CN111687592A - Integrated forming method for storage tank barrel section and integrated storage tank barrel section - Google Patents
Integrated forming method for storage tank barrel section and integrated storage tank barrel section Download PDFInfo
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- 238000000034 method Methods 0.000 title claims abstract description 44
- 238000003860 storage Methods 0.000 title claims abstract description 39
- 238000009987 spinning Methods 0.000 claims abstract description 89
- 239000000463 material Substances 0.000 claims abstract description 46
- 238000003466 welding Methods 0.000 claims abstract description 24
- 238000005096 rolling process Methods 0.000 claims abstract description 14
- 238000010438 heat treatment Methods 0.000 claims abstract description 10
- 238000007689 inspection Methods 0.000 claims abstract description 9
- 230000032683 aging Effects 0.000 claims abstract description 8
- 238000007514 turning Methods 0.000 claims abstract description 8
- 239000006104 solid solution Substances 0.000 claims abstract description 7
- 238000001125 extrusion Methods 0.000 claims abstract description 5
- 238000000137 annealing Methods 0.000 claims description 20
- 230000035882 stress Effects 0.000 claims description 14
- 238000003754 machining Methods 0.000 claims description 12
- 229910000838 Al alloy Inorganic materials 0.000 claims description 9
- 238000013000 roll bending Methods 0.000 claims description 5
- 239000000243 solution Substances 0.000 claims description 4
- 238000005452 bending Methods 0.000 claims description 3
- 238000003756 stirring Methods 0.000 claims description 3
- 238000003825 pressing Methods 0.000 claims description 2
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims description 2
- 230000015572 biosynthetic process Effects 0.000 claims 1
- 238000012545 processing Methods 0.000 abstract description 9
- 239000002131 composite material Substances 0.000 abstract description 4
- 238000005516 engineering process Methods 0.000 description 4
- 238000003801 milling Methods 0.000 description 4
- 239000003380 propellant Substances 0.000 description 4
- 238000004321 preservation Methods 0.000 description 3
- 239000002699 waste material Substances 0.000 description 3
- 238000011161 development Methods 0.000 description 2
- 230000018109 developmental process Effects 0.000 description 2
- 210000001503 joint Anatomy 0.000 description 2
- 238000003701 mechanical milling Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 239000000126 substance Substances 0.000 description 2
- 238000002048 anodisation reaction Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000005266 casting Methods 0.000 description 1
- 238000012937 correction Methods 0.000 description 1
- 238000005520 cutting process Methods 0.000 description 1
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
- B23P15/00—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21D—WORKING OR PROCESSING OF SHEET METAL OR METAL TUBES, RODS OR PROFILES WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21D22/00—Shaping without cutting, by stamping, spinning, or deep-drawing
- B21D22/14—Spinning
- B21D22/16—Spinning over shaping mandrels or formers
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/40—Arrangements or adaptations of propulsion systems
- B64G1/402—Propellant tanks; Feeding propellants
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Abstract
The invention provides an integrated forming method of a storage box barrel section and an integrated storage box barrel section, wherein an original barrel blank is obtained through a blank making process; installing a spinning die, installing the original cylinder blank outside the tool, extruding the cylinder blank material into the spinning die by adopting a flow spinning process until the cylinder blank material is attached to the spinning die, and forming a spun cylinder section; the integral solid solution aging is adopted, the material performance of the barrel blank is improved to a T6 state, and the internal structure performance of the barrel blank material is uniform, so that a part is formed; turning and flattening the local depression on the outer side of the part caused by extrusion; and (4) unloading the spinning die, taking out the formed part after the return stroke of the spinning wheel, and carrying out nondestructive inspection on the formed part. The invention utilizes the integral ring rolling cylinder blank/coil welding to form the cylinder blank, realizes the integral forming of the storage cylinder section with the rib structure by composite processing modes such as flow spinning forming, integral heat treatment, numerical control precision processing and the like, improves the material utilization rate, the product reliability and the dimensional precision, and realizes the integral near-net forming of the storage cylinder section of the carrier rocket.
Description
Technical Field
The invention relates to the technical field of spacecrafts, in particular to a storage tank barrel section integrated forming method and an integrated storage tank barrel section, and especially relates to a carrier rocket storage tank barrel section integrated forming process technology.
