Forging method of aviation undercarriage high package type forge piece

Abstract

The invention relates to a forging method of an aviation undercarriage high-package forging, belongs to the technical field of forging of high-strength steel aviation undercarriages, and solves the technical problem that a finish forging die and large forging equipment need to be used twice in a current forging process for manufacturing aviation undercarriage high-package workpieces. The method comprises the steps that a drawing tool is used for drawing a bar, so that the bar is formed into a step shaft-shaped blank with a high bag at one end; carrying out temperature control treatment on the blank; the blank is put into a blank manufacturing tool, the blank manufacturing tool is provided with a cavity, and a convex part is arranged in the cavity; a small fast forging machine acts on the blank manufacturing tool, and a rough blank is obtained; carrying out temperature control treatment on the rough blank; putting the blank subjected to temperature control treatment into a finish forging die; large forging equipment is used for acting on the finish forging die to forge the rough blank, so that the rough blank is forged into a formed forge piece in the finish forging die; and the formed forge piece is subjected to follow-up treatment, so that the formed forge piece is treated into a finished forge piece. The method for manufacturing the high-package forgings is lower in cost and shorter in finished product period.

Description

Technical Field

[0001] The invention belongs to the technical field of high-strength steel aviation landing gear forging, and particularly relates to a forging method for aviation landing gear high-package forgings. Background Art

[0002] The aircraft landing gear system is the main device for the aircraft to take off and land, and is a key component to ensure the safety of the aircraft. The connecting parts of the system have complex shapes, including thin web forgings, which have thin webs and high ribs and high laps on both sides. The traditional manufacturing method is to process the bar into an irregular rectangular billet by free hammer forging, and then forge it on a large forging equipment by multi-fire die forging.

[0003] The existing forging methods for landing gear thin web forgings are as follows: Figure 7 As shown, the specific process is as follows: the bar is stretched by a stretching tool to form a billet 200 with high laps at both ends, and then the billet 200 is subjected to temperature control treatment, and then the billet 200 is directly placed in the final forging die 100, and a large-scale forging equipment is used to perform the first forging (i.e., pre-forging treatment), so that a concave cavity is formed on the high lap of the billet 200, so that the billet 200 becomes a pre-forging, and then the pre-forging is subjected to temperature control treatment, and finally the pre-forging is placed in the final forging die 100 again, and a large-scale forging equipment is used to perform the second forging again, so that the pre-forging is formed into a finished forging. The cavity of the final forging die 100 in the related art is provided with a protrusion 110 corresponding to the concave cavity on the finished forging.

[0004] Since no cavity is formed on the high package of the billet 200 with high packages at both ends after being stretched, when the billet 200 is placed in the final forging die 100, Figure 1 As shown, the blank 200 cannot be well positioned and limited in the cavity of the final forging die 100 (Note: the above positioning and limiting rely on the cooperation of the above concave cavity and the above protrusion 110), and the blank 200 can only be placed in the accurate position as much as possible relying on the experience of the operator. However, in actual operation, the placement position of the blank 200 in the cavity of the final forging die 100 usually has a certain deviation from the ideal position. In addition, the cavity size of the final forging die 100 is larger than the blank 200. Therefore, when the first forging is performed in the final forging die 100, the blank 200 will have a certain displacement, which is prone to instability and scrapping in severe cases. Even if the displacement is very small, the size and / or shape of the concave cavity and high package on the pre-forged part formed by the first forging will also have a certain deviation. Therefore, the pre-forged part obtained by the first forging usually needs to be manually polished and trimmed, which will undoubtedly increase the labor workload of the workers and increase the manufacturing cost of the landing gear.

[0005] Moreover, in the above-mentioned forging process, the final forging die 100 and the large forging equipment need to be used twice, which will cause serious wear of the final forging die 100. The cost of using the large forging equipment and the final forging die 100 is also very high, which is bound to increase the cost of enterprises in manufacturing aircraft landing gear. Summary of the invention

[0006] The invention provides a forging method for high-package forgings of aircraft landing gear, which is used to solve the technical problem that the current forging process for manufacturing high-package forgings of aircraft landing gear requires twice using a final forging die and large-scale forging equipment.

