positioning system of the CNC drill can ensure that the drilling position accuracy is controlled within ±0.05 mm.

4. The machining process of the support plate according to claim 1, characterized in that, For the first surface grinding process, a brown fused alumina grinding wheel with a grit size of 46# is selected, for the second, a white fused alumina grinding wheel with a grit size of 80# is selected, and for the third, a green silicon carbide grinding wheel with a grit size of 120# is selected.

5. The machining process of the support plate according to claim 1, characterized in that, The cleaning process is carried out by using an ultrasonic cleaning device equipped with a circulating filtration system and a biodegradable environmentally friendly water-based cleaning agent.

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