Background
The propellant storage tank is one of the most critical structural components of the carrier rocket, is a large-size, thin-wall and high-strength aluminum alloy welded structure, is used as a main bearing structure of the carrier rocket, is the largest structural component in the rocket body structure and the key component influencing the safety and reliability of the carrier rocket, and accounts for 60 percent of the total mass of the rocket and 2/3 percent of the total rocket length. The propellant storage tank has the typical characteristics of large size, light weight, thin wall, complexity and the like, and is also an important determinant factor of the carrying capacity and the deployment capacity of the carrier rocket. The propellant storage tank is formed by combining a tank bottom and a cylinder section, and the weight is reduced by adopting a high-strength aluminum alloy thin-wall grid skin structure such as 2A14, 2219 and the like.
At the present stage, after the barrel section of the propellant tank of the carrier rocket adopts the processes of panel roll bending forming, milling (mechanical milling/chemical milling), surface anodization treatment and the like, 3-6 sections of panels are welded into a whole, and the main processing difficulty existing at present is as follows: 1) after the wall plate parts are machined, the wall plate parts are influenced by factors such as mechanical milling/chemical milling deformation, residual stress release after the parts are rolled and bent, the resilience amount of the molded surface is large, a large amount of shape correction work is needed, and after the wall plate parts are finally welded into a storage box barrel section, the wall plate parts are difficult to completely overlap with an actual theoretical model due to the influence of factors such as welding deformation, so that the molded surface is difficult to accurately control; 2) 70% -90% of materials need to be removed in wallboard part machining grids, so that the material utilization rate is low, waste is serious, and meanwhile, due to the fact that the size of parts is large (the diameter is more than 2-3 meters) and the parts are of thin-wall structures (the wall thickness of the thinnest part is only about 2.3 mm), grid machining difficulty is large, and production efficiency is low.
Through investigation, currently, the U.S. NASA starts the development of a cylinder section integrated forming technology from 2012, and in 2017, the development of a storage box sample with a rib structure with a diameter of phi 200 mm-phi 2800mm is completed, and flight examination is performed on a sounding rocket, and currently, the domestic main processing technology still adopts the traditional tailor-welding process, for example, the storage box cylinder section integrated forming method with grid ribs in the inner cavity disclosed in patent document CN109604966A, and the technology adopts a cylinder blank and then processes grids through a mirror image milling process, so that the problem of large material waste is also existed.
Patent document CN110985239A discloses a near-integrated formed lining-free composite material storage tank structure, which comprises a tank body, an ellipsoidal top cover, a spherical top cover, a butt-joint end frame and a tank bottom cover; the box body comprises a front bottom, an inner cylinder section and a rear bottom, openings for mounting an ellipsoidal top cover and a spherical top cover are arranged on the front bottom and the rear bottom, the ellipsoidal top cover and the spherical top cover are respectively matched and connected with the openings on the front bottom and the rear bottom, and a cover of the box bottom is mounted on the ellipsoidal top cover and the spherical top cover, so that a closed cavity is formed inside the front bottom, the inner cylinder section and the rear bottom and is used for storing media; the storage tank barrel section is formed by co-curing an inner barrel section, a barrel section and an outer barrel section; the butt joint end frame is connected with the two ends of the barrel section and the outer barrel section and is used for butt joint with other structures. However, since the material used in this document is a composite material, it is not suitable for a metal material such as an aluminum alloy.
Disclosure of Invention
Aiming at the defects in the prior art, the invention aims to provide a storage tank barrel section integrated forming method and an integrated storage tank barrel section.
The invention provides a method for integrally forming a storage box barrel section, which comprises the following steps:
step S1: obtaining an original cylinder blank through a blank making process;
step S2: installing a spinning die, installing the original cylinder blank outside the tool, extruding the cylinder blank material into the spinning die by adopting a flow spinning process until the cylinder blank material is attached to the spinning die, and forming a spun cylinder section;
step S3: the integral solid solution aging is adopted for the barrel section after spinning, the material performance of the barrel blank is improved to a T6 state, and meanwhile, the internal structure performance of the barrel blank material is uniform, so that a part is formed;
step S4: the method comprises the following steps of turning and flattening the local depressions on the outer side of a part caused by extrusion through numerical control machining, and ensuring that the final size of a product meets the precision requirement within 1mm of straightness and within 1mm of roundness of the product;
step S5: and (4) unloading the spinning die, taking out the formed part after the return stroke of the spinning wheel, and carrying out nondestructive inspection on the formed part.