[0007] The present invention is implemented by the following technical scheme: A forging method for high-package forgings of aviation landing gear, comprising:

[0008] Step 1: Use a drawing tool to draw the bar material so that the bar material is formed into a step shaft-shaped blank with a high package at one end;

[0009] Step 2: performing temperature control treatment on the blank;

[0010] Step 3: placing the temperature-controlled blank into a blank-making tool, wherein the blank-making tool is provided with a cavity adapted to the blank, and the cavity of the blank-making tool is provided with a convex portion adapted to the concave cavity on the finished forging and a concave portion adapted to the high package on the finished forging, wherein the convex portion includes a first convex portion close to one end of the cavity and a long strip convex portion located in the middle of the cavity, and the bottom of the concave portion is provided with a second convex portion close to the other end of the cavity;

[0011] Step 4: Using a small fast forging machine to act on the blank making tool to forge the blank, so that the blank is forged in the blank making tool into a rough blank with a high package and a corresponding concave cavity;

[0012] Step 5: performing temperature control treatment on the blank;

[0013] Step 6: placing the blank after temperature control treatment into the final forging die, so that the concave cavity on the blank matches with the protrusion on the cavity wall of the final forging die, so that the blank is accurately positioned in the final forging die;

[0014] Step 7: Using large-scale forging equipment to act on the final forging die to forge the blank, so that the blank is forged into a formed forging in the final forging die;

[0015] Step 8: performing subsequent processing on the formed forging to process the formed forging into a finished forging.

[0016] Furthermore, in order to better realize the present invention, the blank making tooling includes an upper die and a lower die, the upper die and the lower die are respectively provided with an upper cavity and a lower cavity, the lower cavity and the upper cavity are both provided with grooves adapted to the high package on the blank, the convex portion is arranged on the cavity wall of the upper cavity, and after the upper die and the lower die are closed, the upper cavity and the lower cavity are assembled to form the cavity of the blank making tooling.

[0017] Furthermore, in order to better implement the present invention, before step 1, the following steps are further included:

[0018] The rod is heated to 1000°C-1250°C and kept at this temperature for 105min-205min.

[0019] Furthermore, in order to better implement the present invention, when the bar material is heated or kept warm, the drawing tool is heated so that the temperature of the drawing tool is raised to greater than or equal to 200°C.

[0020] Furthermore, in order to better implement the present invention, in the step 1, the length of the billet formed by drawing the bar is 1210 mm, and the temperature of the billet after drawing is greater than or equal to 800°C.

[0021] Further, in order to better implement the present invention, the temperature control treatment of the blank in step 2 includes:

[0022] The billet obtained after drawing is immediately placed in a heating furnace for heating, so that the billet is heated to 1000° C.-1250° C. and kept warm for 30 min-130 min.

[0023] Furthermore, in order to better implement the present invention, when the blank is heated or kept warm, the blank-making tool is heated so that the temperature of the blank-making tool rises to greater than or equal to 200°C.

[0024] Further, in order to better implement the present invention, the temperature control treatment of the blank in step 5 includes:

[0025] The blank forged by the blank making tool is immediately placed in a heating furnace for heating, so that the blank is heated to 1000° C.-1250° C. and kept warm for 90 min-120 min.

[0026] Further, in order to better implement the present invention, the temperature control treatment of the blank in step 5 includes:

[0027] The blank forged by the blank making tool is turned 180 degrees, and then placed in a heating furnace for heating, so that the blank is heated to 1000°C-1250°C, and kept warm for 90min-120min.

[0028] Further, in order to better implement the present invention, the subsequent processing of the formed forging in step 8 includes:

[0029] air cooling the formed forging;

[0030] The air-cooled forging is ground and trimmed.

