CN115156844A - Machining method for integrally formed box bottom of carrier rocket fuel storage box - Google Patents
Machining method for integrally formed box bottom of carrier rocket fuel storage box Download PDFInfo
- Publication number
- CN115156844A CN115156844A CN202210644246.7A CN202210644246A CN115156844A CN 115156844 A CN115156844 A CN 115156844A CN 202210644246 A CN202210644246 A CN 202210644246A CN 115156844 A CN115156844 A CN 115156844A
- Authority
- CN
- China
- Prior art keywords
- integrally formed
- box bottom
- turning
- carrier rocket
- milling
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
- 238000003754 machining Methods 0.000 title claims abstract description 25
- JTJMJGYZQZDUJJ-UHFFFAOYSA-N phencyclidine Chemical compound C1CCCCN1C1(C=2C=CC=CC=2)CCCCC1 JTJMJGYZQZDUJJ-UHFFFAOYSA-N 0.000 title claims abstract description 23
- 239000002760 rocket fuel Substances 0.000 title claims abstract description 23
- 238000003860 storage Methods 0.000 title claims abstract description 23
- 238000000034 method Methods 0.000 title claims description 26
- 238000003801 milling Methods 0.000 claims abstract description 42
- 238000007514 turning Methods 0.000 claims abstract description 38
- 238000003698 laser cutting Methods 0.000 claims abstract description 19
- 238000005520 cutting process Methods 0.000 claims abstract description 16
- 238000012545 processing Methods 0.000 claims abstract description 15
- 238000013461 design Methods 0.000 claims abstract description 11
- 239000000446 fuel Substances 0.000 claims abstract description 11
- 238000003672 processing method Methods 0.000 claims abstract description 11
- 238000005553 drilling Methods 0.000 claims description 6
- 230000003746 surface roughness Effects 0.000 claims description 4
- 239000007788 liquid Substances 0.000 claims description 3
- 238000004080 punching Methods 0.000 claims description 3
- 238000009987 spinning Methods 0.000 claims description 3
- 230000007704 transition Effects 0.000 claims description 3
- 239000002828 fuel tank Substances 0.000 claims 4
- 238000003466 welding Methods 0.000 description 8
- 239000000463 material Substances 0.000 description 5
- 239000000126 substance Substances 0.000 description 5
- 241000219112 Cucumis Species 0.000 description 4
- 235000015510 Cucumis melo subsp melo Nutrition 0.000 description 4
- FJJCIZWZNKZHII-UHFFFAOYSA-N [4,6-bis(cyanoamino)-1,3,5-triazin-2-yl]cyanamide Chemical compound N#CNC1=NC(NC#N)=NC(NC#N)=N1 FJJCIZWZNKZHII-UHFFFAOYSA-N 0.000 description 4
- 238000005516 engineering process Methods 0.000 description 3
- 230000008569 process Effects 0.000 description 3
- 230000007547 defect Effects 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000007797 corrosion Effects 0.000 description 1
- 238000005260 corrosion Methods 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 238000005259 measurement Methods 0.000 description 1
- 238000001179 sorption measurement Methods 0.000 description 1
- 230000008719 thickening Effects 0.000 description 1
Images
Classifications
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Milling Processes (AREA)
Abstract
The invention provides a processing method for an integrally formed box bottom of a fuel storage box of a carrier rocket, which is characterized by comprising the following steps of: step 1, turning an inner profile: turning an inner profile of the integral box bottom blank on a vertical numerical control lathe by using a turning tool according to a theoretical inner profile equation; step 2, milling the external-shape mirror image: machining an outer molded surface on a five-axis mirror milling machine tool by using a milling cutter according to design requirements; step 3, laser cutting of the outline and the through hole: and cutting the outline and the through hole on a five-axis laser cutting machine according to the design requirement to finally obtain the integral box bottom part. The processing method for the integrally formed box bottom of the carrier rocket fuel storage box disclosed by the invention is used for processing the integrally formed box bottom of the carrier rocket fuel storage box by using a combined processing method of turning, milling and laser cutting, solves the problem of difficulty in processing parts of the box bottom, ensures uniform wall thickness and good surface quality of the integral box bottom, improves the performance and reliability of the integral box bottom, and further can improve the bearing capacity and reliability of the carrier rocket.