Preferably, the step S1 adopts any one of the following:
step S11: adopting a hollow aluminum alloy cast ingot as an original blank, and heating the cast ingot;
step S12: rolling and deforming the heated hollow aluminum alloy cast ingot by using a numerical control ring rolling mill, so that the diameter of the blank is increased to the diameter of a barrel blank of an original barrel blank, the length of the blank is increased to the height of the barrel blank of the original barrel blank, and the blank is in an annealing state;
or
-step S11: rolling and bending the annealed plate into a cylinder by adopting a numerical control roll bending process, wherein the size of the cylinder is equal to the diameter of the original cylinder blank multiplied by the height of the original cylinder blank;
step S12: and welding longitudinal seams on the rolled cylinder blank by adopting a friction stir welding process to obtain a closed cylinder, carrying out nondestructive inspection on the welding seams, and checking that the quality of the welding seams reaches the I-grade welding seam standard.
Preferably, the step S2 includes:
step S21: installing a spinning die with a split structure, sleeving an original cylinder blank into the spinning die, installing the original cylinder blank on a spinning base, starting spinning forming equipment, and feeding a spinning wheel to the original cylinder blank;
step S22: the spinning wheel moves along the axial direction and the normal direction, the original cylinder blank is fed along the axial direction to increase the length of the cylinder blank, and the cylinder blank material is pressed into a groove of a spinning die through feeding along the normal direction;
step S23: after the thinning rate of the barrel blank material is increased to the set thinning rate, carrying out primary stress relief annealing treatment on the original barrel blank;
step S24: continuously carrying out flow spinning forming on the annealed original barrel blank, and extruding and pressing the barrel blank material into a groove of a spinning die;
step S25: and after the height of the spinning rib is increased to the set proportion of the height of the total rib, carrying out secondary stress relief annealing treatment on the original cylinder blank so that the cylinder blank material is attached to the spinning die to form a spinning rear cylinder section.
Preferably, the spinning die in step S2 is of a split structure, so that the rib cylinder section with the grid is disassembled and assembled, and the grid groove matching the height and width of the target rib is processed on the outer surface of the tool in a numerical control manner.
Preferably, the diameter of the original blank is within 1.5mm, and the height of the original blank is within 2 mm.
Preferably, the diameter of the original cylinder blank is 2-3mm larger than that of the tool, and the height of the original cylinder blank is 50-60mm smaller than that of the tool.
Preferably, the annealing heating temperature of the first stress relief annealing treatment and the second stress relief annealing treatment is 350-420 ℃, and the heat preservation time is 2-2.5 h.
Preferably, in the step S3, the whole solution aging adopts the whole water-entering solution of the tool clamping part.
Preferably, in step S4, numerical control machining is performed on the basis of the original spinning die, the spinning wheel is replaced by a numerical control turning tool bit, and the heat-treated part is subjected to overall numerical control machining to remove the outside allowance.
The invention also discloses an integrated storage tank barrel section which is prepared by adopting the integrated forming method of the storage tank barrel section.
Compared with the prior art, the invention has the following beneficial effects:
1. the product reliability is high. The number of longitudinal welding lines of the integral spinning formed cylinder section can be reduced from 4 to 0-1, and the integral forming adopts an integral seamless pipe blank, and the integral spinning forming mode replaces the traditional tailor-welding forming mode, so that the integral seamless forming can be realized, and the reliability of products is effectively improved.
2. The material utilization rate is improved. The material is extruded into the grid by the integrally formed cylinder section in a flow spinning mode, the traditional machining and cutting grid form is replaced, the material utilization rate is improved to over 90% from 10% -30%, and material waste is effectively reduced.
3. The product size precision is high. The flow spinning forming realizes the integral forming of the storage tank barrel section, eliminates the thermal deformation and residual stress generated in the welding process, and reduces the product size precision deviation from 3-4mm in the prior art to about 1 mm.
Drawings
Other features, objects and advantages of the invention will become more apparent upon reading of the detailed description of non-limiting embodiments with reference to the following drawings:
FIG. 1 is a schematic view of a flow-spinning forming method of the present invention;
FIG. 2 is a schematic structural view of a flow-spinning forming apparatus according to the present invention.