[0031] Compared with the prior art, the present invention has the following beneficial effects:

[0032] The forging method of high-bump forgings of aviation landing gear provided by the present invention utilizes a blank making tooling in cooperation with a small-scale fast forging machine to perform blank making processing on a drawn blank to obtain a rough blank, so that a high bump and a concave cavity matching with a protrusion on a final forging die are formed at the end of the blank, and the high bump of the rough blank also has a concave cavity matching with the protrusion on the final forging die, and then the rough blank is placed in the final forging die, and the concave cavity on the rough blank matches with the protrusion in the die cavity of the final forging die, so that the rough blank placed in the final forging die is accurately positioned, and then large-scale forging equipment is used for forging to obtain a formed forging, and finally the formed forging is subjected to subsequent processing to obtain a finished forging.

[0033] In this method, a blank is formed on the drawn blank by using a blank making tool and a small fast forging machine instead of a final forging die and a large forging equipment. The blank is provided with a cavity matched with the blank, so that the blank can be accurately positioned when placed in the cavity of the blank making tool without any deviation during the blank making process. In addition, the cavity of the blank making tool is provided with corresponding convex portions and grooves corresponding to the high package, so that during the blank making process, a concave cavity matched with the convex portion on the final forging die can be formed on the high package and the blank to match the convex portion on the final forging die, so that the blank placed in the final forging die for final forging can be accurately positioned and limited in the final forging die, and the blank can be placed in the cavity of the final forging die more accurately.

[0034] Thus, in the forging method, only the final forging die and large forging equipment need to be used during the final forging. In the process of making the blank into a rough blank, a blank making tool and a small fast forging machine are used. Compared with the existing forging process for high-package forgings of landing gear, the forging method provided by the present invention uses the final forging die and large forging equipment less frequently, because the use cost of the final forging die and large forging equipment is higher. Therefore, the forging method has a lower cost for manufacturing high-package forgings of aviation landing gear, and less wear on the final forging die. In addition, the rough blank placed in the final forging die can be placed in the correct position. During the final forging process, the offset of the rough blank in the cavity of the final forging die is almost zero, so the wear on the final forging die can also be reduced, and the yield rate of forgings can also be improved. During the blank making process, the rough blank can be quickly placed in the cavity of the blank making tool in the correct position, so the deviation caused by manual swinging can be eliminated to ensure that the rough blank formed by the rough blank meets the requirements more effectively, and the rough blank obtained by blank making does not need to be polished. and trimming, it can be directly heated and then placed in the final forging die, so the operations of grinding and trimming the rough billet can be omitted, thereby reducing the labor of workers, saving the manufacturing cost of high-package forgings for aviation landing gear, and shortening the production cycle of high-package forgings for aviation landing gear. In addition, the billet making process and the final forging treatment are respectively carried out in the billet making tooling and the final forging die, so the billet making treatment and the final forging treatment of different forgings can be carried out at the same time, so that continuous production can be achieved and the production cycle of high-package forgings for aviation landing gear can be further shortened; further, the billet after drawing is directly heated and then placed in the billet making tooling for billet making treatment. In the existing forging process, the billet needs to be placed in the final forging die for pre-forging treatment. Therefore, the existing forging process also needs to air-cool, detect and heat the billet before pre-forging treatment. Therefore, the method provided by the present invention can also omit the steps of air-cooling and detecting the billet, further reducing labor costs and shortening the manufacturing cycle. BRIEF DESCRIPTION OF THE DRAWINGS

[0035] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0036] Figure 1 It is a schematic diagram of the swing positioning of a billet with high laps at both ends in a final forging die in the existing forging process of high lap forgings of aviation landing gear;

[0037] Figure 2 It is a schematic diagram of the swing positioning of the blank produced by the forging method provided in the embodiment of the present invention in the final forging die;

[0038] Figure 3It is a schematic structural diagram of a blank making tool in an embodiment of the present invention;

[0039] Figure 4 Schematic diagram of the structure of the lower die of the blank making tool in the embodiment of the present invention;

[0040] Figure 5 Schematic diagram of the structure of the upper die of the blank making tool in the embodiment of the present invention;

[0041] Figure 6 It is a flow chart of a forging method of aviation landing gear high package forgings provided by an embodiment of the present invention;

[0042] Figure 7 The present invention is a flow chart of a forging method for high-package forgings of aviation landing gear in the prior art.