Description
Technical Field
The invention relates to the field of numerical control machining, in particular to a machining method for an integrally formed box bottom of a fuel storage box of a carrier rocket.
Background
The tank bottom is an important component of a fuel storage tank of a carrier rocket and is a typical thin-wall, large-size and complex curved surface component. The design profile of the box bottom is a revolution surface of an elliptic first quadrant curve around a short shaft, a plurality of through holes are generally designed for welding with other parts subsequently, and meanwhile, the locally thickened wall thickness is used as a welding influence area, so that the box bottom generally has the characteristics of through holes, thickened areas and the like on the profile surface, and the structure is complex. Due to the complex structure and high quality requirement, the material is one of the most difficult products to be processed in the structural member of the carrier rocket.
The traditional manufacturing process of the bottom of the fuel storage tank of the carrier rocket adopts a mode of forming, chemical milling and tailor welding, firstly, the shape of the melon petal is formed by stretching, then the melon petal which is formed by stretching is thinned by chemical milling, the edge of the melon petal is cut and corrected, and finally, the melon petal is spliced into a circular ring piece by welding. The process method has the problems of low chemical corrosion milling precision, high pollution, more defects, uncontrollable welding seam quality, long working procedure, low reliability and the like, limits the performance and reliability of the box bottom and further directly influences the bearing capacity and reliability of the carrier rocket.
Based on the fact that the traditional chemical milling and tailor welding mode can not meet the increasing requirements of the carrier rocket on manufacturing capability improvement and reliability, the integral forming technology of the box bottom is applied, the integral forming blank parts can be manufactured by the technologies of large-scale curved surface thin-wall part spinning, liquid punching drawing and the like, but the great challenge is met in the surface feature finish machining of the box bottom. The characteristics of a thickened area cannot be freely processed by vertical lathe turning, and the problems of deformation, flutter and the like during thin-wall processing cannot be solved, so that the wall thickness and the surface quality of a product cannot be guaranteed; the problems that the stress is large after the ellipsoidal surface is deformed, the mold is difficult to attach and the like exist in the adsorption processing of the traditional mold, and the wall thickness of a part is difficult to guarantee. Under the situation, the machining mode of internal support and external milling is adopted, and the mirror milling technology of real-time thickness measurement in the cutting process is used as a solution for solving the machining problem of the whole box bottom. However, the mirror milling method is only suitable for machining the outer profile of the tank bottom and is not suitable for machining the inner profile, the flange opening, the appearance profile and other features, so that an overall reliable machining process method is urgently needed to achieve efficient and high-quality machining of the integrally-formed tank bottom of the carrier rocket fuel storage tank.
Disclosure of Invention
In order to solve the defects in the prior art, the invention provides a processing method for an integrally formed box bottom of a fuel storage box of a carrier rocket, which comprises the following steps:
step 1, turning an inner profile: turning an inner profile of the whole box bottom blank on a vertical numerical control lathe by using a turning tool according to a theoretical inner profile equation;
Preferably, the integral box bottom blank is machined by adopting a forming method of liquid punching, deep drawing or spinning, and the blank allowance is required to envelop the final part.
Preferably, in step 1, when the inner profile is turned by using a vertical numerically controlled lathe and a turning tool, the turning track is an ellipsoid equation of the theoretical inner profile, and the turning range extends 50 mm towards the top and the mouth on the basis of the theoretical size of the part.
Preferably, in the step 1, the wall thickness of the integral box bottom part turned by the vertical numerical control lathe is not lower than the theoretical wall thickness at the thinnest position, and the turning surface roughness is superior to Ra1.6.
Preferably, in the step 2, after the inner profile of the box bottom is machined, the outer profile is milled by using mirror milling equipment and an end mill according to the drawing requirements of the part, the characteristics of a thickened area and a thinned area are machined, and the milling range is 15 mm respectively extending towards the top and the mouth on the basis of the theoretical size of the part.