The figures show that: a spinning wheel 1; an original barrel blank 2; spinning the mold 3; spinning the base 4.
Detailed Description
The present invention will be described in detail with reference to specific examples. The following examples will assist those skilled in the art in further understanding the invention, but are not intended to limit the invention in any way. It should be noted that it would be obvious to those skilled in the art that various changes and modifications can be made without departing from the spirit of the invention. All falling within the scope of the present invention.
In the description of the present application, it is to be understood that the terms "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience in describing the present application and simplifying the description, but do not indicate or imply that the referred device or element must have a specific orientation, be constructed in a specific orientation, and be operated, and thus, should not be construed as limiting the present application.
Example 1
The invention discloses a storage tank barrel section integrated forming method, which comprises the following steps:
firstly, a blank making process, namely processing an original cylinder blank by adopting a casting ring rolling process; or rolling the flat plate into a barrel blank by adopting a roll welding process, and carrying out nondestructive inspection treatment on the welding seam.
Specifically, the blank making process is divided into two technical schemes:
the first scheme is as follows:
1) adopting a hollow aluminum alloy cast ingot as an original blank, and heating the cast ingot;
2) and (3) rolling and deforming the heated hollow aluminum alloy cast ingot by using a numerical control ring rolling mill, so that the diameter of the blank is increased to a target size phi, the length is increased to H, and the material state is an annealing state.
Scheme II:
1) rolling and bending the plate (the material state is an annealing state) into a cylinder by adopting a numerical control roll bending process, wherein the size of the cylinder is phi multiplied by H (wherein phi represents the diameter of the cylinder blank, and H represents the height of the cylinder blank);
2) and welding longitudinal seams on the rolled cylinder blank by adopting a friction stir welding process to obtain a closed cylinder, carrying out nondestructive inspection (X-ray shooting) on the welding seams, and checking that the quality of the welding seams reaches the I-level welding seam standard.
Specifically, in the step 1) of the scheme I/the scheme II, the roundness of the ring-rolled/rolled cylinder blank is within 1.5mm, and the straightness is within 2 mm. Scheme one step 2) in the ring rolling/roll bending process, the diameter phi of the cylinder blank is relative to the diameter phi of the tool12-3mm large and H relative tool size1The size is 50-60 mm.
The following technical scheme is unified for the scheme one and the scheme two:
3) machining spinning die with the size of phi1×H1Installing the first molded light cylinder outside the tool, and adopting flow spinningThe process extrudes the material into a die; the spinning die is of a split structure, so that the rib cylinder section with the grids can be disassembled and assembled, and grid grooves matched with the height and width of the target ribs are machined on the outer surface of the tool in a numerical control mode.
4) When the material thinning rate in the step 3) is increased to 5%, performing stress relief annealing treatment on the barrel blank; the annealing heating temperature is 350-420 ℃, and the heat preservation time is 2-2.5 h.
5) Continuously carrying out flow spinning forming on the annealed barrel blank, and extruding the material into a grid groove of a die;
6) when the height of the spinning rib is increased to 50% of the height of the total rib, performing stress relief annealing treatment on the barrel blank; the annealing heating temperature is 350-420 ℃, and the heat preservation time is 2-2.5 h.
7) And continuously carrying out flow spinning forming on the annealed barrel blank, and extruding the material into the grid grooves of the die to the attaching die to reach 100% of the total rib height.
In the above 3 to 7, the material is extruded into the grid grooves of the die by adopting the flow spinning process to form the grid structure.
8) The processed parts are subjected to integral heat treatment, and the material performance is improved to a T6 state through integral solid solution aging of the barrel section after spinning, so that the uniformity of the internal structure performance of the material is ensured; the solid solution aging adopts the whole water entering of a tool clamping part to carry out solid solution.
9) And (3) turning and flattening the local depressions on the outer side of the heat-treated part caused by extrusion deformation by adopting numerical control machining, wherein the product size meets the precision requirement of a target value (the straightness is within 1mm, and the product roundness is within 1 mm). The numerical control machining is that on the basis of the original spinning equipment, the spinning wheel is replaced by a numerical control turning tool bit, and the whole numerical control machining is carried out on the heat-treated part to remove the outside allowance.