[0043] In the figure:

[0044] 100-final forging die, 110-protrusion, 200-blank with high bulges at both ends, 300-rough blank, 400-blank making tooling, 410-lower die, 411-lower cavity, 420-upper die, 421-upper cavity, 422-protrusion, 4221-first protrusion, 4222-long strip protrusion, 4223-second protrusion, 423-groove. DETAILED DESCRIPTION

[0045] To make the purpose, technical solution and advantages of the present invention clearer, the technical solution of the present invention will be described in detail below. Obviously, the described embodiments are only part of the embodiments of the present invention, rather than all the embodiments. Based on the embodiments of the present invention, all other implementation methods obtained by ordinary technicians in this field without creative work belong to the scope of protection of the present invention.

[0046] Example:

[0047] like Figure 2-Figure 6 As shown, the forging method of the aviation landing gear high package forging provided by the present invention comprises the following steps:

[0048] Step 1:

[0049] The bar is stretched by a stretching tool, so that the bar is formed into a step shaft-shaped blank with a high package at one end. The stretching tool is a prior art, and the method of stretching the bar using the stretching tool is the same as the prior art, so it will not be described in detail here.

[0050] In this embodiment, the raw material of the bar is high-strength steel material, and the bar specification is φ300×650mm. Before drawing, the bar needs to be heated to a temperature of 1000℃-1250℃, and kept warm for 105min-205min, so that the inside of the bar is heated evenly. Optionally, the bar is heated to 1000℃, 1150℃, or 1250℃ before drawing, and the holding time is 105min, 155min, or 205min.

[0051] When heating or keeping the bar stock warm, the drawing tool is heated by a heating device so that the temperature of the drawing tool is raised to 200°C or higher. For example, before the drawing process, the drawing tool is heated to 200°C, 210°C or 220°C. By drawing the heated bar stock with the heated drawing tool, cracking due to a sudden drop in temperature when the bar stock contacts the colder drawing tool can be avoided, so as to ensure that the bar stock is smoothly drawn to the desired length and shape.

[0052] After step 1, the rod is stretched to form a blank, and the length of the blank is 1200 mm. It is necessary to ensure that the temperature of the blank is greater than or equal to 800°C at the moment of stretching. For example, the temperature of the blank is 800°C, 820°C or 850°C at the moment of stretching.

[0053] Step 2:

[0054] The temperature of the blank obtained after the drawing is controlled so that the temperature of the blank is more reasonable when it is loaded into the blank making tool 400. Specifically, the temperature control treatment in this step includes:

[0055] The billet obtained after drawing is immediately placed in a heating furnace for heating, so that the billet is heated to 1000°C-1250°C and kept at this temperature for 30min-130min. For example, the billet is heated to 1000°C, 1150°C or 1250°C, and the holding time is 30min, 80min or 130min, so that the inside of the billet is evenly heated.

[0056] When the blank is heated or kept warm, the blank making tool 400 is heated by a heating device so that the temperature of the blank making tool 400 rises to 200° C. or higher. For example, before the blank making process, the blank making tool 400 is heated to 200° C., 210° C., or 220° C. By using the heated blank making tool 400 to process the blank, cracking of the blank due to a sudden drop in temperature when the blank contacts the cold blank making tool 400 can be avoided, thereby ensuring that the blank is smoothly forged into the blank 300.

[0057] Step 3:

[0058] The temperature-controlled blank is placed in a heated blank-making tool 400, which is provided with a cavity adapted to the blank, wherein the cavity is provided with a convex portion 422 adapted to the concave cavity on the finished forging and a concave portion 423 adapted to the high package on the finished forging, wherein the convex portion 422 includes a first protrusion 4221 close to one end of the cavity and a long protrusion 4222 located in the middle of the cavity, and the bottom of the groove is provided with a second protrusion 4223 close to the other end of the cavity.

