A novel tail wing structure manufacturing method

Abstract

The present invention discloses a novel tail wing structure manufacturing method, comprising the following steps: S1, split forming of tail wing parts: split processing of tail pipe and tail wing part, using extrusion forming process to process tail pipe, and using casting and forging composite process to process tail wing part; S2, connection of tail wing parts: using stir friction welding process to connect tail pipe and tail wing part to obtain formed tail wing structure. The present invention adopts the above novel tail wing structure manufacturing method, and processes the tail pipe and tail wing seat which were originally produced in one piece separately, thus avoiding the problem of material waste caused by milling, which is conducive to reducing production cost, improving production efficiency, and ensuring that the produced products meet performance requirements, and is suitable for rapid mass production of tail wing structures.

Description

Technical Field

[0001] The invention relates to the technical field of tail wing processing, and in particular to a novel tail wing structure manufacturing method. Background Art

[0002] As one of the common military consumables in modern warfare, artillery shells are used in large quantities, which is a huge challenge for weapons manufacturers. During the use of artillery shells, the tail fin, as one of the key components, plays an important role. It can ensure that the artillery shells remain stable during flight and plays a decisive role in the accuracy of the weapon.

[0003] The tail fins of the shells are processed by integrated milling. However, due to the special structure of the tail fin, a whole piece of material is needed to mill out the tail pipe, tail fin seat and the grooves on the tail fin seat for installing the tail fin blades.

[0004] The tail tube is a short tube with a hollow structure. When in use, it needs to be filled with propellant, and when the shell is fired, the tube wall needs to withstand the expansion of the propellant. Therefore, the tail tube is required to have high strength and good flatness of the inner wall of the tail tube. This is to ensure stability while generating huge internal pressure during firing.

[0005] Traditionally, the tail wing seat and tail wing blade are split structures, wherein the tail wing blade is produced by forging and the tail wing seat is obtained by milling. During the processing of the tail wing seat, it is necessary to process multiple grooves for installing the tail wing blade and through holes required for riveting.

[0006] In the prior art, when manufacturing the tail pipe, it is necessary to cut the inside of it, which not only increases the processing time, but also causes a large waste of materials, resulting in increased costs. In addition, the production process of the tail wing seat is complicated, with high technical requirements and long processing time. For large-scale production, the production cycle of this process is long, and it is difficult to improve production efficiency. Summary of the invention

[0007] The purpose of the present invention is to provide a new tail wing structure manufacturing method, which separates the tail pipe and tail wing seat that were originally produced in an integrated manner, avoids the material waste problem caused by milling, is conducive to reducing production costs, improving production efficiency, and ensuring that the produced products meet performance requirements, and is suitable for rapid and large-scale production of tail wing structures.

[0008] To achieve the above object, the present invention provides a novel tail wing structure manufacturing method, comprising the following steps:

[0009] S1. Split-type forming of tail wing parts: The tail pipe and tail wing parts are processed separately, the tail pipe is processed by extrusion forming process, and the tail wing part is processed by casting and forging composite process;

[0010] S2. Tail wing parts connection: The tail pipe and the tail wing part are connected by using a stir friction welding process to obtain a formed tail wing structure.

[0011] Preferably, in step S1, the extrusion forming process is a cold extrusion forming process, and the specific process is as follows:

[0012] Sa1, placing the metal blank in the cold extrusion die cavity;

[0013] Sa2, at room temperature, applying pressure to the metal blank by a press machine to cause the metal blank to undergo plastic deformation to obtain a tail pipe;

[0014] The tail pipe has a length of 80 to 120 mm, a diameter of 30 to 50 mm, and a wall thickness of 2.5 to 5 mm;

[0015] The material of the metal blank is 2024 aluminum alloy.

[0016] Preferably, in step S1, the casting-forging composite process is liquid die forging, specifically, adding liquid metal material into a mold and forming it under high pressure in a machine.

[0017] Preferably, the mold comprises a die, a punch and a plurality of cooling channels arranged in the die, the die is a square frame structure, the inner side wall of the die is provided with arc-shaped convex blocks, there are gaps between adjacent arc-shaped convex blocks, a cylindrical convex block is provided at the center of the die, the height of the gap is smaller than the height of the cylindrical convex block, and the punch is provided with an inclined surface corresponding to the gap;

[0018] The concave mold is used to carry liquid metal materials, the convex mold is used to apply external loads, and cooling water is added to the cooling channel to accelerate the cooling of the ingot.

[0019] Preferably, the liquid metal material is made of ZL101 aluminum alloy.