10) And unloading the spinning die, taking out the formed part after the return stroke of the spinning machine, and carrying out nondestructive inspection (X-ray shooting) on the part.
Through the 10 steps, the integral ring rolling barrel blank/roll welding forming barrel blank is utilized, the integral forming of the storage box barrel section with the rib structure is realized through composite processing modes such as flow spinning forming, integral heat treatment, numerical control precision processing and the like, the existing tailor-welded structural form is replaced, the material utilization rate is greatly improved, the processing efficiency and the size precision of the storage box barrel section are improved, and the integral near-net forming of the storage box barrel section of the carrier rocket is realized.
Example 2
A schematic diagram of a method for integrally forming a tank barrel section as shown in fig. 1, comprising the steps of:
1) processing the blank by the blank making process to obtain an original barrel blank 2;
2) installing a spinning die 3 with a split structure, sleeving an original barrel blank 2 into the spinning die 3, installing the original barrel blank on a spinning base 4, starting spinning forming equipment, and feeding four spinning wheels 1 to the barrel blank;
3) the four spinning wheels 1 move along the axial direction and the normal direction, and the barrel blank is fed along the axial direction so as to increase the length of the barrel blank; feeding along the normal direction so as to press the barrel blank material into the groove of the spinning die 3;
4) when the material thinning rate of the original barrel blank 2 is increased to 5%, the spinning die 3 is dismounted, and the original barrel blank 2 is subjected to stress relief annealing treatment;
5) continuously installing the annealed original barrel blank 2 on a spinning die 3 for flow spinning forming, and extruding the material into grid grooves of the spinning die 3;
6) when the height of the spinning rib is increased to 50% of the height of the total rib, the original cylinder blank 2 is subjected to stress relief annealing treatment;
7) continuously carrying out flow spinning forming on the annealed barrel blank, and extruding the material into a grid groove of a spinning die 3 until the material is attached to the die to reach 100% of the total rib height;
8) the integral solid solution aging is adopted for the spinning rear cylinder section, so that the material performance is improved to a T6 state, and the internal structure performance of the material is uniform;
9) turning and flattening the local depression on the outer side of the part caused by extrusion, and ensuring that the final size of the product meets the precision requirement that the straightness is within 1mm and the roundness of the product is within 1 mm;
10) and (3) unloading the spinning die 3, taking out the formed part after the spinning wheel 1 returns, and carrying out nondestructive inspection (X-ray shooting) on the part.
Example 3
The invention also discloses an integrated storage tank barrel section which is prepared by adopting the integrated forming method of the storage tank barrel section.
The integrated tank segment described in example 3 was formed by the method of integrally forming the tank segment described in example 1 or example 2.
The foregoing description of specific embodiments of the present invention has been presented. It is to be understood that the present invention is not limited to the specific embodiments described above, and that various changes or modifications may be made by one skilled in the art within the scope of the appended claims without departing from the spirit of the invention. The embodiments and features of the embodiments of the present application may be combined with each other arbitrarily without conflict.
Claims (10)
1. A method of integrally forming a tank barrel section, comprising:
step S1: obtaining an original cylinder blank through a blank making process;
step S2: installing a spinning die, installing the original cylinder blank outside the tool, extruding the cylinder blank material into the spinning die by adopting a flow spinning process until the cylinder blank material is attached to the spinning die, and forming a spun cylinder section;
step S3: the integral solid solution aging is adopted for the barrel section after spinning, the material performance of the barrel blank is improved to a T6 state, and meanwhile, the internal structure performance of the barrel blank material is uniform, so that a part is formed;
step S4: turning and flattening the local depression on the outer side of the part caused by extrusion, and ensuring that the final size of the product meets the precision requirement that the straightness is within 1mm and the roundness of the product is within 1 mm;
step S5: and (4) unloading the spinning die, taking out the formed part after the return stroke of the spinning wheel, and carrying out nondestructive inspection on the formed part.