[0059] The blank making tool 400 provided in this embodiment includes an upper die 420 and a lower die 410, and the upper die 420 and the lower die 410 are respectively provided with an upper cavity 421 and a lower cavity 411, and the lower cavity 411 and the upper cavity 421 are both provided with a groove 423 adapted to the high package on the blank. Putting the blank into the blank making tool 400 actually refers to putting the blank into the lower cavity 411 of the lower die 410, and the high package on the blank falls into the above-mentioned groove 423, so as to position and limit the blank. The above-mentioned protrusion 422 is arranged on the cavity wall of the upper cavity 421, and the upper die 420 is connected to a small fast forging machine. After the upper die 420 and the lower die 410 are closed, the above-mentioned upper cavity 421 and the lower cavity 411 are assembled to form the cavity of the blank making tool 400.

[0060] Specifically, the above grooves 423 are provided at both ends of the lower cavity 411 of the lower die 410 in this embodiment, wherein the groove 423 at one end is adapted to the high package with a larger size on the blank 300, and the groove 423 at the other end is adapted to the high package with a smaller size on the blank 300, and there is a linear middle groove between the grooves 423 at both ends, and the middle groove connects the grooves 423 at both ends. The high package at one end of the blank in this embodiment corresponds to the high package with a larger size on the blank 300. When the blank is placed in the lower cavity 411 of the lower die 410, the end of the blank without the high package is first placed in the corresponding groove 423, and then the blank is released, so that the high package at the other end of the blank automatically falls into the corresponding groove 423 under the action of gravity. In this way, the blank can be accurately placed in the lower cavity 411 of the lower die 410 during blank making, and the cavity wall of the lower cavity 411 is used to position and limit the blank.

[0061] The upper cavity 421 in this embodiment has a groove 423 and a middle groove corresponding to the lower cavity 411. When the upper die 420 and the lower die 410 are closed, the groove in the upper cavity 421 of the upper die 420 and the groove in the lower cavity 411 of the lower die 410 act together on the two ends of the blank, so that a larger high package and a smaller high package are forged at both ends of the blank respectively, and a concave cavity corresponding to the above-mentioned convex portion 422 is formed on the high package, and the concave cavity is adapted to the convexity 110 in the cavity of the final forging die 100.

[0062] In this step, the drawn billet is directly heated and then placed in the billet making tool 400 for billet making. In the existing forging process, the billet needs to be placed in the final forging die 100 for billet making. Therefore, the existing forging process also needs to air-cool, test and heat the billet before billet making. Therefore, the method provided by the present invention can also omit the steps of air-cooling and testing the billet, further reducing labor costs and shortening the manufacturing cycle.

[0063] In addition, during the blank making process, the blank can be quickly placed in the correct position when placed in the cavity of the blank making tool, thereby eliminating the deviation caused by manual material swinging to ensure that the blank 300 formed by the blank is more in line with the requirements, and the blank 300 obtained by blank making does not require grinding and trimming, and can be directly heated and placed in the final forging die 100, so the operations of grinding and trimming the blank 300 can also be omitted, thereby reducing the labor workload of workers, saving the manufacturing cost of high-package forgings of aviation landing gear, and shortening the production cycle of high-package forgings of aviation landing gear. The shape and size of the blank 300 obtained by the blank making process are more precise, which helps to improve the final qualified rate of forgings.

[0064] Step 4:

[0065] A small fast forging machine is used on the above-mentioned blank making tool 400 to forge the blank, so that the blank is forged in the blank making tool 400 into a rough blank 300 with a high package and a suitable cavity. Since the blank is placed in the blank making tool 400 more accurately, the shape and size of the produced rough blank 300 are more in line with the requirements, and the position, shape and size of the cavity on the rough blank 300 are also more in line with the requirements.