[0020] Preferably, the specific process of the casting and forging composite process is:

[0021] Sb1, injecting liquid metal material into the concave mold through a pouring device;

[0022] Sb2, applying external pressure to the liquid metal under the action of the punch, filling and solidifying and crystallizing the metal under the dual action of gravity and external pressure, and accelerating the solidification process through the cooling channel;

[0023] Sb3. After the parts are cooled to room temperature, the punch is raised, and the formed parts are taken out with the help of the shorter cylindrical part protruding from the front end of the tail wing seat to obtain an integrally formed tail wing seat and tail wing blades.

[0024] Preferably, in step S2, the specific process of the friction stir welding process is:

[0025] S21, respectively fixing the tail pipe and the tail wing seat so that their end faces are butted against each other;

[0026] S22, a cylindrical stirring head extends into the joint between the tail pipe and the tail wing;

[0027] S23. When the stirring head rotates at high speed and moves along the welding part, the softened material flows from the front to the rear of the stirring head under the action of the rotating friction of the stirring head, and forms a dense solid phase weld under the extrusion of the stirring head.

[0028] Preferably, the rotation speed of the stirring head is 600-1000 r / min, and the travel speed is 30-50 mm / min.

[0029] Therefore, the present invention adopts the above-mentioned novel tail wing structure manufacturing method, and the beneficial effects are as follows:

[0030] (1) The present invention designs a new tail pipe forming process for the traditional tail pipe forming process. The tail pipe is obtained by cold extrusion. During the extrusion forming process, the inner wall of the tail pipe is extruded, and the obtained finished product has high precision and good surface quality, and there is no need to smooth the inner wall. At the same time, the extrusion process can improve the mechanical properties of the tail pipe, obtain parts that meet the requirements, simplify the processing process, reduce the loss of production materials, and help improve production efficiency and reduce production costs.

[0031] (2) The present invention designs a new manufacturing process based on the traditional tail wing part forming process. The tail wing seat and tail wing blades that were originally produced separately are obtained at one time through a casting and forging composite production process, and the grooves originally located on the tail wing seat for installing the tail wing blades are no longer needed. This can greatly reduce the complexity of the previous tail wing seat processing process, thereby improving the production efficiency of the tail wing part.

[0032] (3) The present invention processes and manufactures the tail pipe and the tail wing seat separately and then connects them. The processing of the joint is particularly important. The stir friction welding process is used to connect the tail pipe and the tail wing. During the welding process, the stir friction welding can achieve small changes in the microstructure of the heat affected zone of the welded joint, low residual stress at the weld, and the workpiece is not easy to deform after welding, which is beneficial to the good stability of the overall structure of the shell.

[0033] (4) The present invention processes the tail pipe and the tail wing seat, which are originally integrally formed, in steps, and the two steps are performed simultaneously, and then the tail pipe and the tail wing part are connected by stir friction welding, which is conducive to the rapid and large-scale production of tail wing structures. BRIEF DESCRIPTION OF THE DRAWINGS

[0034] Figure 1 It is a flow chart of an embodiment of a novel tail wing structure manufacturing method of the present invention;

[0035] Figure 2 It is a schematic diagram of the finished product of an embodiment of a novel tail wing structure manufacturing method of the present invention;

[0036] Figure 3 It is a structural schematic diagram of a tail wing part extrusion casting mold according to an embodiment of a novel tail wing structure manufacturing method of the present invention;

[0037] Figure 4 It is a schematic diagram of the interior of a tail wing part extrusion casting mold according to an embodiment of a novel tail wing structure manufacturing method of the present invention;

[0038] Figure 5 It is a schematic diagram of friction stir welding according to an embodiment of a novel tail wing structure manufacturing method of the present invention.

[0039] Reference numerals

[0040] 1. Tail pipe; 2. Tail wing seat; 3. Tail wing blade; 4. Punch; 5. Die; 6. Cooling channel; 7. Stirring head. DETAILED DESCRIPTION

[0041] The technical solution of the present invention is further described below through the accompanying drawings and embodiments.

[0042] Unless otherwise defined, technical or scientific terms used in the present invention shall have the common meanings understood by one having ordinary skills in the field to which the present invention belongs.

[0043] Embodiment 1

[0044] The processing principle of a new tail wing structure is as follows:

[0045] The tail pipe 1 and the tail wing part are changed from the previous one-piece milling process to a separate process, wherein the tail pipe 1 is processed by extrusion forming; the structure of the tail wing seat 2 is modified, and the groove previously used to fix the tail wing blade 3 is removed. The tail wing blade 3 is no longer processed separately, but is processed together with the tail wing seat 2 by a casting and forging composite method, which can reduce the processing difficulty and material loss of the tail wing part and improve production efficiency. At the same time, since the groove used to fix the tail wing blade 3 and the rivets used for riveting are removed, the weight of the overall structure is reduced, which is conducive to the performance optimization of the subsequent produced shells; the tail pipe 1 and the tail wing part obtained by separate processing are connected by stir friction welding. In this way, the residual stress at the connection between the two can be reduced, so that the obtained shell structure has good stability.