Preferably, in step 2, the thickened area and the thinned area of the integral box bottom are processed according to a transition fillet of 3-5 mm.
Preferably, in step 2, all the through hole features on the box bottom are processed according to the thickened area in the milling process, and the drill is used for drilling holes to mark the center positions of the holes, wherein the drilling depth is 1 mm.
Preferably, a nicking tool is used for marking quadrant lines at positions below the part boundary at the bottom opening of the box bottom and above the part boundary at the top opening, the quadrant lines are 5-10 mm long and 0.1-0.2 mm deep along the longitude direction of the box bottom, and are marked with marks I, II, III and IV respectively.
Preferably, in the step 2, the wall thicknesses of the thickened area and the thinned area after the outer surface of the box bottom is machined meet the requirement of dimensional tolerance, the position of the thickened area meets the requirement of the dimensional tolerance, and the roughness of the milling surface is superior to Ra1.6.
Preferably, in step 3, after the outer surface of the box bottom is machined, the five-axis laser cutting machine is used for cutting the top and bottom profiles according to the design requirements, and cutting the through hole according to the central mark position of the through hole, wherein the axis is perpendicular to the cut normal direction during cutting.
Compared with the prior art, the invention has the following beneficial effects:
1. the machining of the characteristics of the freely distributed thickened area of the integral tank bottom is realized by the machining method of the integral forming tank bottom of the carrier rocket fuel storage tank combining vertical numerical control turning, mirror milling and five-axis laser cutting.
2. The machining method for the integrally-formed bottom of the fuel storage tank of the carrier rocket through combination of vertical numerical control turning, mirror milling and five-axis laser cutting realizes accurate and controllable machining characteristic wall thickness, reduces welding seams and improves machining quality.
3. The machining method for the integrally-formed bottom of the fuel storage tank of the carrier rocket through the combination of vertical numerical control turning, mirror milling and five-axis laser cutting greatly reduces the number of working procedures and improves the machining efficiency.
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 flow diagram of a method of processing an integrally formed case bottom of a carrier rocket fuel tank of the present invention;
FIG. 2 is a schematic view of the bottom parts and blanks of the integrally formed tank of a carrier rocket fuel tank of the present invention;
FIG. 3 is a schematic view of the turning of the inner profile of the parts of the integrally formed bottom of the carrier rocket fuel tank of the present invention;
FIG. 4 is a schematic view of mirror milling of the outer profile of a part of the integrally formed bottom of a carrier rocket fuel tank of the present invention;
FIG. 5 is a schematic view of the contour of the parts and the cutting of the flange hole of the integrally formed bottom of the carrier rocket fuel tank of the present invention.
Description of reference numerals:
Detailed Description
The present invention will be described in detail below with reference to specific embodiments and the accompanying drawings. The following examples will aid those skilled in the art in further understanding the present invention, but are not intended to limit the invention in any manner. 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.
Examples
FIG. 1 is a schematic flow chart of the method for processing the integrally formed bottom of the fuel storage tank of a carrier rocket according to the present invention. The invention provides a processing method of an integrally formed tank bottom of a carrier rocket fuel storage tank, which comprises the following steps as shown in figure 1:
step 1, turning an inner profile: and turning the inner profile of the integral box bottom blank on a vertical numerical control lathe by using a turning tool according to a theoretical inner profile equation.
FIG. 2 is a schematic view of the bottom parts and blanks of the integrally formed tank of a carrier rocket fuel tank of the present invention. As shown in fig. 2, the box bottom blank 3 composed of the blank lower end face 5, the blank inner profile 6 and the blank outer profile 7 should completely cover the whole box bottom part composed of the part theoretical inner profile 8, the part theoretical thinning area outer profile 9, the part theoretical thickening area outer profile 10, the part bottom contour 11 and the whole box bottom part top flange contour 12, and the blank lower end face 5 should exceed the part bottom contour by about 150 mm, so as to facilitate subsequent clamping and processing.