[0066] It is worth noting that in the existing related forging process, the billet 200 with high laps at both ends after being stretched is placed in the final forging die 100, and a large forging equipment is used for pre-forging. Since the cavity of the final forging die 100 is larger than the size of the billet 200 and there is no concave cavity on the high lap, the placement of the billet 200 in the final forging die 100 is as shown in the attached figure. Figure 1 As shown, the blank 200 cannot be effectively positioned and limited in the final forging die 100, so during the blank making process, the blank is prone to deviation, and the pre-forged parts obtained by pre-forging have errors in size and shape, resulting in instability or even scrapping. Therefore, manual grinding and trimming of the pre-forged parts are required.

[0067] Since the small fast forging machine belongs to the prior art, it will not be described in detail here.

[0068] Step 5:

[0069] The blank 300 obtained in step 4 is subjected to temperature control treatment so that the temperature of the blank 300 when it is loaded into the final forging die 100 is more in line with the requirements. Specifically, the temperature control treatment in this step includes:

[0070] The blank 300 forged by the blank making tool 400 is immediately placed in a heating furnace for heating, so that the blank 300 is heated to 1000°C-1250°C and kept at this temperature for 90min-120min. For example, the blank 300 is heated to 1000°C, 1150°C or 1250°C, and the holding time is 90min, 105min or 120min, so that the inside of the blank 300 is evenly heated.

[0071] Or:

[0072] The blank 300 forged by the blank making tool 400 is turned 180 degrees and placed on a swing frame for air cooling, and then the air-cooled blank 300 is placed in a heating furnace for heating, so that the blank 300 is heated to 1000°C-1250°C and kept warm for 90min-120min. For example, the blank 300 is heated to 1000°C, 1150°C, or 1250°C, and the holding time is 90min, 105min, or 120min, so that the inside of the blank 300 is evenly heated.

[0073] Step 6:

[0074] The blank 300 after temperature control treatment is placed in the final forging die 100, so that the concave cavity on the blank 300 matches the protrusion 110 on the cavity wall of the final forging die 100, so that the blank 300 is accurately positioned in the final forging die 100. Since the shape and size of the blank 300 are more in line with the requirements, the position, shape and size of the concave cavity on the high package of the blank 300 are also more in line with the requirements, so the placement position of the blank 300 in the final forging die 100 is also more accurate. During the final forging process, the offset of the blank 300 is almost zero, so the wear on the final forging die 100 can be reduced and the yield rate of forgings can be improved.

[0075] Step 7:

[0076] The blank 300 is forged by using large-scale forging equipment to act on the final forging die 100 , so that the blank 300 is forged into a formed forging in the final forging die 100 , and the formed forging is closer to the finished forging.

[0077] The forging method through the above steps, that is, the forging method of aviation landing gear high-package forgings provided in an embodiment of the present invention, only needs to use the final forging die 100 and large-scale forging equipment during final forging. In the process of making the blank 300 from the blank, the blank making tool 400 and a small fast forging machine are used. Compared with the existing forging process of landing gear high-package forgings, the forging method provided by the present invention uses the final forging die 100 and large-scale forging equipment less frequently, because the use cost of the final forging die 100 and large-scale forging equipment is higher. Therefore, the forging method has a lower cost for manufacturing aviation landing gear high-package forgings and less wear on the final forging die 100.

[0078] Step 8:

[0079] The formed forging obtained in step 7 is subsequently processed to be processed into a finished forging.

[0080] Specifically, the subsequent processing of the formed forging in this step includes:

[0081] The formed forging obtained in the final forging die 100 is taken out and air-cooled to cool the formed forging to room temperature, and then the formed forging is polished and trimmed to finally obtain a finished forging.

[0082] The above is only a specific embodiment of the present invention, but the protection scope of the present invention is not limited thereto. Any person skilled in the art can easily think of changes or substitutions within the technical scope of the present invention, which should be included in the protection scope of the present invention. Therefore, the protection scope of the present invention should be based on the protection scope of the claims.