[0046] A novel tail wing structure manufacturing method comprises the following steps:

[0047] S1. Split-type forming of tail wing parts: The tail pipe 1 and the tail wing part are processed separately. The tail pipe 1 is processed by an extrusion forming process, and the tail wing part is processed by a casting and forging composite process. The tail wing part includes a tail wing seat 2 and a tail wing blade 3.

[0048] The extrusion forming process is a cold extrusion forming process, and the specific process is as follows:

[0049] Sa1, placing the metal blank in the cold extrusion die cavity;

[0050] Sa2. At room temperature, a press machine is used to apply pressure to the metal blank to cause the metal blank to undergo plastic deformation, thereby obtaining a tail pipe 1;

[0051] Specifically, the tail pipe 1 has a length of 80 to 120 mm, a diameter of 30 to 50 mm, and a wall thickness of 2.5 to 5 mm; the material of the metal blank is 2024 aluminum alloy. In this embodiment, a tail pipe 1 with a length of 100 mm, an outer diameter of 32 mm, and a wall thickness of 3 mm is obtained at one time through a cold extrusion forming process. The inner wall surface of the extruded tail pipe 1 has high precision and good quality, and no additional flattening treatment of the inner wall is required. In addition, extrusion forming can change the organizational structure of the raw material and improve its mechanical properties. At the same time, the process of using the extrusion forming process to produce the tail pipe 1 is simple, requires less equipment, has low production cost, and has high production efficiency, which is conducive to large-scale and large-volume production.

[0052] The tail part is formed into an integrated form by casting and forging composite processing to form the complex tail seat 2 and tail blade 3, removing the original structure for installing the tail blade 3 on the tail seat 2, greatly reducing the processing difficulty. Since the original processing technology is to produce the tail seat 2 by subtractive manufacturing, after the casting and forging composite is used to replace the original process, it is no longer necessary to use the traditional subtractive manufacturing method, which will reduce material consumption and thus reduce production costs.

[0053] The casting and forging composite process is liquid die forging, which involves adding liquid metal materials into a mold and forming them under high pressure in a machine. The parts obtained through extrusion casting do not have common casting defects such as pores and shrinkage holes like general castings. The parts have a tight internal structure and can be further improved in mechanical properties through heat treatment. The quality of extrusion castings is comparable to that of forgings. At the same time, due to its high production efficiency, it has the competitive advantages of high efficiency and low cost in casting production, and also has the advantages of forging production in mechanical properties and other aspects.

[0054] The mold includes a die 5, a punch 4 and a plurality of cooling channels 6 arranged in the die 5. The die 5 is a square frame structure. The inner side wall of the die 5 is provided with arc-shaped protrusions. There are gaps between adjacent arc-shaped protrusions. A cylindrical protrusion is provided at the center of the die 5. The height of the gap is smaller than the height of the cylindrical protrusion. The punch 4 is provided with an inclined surface corresponding to the gap.

[0055] The concave mold 5 is used to carry the liquid metal material, the convex mold 4 is used to apply an external load, and the cooling channel 6 is used to accelerate the cooling of the ingot. Cooling water is passed through the cooling channel 6.

[0056] The liquid metal material is ZL101 aluminum alloy.

[0057] The specific process of the casting and forging composite process is as follows:

[0058] Sb1. Inject high-temperature liquefied ZL101 aluminum alloy into the die 5 through a pouring device.

[0059] Sb2. Under the action of the punch 4, external pressure is applied to the liquid metal, and the metal is filled and solidified and crystallized under the dual action of gravity and external pressure, so as to achieve forced shrinkage compensation for shrinkage porosity and shrinkage cavities, so that a casting with excellent performance can be obtained, and the solidification process is accelerated through the cooling channel 6.

[0060] Sb3. After the parts are cooled to room temperature, the punch 4 is raised, and the formed parts are taken out with the help of the shorter cylindrical part protruding from the front end of the tail wing seat 2, so as to obtain the integrally formed tail wing seat 2 and tail wing blade 3.

[0061] S2. Tail wing parts connection: The tail pipe 1 and the tail wing part are connected by using a stir friction welding process to obtain a formed tail wing structure.

[0062] In the connection process between the tail pipe 1 and the tail wing part, it is necessary to ensure that the connection part has sufficient strength and good stability, so as to ensure that the shell remains stable during flight. Therefore, stir friction welding is used to connect the tail pipe 1 and the tail wing part. The specific process of stir friction welding is as follows:

[0063] S21, respectively fixing the tail pipe 1 and the tail wing seat 2 so that their end faces are butted against each other;

[0064] S22, a cylindrical stirring head 7 is inserted into the joint between the tail pipe 1 and the tail wing seat 2, and the specific welding position is as follows Figure 4 shown.