FIG. 3 is a schematic view of the turning of the inner profile of the part of the integrally formed bottom of the carrier rocket fuel tank of the present invention. As shown in fig. 3, a box bottom blank 3 is placed on a rotary worktable of a vertical numerical control lathe in a mode that a large opening faces upwards, the lower end face 5 of the blank is corrected to enable the parallelism of the lower end face and the long axis 1 of a theoretical profile of the box bottom to be not more than 1 mm, meanwhile, the rotation center of a part is corrected according to the inner profile 6 of the blank, and the short axis 2 of the theoretical profile of the box bottom and the short axis of the worktable are basically overlapped, and the difference is not more than 1 mm; turning the inner profile 6 of the blank by using a turning tool 13 according to a theoretical ellipsoid equation, and removing materials 14 from the inner profile; the turning process is carried out in a rough and fine machining mode, a high-rotating-speed and low-feed mode is adopted during fine machining, preferably, when the inner molded surface is turned by using a vertical numerical control lathe and a turning tool, the turning track is an ellipsoid equation of the theoretical inner molded surface, turning is carried out from top to bottom, the turning range is 50 millimeters from the top to the mouth on the basis of the theoretical size of the part, preferably, the wall thickness of the part at the thinnest position of the whole box bottom after turning of the vertical numerical control lathe is not lower than the theoretical wall thickness, and the turning surface roughness is superior to Ra1.6.
FIG. 4 is a schematic view of mirror milling of the outer profile of a part of the integrally formed bottom of a carrier rocket fuel tank of the present invention;
step 2.1, fig. 4 is a schematic diagram of mirror-image milling of an external profile of a part at the bottom of an integrally formed tank of a carrier rocket fuel storage tank, as shown in fig. 4, after the internal profile of the tank is machined, the part is turned over 180 degrees and mounted on a workbench of mirror-image milling equipment, a large opening faces downwards, the external profile is milled according to the requirement of a part drawing by using mirror-image milling equipment and a milling cutter 15, firstly, a thickened area of the external profile is removed, a material 16 is removed, an external profile 10 of a theoretical thickened area is machined, then, a material 17 is removed from a thinned area of the external profile, an internal profile 9 of the theoretical thinned area is machined, a transition fillet of 3-5 mm is machined between the thickened area and the thinned area, and the milling range is that the internal profile extends 15 mm towards the top and the opening on the basis of the theoretical size of the part; preferably, all through hole features on the box bottom are processed according to a thickened area in the milling process, a drill bit is used for drilling holes to mark the center position of the holes, and the drilling depth is 1 mm; the wall thicknesses of the thickened area and the thinned area after the outer surface of the box bottom is machined meet the requirement of dimensional tolerance, the position of the thickened area meets the requirement of the dimensional tolerance, and the milling surface roughness is superior to Ra1.6.
And 2.2, marking quadrant lines at positions below the part boundary at the bottom opening of the box bottom and above the part boundary at the top opening by using a lettering knife, wherein the quadrant lines are 5-10 mm long and 0.1-0.2 mm deep along the longitude direction of the box bottom, and respectively marked with marks I, II, III and IV.
FIG. 5 is a schematic view of the contour of the parts and the cutting of the flange hole of the integrally formed bottom of the carrier rocket fuel tank of the present invention. As shown in fig. 5, the box bottom after the outer profile is processed is mounted on a five-axis laser cutting machine, a five-axis laser cutting machine is used for removing a bottom cutting profile 20 according to a top flange laser cutting profile 18, then removing a bottom cutting removal material 21 according to the bottom cutting profile 20, preferably, a through hole is cut according to a through hole center marking position, an axis is perpendicular to a cut normal during cutting, and finally, an integral box bottom part is obtained.
According to the processing method for the integrally formed bottom of the carrier rocket fuel storage tank provided by the invention, the processing of the characteristics of the freely distributed thickened area of the integral bottom is realized by the processing method for the integrally formed bottom of the carrier rocket fuel storage tank, which combines vertical numerical control turning, mirror milling and five-axis laser cutting. In addition, compared with the chemical milling and welding, the method has the advantages of high processing precision, environmental friendliness, no pollution, excellent surface quality, good reliability and strong pressure bearing capacity.