Claims

1. A forging method for high-package forgings of aviation landing gear, characterized in that: include: Step 1: Use a drawing tool to draw the bar material so that the bar material is formed into a step shaft-shaped blank with a high package at one end; Step 2: performing temperature control treatment on the blank; Step 3: placing the temperature-controlled blank into a blank-making tool (400), wherein the blank-making tool (400) is provided with a cavity adapted to the blank, and the cavity of the blank-making tool (400) is provided with a convex portion (422) adapted to the concave cavity on the finished forging and a concave portion (423) adapted to the high package on the finished forging, wherein the convex portion (422) includes a first protrusion (4221) close to one end of the cavity and a long strip protrusion (4222) located in the middle of the cavity, and the bottom of the groove (423) is provided with a second protrusion (4223) close to the other end of the cavity; Step 4: using a small-sized fast forging machine to act on the blank making tool (400) to forge the blank, so that the blank is forged in the blank making tool (400) into a blank (300) having a high package and a corresponding concave cavity; Step 5: performing temperature control treatment on the blank (300); Step 6: placing the blank (300) after the temperature control treatment into the final forging die (100), so that the concave cavity on the blank (300) matches with the protrusion (110) on the cavity wall of the final forging die (100), so that the blank (300) is accurately positioned in the final forging die (100); Step 7: using large-scale forging equipment to act on the final forging die (100) to forge the blank (300), so that the blank (300) is forged into a formed forging in the final forging die (100); Step 8: performing subsequent processing on the formed forging to process the formed forging into a finished forging.

2. The forging method of high-package forgings for aircraft landing gear according to claim 1, characterized in that: The blank making tool (400) comprises an upper die (420) and a lower die (410), wherein the upper die (420) and the lower die (410) are respectively provided with an upper cavity (421) and a lower cavity (411), wherein the lower cavity (411) and the upper cavity (421) are both provided with a groove (423) adapted to the high package on the blank, and the convex portion (422) is provided on the cavity wall of the upper cavity (421), and after the upper die (420) and the lower die (410) are molded together, the upper cavity (421) and the lower cavity (411) are assembled to form the cavity of the blank making tool (410).

3. The forging method of high-package forgings for aircraft landing gear according to claim 1, characterized in that: Before step 1, the method further includes: The rod is heated to 1000°C-1250°C and kept at this temperature for 105min-205min.

4. The forging method of high-package forgings for aircraft landing gear according to claim 3, characterized in that: When the bar material is heated or kept warm, the drawing tool is heated so that the temperature of the drawing tool is raised to be greater than or equal to 200°C.

5. The forging method of high-package forgings for aircraft landing gear according to claim 1, characterized in that: In the step 1, the length of the blank formed by drawing the bar is 1200 mm, and the temperature of the blank after drawing is greater than or equal to 800° C.

6. The forging method of aircraft landing gear high package forgings according to claim 5, characterized in that: The temperature control treatment of the blank in step 2 includes: The billet obtained after drawing is immediately placed in a heating furnace for heating, so that the billet is heated to 1000° C.-1250° C. and kept warm for 30 min-130 min.

7. The forging method of high-package forgings for aircraft landing gear according to claim 6, characterized in that: When the blank is heated or kept warm, the blank making tool (400) is heated so that the temperature of the blank making tool (400) rises to be greater than or equal to 200°C.

8. The forging method of aircraft landing gear high package forgings according to claim 1, characterized in that: The temperature control treatment of the blank (300) in step 5 includes: The blank (300) forged by the blank making tool (400) is immediately placed in a heating furnace for heating, so that the blank (300) is heated to 1000° C.-1250° C., and the temperature is kept for 30 min-130 min.

9. The forging method of aircraft landing gear high package forgings according to claim 1, characterized in that: The temperature control treatment of the blank (300) in step 5 includes: The blank (300) forged by the blank making tool (400) is turned 180 degrees and then placed in a heating furnace for heating, so that the blank (300) is heated to 1000°C-1250°C and kept warm for 90min-120min.

10. The forging method of high-package forgings for aircraft landing gear according to any one of claims 1 to 9, characterized in that: The subsequent processing of the formed forging in step 8 includes: air cooling the formed forging; The air-cooled forging is ground and trimmed.

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