[0065] S23, through the high-speed rotation of the stirring head 7, it rubs against the welding workpiece material, so that the temperature of the material at the connection part rises and softens. At the same time, when the stirring head 7 moves along the welding part, the softened material flows from the front to the rear of the stirring head 7 under the action of the rotating friction of the stirring head 7, and forms a dense solid phase weld under the extrusion of the stirring head 7, thereby obtaining a formed tail wing structure, such as Figure 1 As shown. Stir friction welding has low heat input and good joint performance, and usually does not have conventional fusion welding defects such as welding pores, thermal cracks and post-weld stress corrosion cracks. Therefore, stir friction welding is used for the connection between the tail pipe 1 and the tail wing to ensure that the formed parts achieve the required performance.

[0066] In this embodiment, the rotation speed of the stirring head 7 is 700 r / min and the travel speed is 40 mm / min. , so as to ensure good welding and form a dense solid phase weld.

[0067] Therefore, the present invention adopts the above-mentioned new tail wing structure manufacturing method to separately process the tail pipe and tail wing seat that were originally produced in an integrated manner, thereby avoiding the material waste problem caused by milling, which is beneficial to reducing production costs, improving production efficiency, and ensuring that the produced products meet performance requirements. It is suitable for rapid and large-scale production of tail wing structures.

[0068] Finally, it should be noted that the above embodiments are only used to illustrate the technical solution of the present invention rather than to limit it. Although the present invention has been described in detail with reference to the preferred embodiments, those skilled in the art should understand that they can still modify or replace the technical solution of the present invention with equivalents, and these modifications or equivalent replacements cannot cause the modified technical solution to deviate from the spirit and scope of the technical solution of the present invention.

Claims

1. A novel tail wing structure manufacturing method, characterized in that: The following steps are involved: S1. Split-type forming of tail wing parts: The tail pipe and tail wing parts are processed separately, the tail pipe is processed by extrusion forming process, and the tail wing part is processed by casting and forging composite process; S2. Tail wing parts connection: The tail pipe and tail wing parts are connected by using a stir friction welding process to obtain a formed tail wing structure; In step S1, the casting and forging composite process is liquid die forging, specifically, adding liquid metal material into a die and forming it under high pressure in a machine; The mold comprises a die, a punch and a plurality of cooling channels arranged in the die. The die is a square frame structure. The inner side wall of the die is provided with arc-shaped convex blocks. There are gaps between adjacent arc-shaped convex blocks. A cylindrical convex block is provided at the center of the die. The height of the gap is smaller than the height of the cylindrical convex block. The punch is provided with an inclined surface corresponding to the gap. The concave mold is used to carry liquid metal material, the convex mold is used to apply external load, and cooling water is added to the cooling channel to accelerate the cooling of the casting; The material of the liquid metal material is ZL101 aluminum alloy; In step S1, the extrusion forming process is a cold extrusion forming process, and the specific process is as follows: Sa1, placing the metal blank in the cold extrusion die cavity; Sa2, at room temperature, applying pressure to the metal blank by a press machine to cause the metal blank to undergo plastic deformation to obtain a tail pipe; The material of the metal blank is 2024 aluminum alloy.

2. A novel tail wing structure manufacturing method according to claim 1, characterized in that: The tail pipe has a length of 80-120 mm, a diameter of 30-50 mm, and a wall thickness of 2.5-5 mm.

3. A novel tail wing structure manufacturing method according to claim 1, characterized in that: The specific process of the casting and forging composite process is as follows: Sb1, injecting liquid metal material into the concave mold through a pouring device; Sb2, applying external pressure to the liquid metal under the action of the punch, filling and solidifying and crystallizing the metal under the dual action of gravity and external pressure, and accelerating the solidification process through the cooling channel; Sb3. After the parts are cooled to room temperature, the punch is raised, and the formed parts are taken out with the help of the shorter cylindrical part protruding from the front end of the tail wing seat to obtain an integrally formed tail wing seat and tail wing blades.

4. A novel tail wing structure manufacturing method according to claim 1, characterized in that: In step S2, the specific process of the friction stir welding process is: S21, respectively fixing the tail pipe and the tail wing seat so that their end faces are butted against each other; S22, a cylindrical stirring head extends into the joint between the tail pipe and the tail wing; S23. When the stirring head rotates at high speed and moves along the welding part, the softened material flows from the front to the rear of the stirring head under the action of the rotating friction of the stirring head, and forms a dense solid phase weld under the extrusion of the stirring head.

5. A novel tail wing structure manufacturing method according to claim 4, characterized in that: The rotation speed of the stirring head is 600-1000r / min, and the travel speed is 30-50mm / min.

Images