The processing method for the integrally formed box bottom of the carrier rocket fuel storage box disclosed by the invention processes the integrally formed box bottom of the carrier rocket fuel storage box by using a combined processing method of turning, milling and laser cutting, solves the problem of processing parts of the box bottom, ensures uniform wall thickness and good surface quality of the integral box bottom, improves the performance and reliability of the integral box bottom, and further can improve the bearing capacity and reliability of a carrier rocket.
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 processing method for an integrally formed box bottom of a fuel storage box of a carrier rocket is characterized by comprising the following steps:
step 1, turning an inner profile: turning an inner profile of the integral box bottom blank on a vertical numerical control lathe by using a turning tool according to a theoretical inner profile equation;
step 2, milling the external-shape mirror image: machining an outer molded surface on a five-axis mirror milling machine tool by using a milling cutter according to design requirements;
and 3, laser cutting of the contour and the through hole: and cutting the top and bottom contour and the through hole on a five-axis laser cutting machine according to the design requirements, and finally obtaining the integral box bottom part.
2. The method for processing the integrally formed bottom of a fuel tank for a launch vehicle according to claim 1, wherein the blank for the integrally formed bottom is an integrally formed bottom processed by a forming method of liquid punching, deep drawing or spinning, and the blank is required to have a margin to envelop final parts.
3. The method for processing the integrally formed bottom of the fuel tank of a launch vehicle according to claim 2, wherein in step 1, when the inner profile is turned by using a vertical numerically controlled lathe and a turning tool, the turning locus is an ellipsoid equation of the theoretical inner profile, and the turning range is 50 mm extending to the top and the bottom respectively on the basis of the theoretical size of the part.
4. The processing method for the integrally formed bottom of the fuel storage tank of the carrier rocket as recited in claim 3, wherein in step 1, the wall thickness of the part of the integrally formed bottom at the thinnest position of the part of the integrally formed bottom, which is turned by the vertical numerically controlled lathe, is not lower than the theoretical wall thickness, and the turning surface roughness is superior to Ra1.6.
5. The method for processing the integrally formed bottom of the fuel tank of a carrier rocket according to claim 4, wherein in the step 2, after the inner profile of the bottom of the tank is processed, the outer profile is milled by using mirror milling equipment and an end mill according to the drawing requirements of parts, the characteristics of a thickened area and a thinned area are processed, and the milling range is 15 mm respectively extending towards the top and the mouth on the basis of the theoretical size of the parts.
6. The method of claim 5, wherein in step 2, the thickened area and the thinned area of the integral bottom are machined with 3-5 mm transition fillets therebetween.
7. The method for machining the integrally formed bottom of the fuel tank of a launch vehicle according to claim 6, wherein in step 2, all through hole features on the bottom of the tank are machined according to a thickened area in a milling process, and a drill is used for drilling holes to indicate the center position of the holes, wherein the drilling depth is 1 mm.
8. The method of forming a case bottom integrally with a vehicle rocket fuel tank as recited in claim 7, wherein in step 2, further comprising: marking quadrant lines at positions below the part boundary of the bottom opening of the box bottom and above the part boundary of the top opening by using a lettering knife, wherein the quadrant lines have the length of 5-10 mm and the depth of 0.1-0.2 mm along the longitude line direction of the box bottom, and are marked with marks I, II, III and IV respectively.
9. The method for processing the integrally formed bottom of the fuel storage tank of a carrier rocket as recited in claim 8, wherein in step 2, the wall thickness of the thickened area and the wall thickness of the thinned area after the outer surface of the bottom of the tank is processed meet the requirement of dimensional tolerance, the position of the thickened area meets the requirement of dimensional tolerance, and the roughness of the milled surface is better than Ra1.6.