2. The method of integrally forming a tank barrel section according to claim 1, wherein said step S1 employs any one of:
step S11: adopting a hollow aluminum alloy cast ingot as an original blank, and heating the cast ingot;
step S12: rolling and deforming the heated hollow aluminum alloy cast ingot by using a numerical control ring rolling mill, so that the diameter of the blank is increased to the diameter of a barrel blank of an original barrel blank, the length of the blank is increased to the height of the barrel blank of the original barrel blank, and the blank is in an annealing state;
or
-step S11: rolling and bending the annealed plate into a cylinder by adopting a numerical control roll bending process, wherein the size of the cylinder is equal to the diameter of the original cylinder blank multiplied by the height of the original cylinder blank;
step S12: and welding longitudinal seams on the rolled cylinder blank by adopting a friction stir welding process to obtain a closed cylinder, carrying out nondestructive inspection on the welding seams, and checking that the quality of the welding seams reaches the I-grade welding seam standard.
3. The method of integrally forming a tank barrel section according to claim 1, wherein said step S2 includes:
step S21: installing a spinning die with a split structure, sleeving an original cylinder blank into the spinning die, installing the original cylinder blank on a spinning base, starting spinning forming equipment, and feeding a spinning wheel to the original cylinder blank;
step S22: the spinning wheel moves along the axial direction and the normal direction, the original cylinder blank is fed along the axial direction to increase the length of the cylinder blank, and the cylinder blank material is pressed into a groove of a spinning die through feeding along the normal direction;
step S23: after the thinning rate of the barrel blank material is increased to the set thinning rate, carrying out primary stress relief annealing treatment on the original barrel blank;
step S24: continuously carrying out flow spinning forming on the annealed original barrel blank, and extruding and pressing the barrel blank material into a groove of a spinning die;
step S25: and after the height of the spinning rib is increased to the set proportion of the height of the total rib, carrying out secondary stress relief annealing treatment on the original cylinder blank so that the cylinder blank material is attached to the spinning die to form a spinning rear cylinder section.
4. The integrated forming method of the storage tank cylinder section according to claim 1, wherein the spinning die in step S2 adopts a split structure to realize the disassembly and assembly of the cylinder section with the grid rib, and the grid groove matched with the height and width of the target rib is processed on the outer surface of the tool in a numerical control manner.
5. The method of integrally forming a storage tank barrel section according to claim 2, wherein the barrel diameter of the original barrel is within 1.5mm and the barrel height of the original barrel is within 2 mm.
6. The integrated forming method of the storage box barrel section according to claim 2, wherein the diameter of the barrel blank of the original barrel blank is 2-3mm larger than that of the tooling, and the height of the barrel blank of the original barrel blank is 50-60mm smaller than that of the tooling.
7. The integrated forming method of the storage box barrel section as claimed in claim 3, wherein the annealing heating temperature of the first stress relief annealing treatment and the second stress relief annealing treatment is 350-420 ℃, and the holding time is 2-2.5 h.
8. The integrated forming method for the storage box barrel section according to claim 1, wherein the integral solution aging in the step S3 adopts integral water solution of a tool clamping part.
9. The integrated forming method of the storage box barrel section according to claim 1, wherein in step S4, the numerical control machining is adopted on the basis of the spinning die, the spinning wheel is replaced by a numerical control turning tool bit, and the whole numerical control machining is carried out on the heat-treated part to remove the outside allowance.
10. An integrated storage barrel section, characterized in that it is produced by the method of integrated formation of a storage barrel section according to any one of claims 1 to 9.
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| CN113020386A (en) * | 2021-03-01 | 2021-06-25 | 上海交通大学 | Multi-stage external rib cylinder rotary extrusion forming equipment and method |
| CN113083974A (en) * | 2021-03-30 | 2021-07-09 | 武汉理工大学 | Rolling-flexible growth composite forming method for thin-wall grid rib cylinder part |
| CN113547022A (en) * | 2021-06-07 | 2021-10-26 | 浙江蓝箭航天空间科技有限公司 | Thermal punching and spinning composite forming process for bottom of rocket fuel storage tank with large diameter-thickness ratio |
| CN113930590A (en) * | 2021-10-08 | 2022-01-14 | 上海航天精密机械研究所 | Laser-assisted solid solution warm spinning forming method and barrel section with crossed ribs |
| CN114178557A (en) * | 2021-12-29 | 2022-03-15 | 湖北三江航天红阳机电有限公司 | Cylindrical skin processing method |
| CN114589467A (en) * | 2022-03-29 | 2022-06-07 | 成都光明派特贵金属有限公司 | Precious metal multistage reducing channel and manufacturing method thereof |
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Application publication date: 20200922 |