10. The method for processing the bottom of the integrally formed tank for a carrier rocket fuel tank according to claim 9, wherein in step 3, after the outer surface of the tank bottom is processed, a five-axis laser cutting machine is used for cutting the top and bottom contours according to the design requirement, and cutting the through hole according to the marked position of the center of the through hole, wherein the axis is perpendicular to the normal direction of the cut position.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210644246.7A CN115156844B (en) | 2022-06-08 | 2022-06-08 | Processing method for integrally formed tank bottom of carrier rocket fuel tank |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210644246.7A CN115156844B (en) | 2022-06-08 | 2022-06-08 | Processing method for integrally formed tank bottom of carrier rocket fuel tank |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN115156844A true CN115156844A (en) | 2022-10-11 |
| CN115156844B CN115156844B (en) | 2024-01-12 |
Family
ID=83485862
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210644246.7A Active CN115156844B (en) | 2022-06-08 | 2022-06-08 | Processing method for integrally formed tank bottom of carrier rocket fuel tank |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN115156844B (en) |
Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE19919777A1 (en) * | 1998-10-24 | 2000-07-13 | Sms Demag Ag | Broad side plate for continuous casting mould, used especially for thin slab or steel strip casting, is produced by smooth rolling and surface hardening of a machined copper alloy plate |
| US20080121078A1 (en) * | 2006-11-24 | 2008-05-29 | Towa Corporation | Method of and apparatus for working structure |
| CN103203591A (en) * | 2012-01-13 | 2013-07-17 | 中国国际海运集装箱(集团)股份有限公司 | Method for manufacturing container underframe |
| CN105772812A (en) * | 2016-04-21 | 2016-07-20 | 上海航天设备制造总厂 | Method for five-axis mirror milling numerical control machining of integrally-formed tank bottom |
| CN106925962A (en) * | 2017-05-03 | 2017-07-07 | 昆山广巨精密五金有限公司 | A kind of auto parts and components production method |
| CN107745029A (en) * | 2017-11-10 | 2018-03-02 | 上海航天设备制造总厂 | A kind of store-vessel bottom integral forming method |
| CN113319300A (en) * | 2021-04-26 | 2021-08-31 | 浙江蓝箭航天空间科技有限公司 | Method for forming integral circular ring at bottom of rocket tank |
| 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 |
| CN113751731A (en) * | 2021-08-31 | 2021-12-07 | 浙江蓝箭航天空间科技有限公司 | Inner-type turning process for bottom of rocket tank |
-
2022
- 2022-06-08 CN CN202210644246.7A patent/CN115156844B/en active Active
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE19919777A1 (en) * | 1998-10-24 | 2000-07-13 | Sms Demag Ag | Broad side plate for continuous casting mould, used especially for thin slab or steel strip casting, is produced by smooth rolling and surface hardening of a machined copper alloy plate |
| US20080121078A1 (en) * | 2006-11-24 | 2008-05-29 | Towa Corporation | Method of and apparatus for working structure |
| CN103203591A (en) * | 2012-01-13 | 2013-07-17 | 中国国际海运集装箱(集团)股份有限公司 | Method for manufacturing container underframe |
| CN105772812A (en) * | 2016-04-21 | 2016-07-20 | 上海航天设备制造总厂 | Method for five-axis mirror milling numerical control machining of integrally-formed tank bottom |
| CN106925962A (en) * | 2017-05-03 | 2017-07-07 | 昆山广巨精密五金有限公司 | A kind of auto parts and components production method |
| CN107745029A (en) * | 2017-11-10 | 2018-03-02 | 上海航天设备制造总厂 | A kind of store-vessel bottom integral forming method |
| CN113319300A (en) * | 2021-04-26 | 2021-08-31 | 浙江蓝箭航天空间科技有限公司 | Method for forming integral circular ring at bottom of rocket tank |
| 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 |
| CN113751731A (en) * | 2021-08-31 | 2021-12-07 | 浙江蓝箭航天空间科技有限公司 | Inner-type turning process for bottom of rocket tank |
Non-Patent Citations (1)
| Title |
|---|
| 机械工业部机械基础装备公司等: "国产数控机床选用指南", 机械工业出版社, pages: 125 - 129 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN115156844B (en) | 2024-01-12 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN105382313A (en) | Machining method for numerical control milling of thin-wall curved-surface irregular parts | |
| CN109483262B (en) | Die and method for machining inner ring of engine spindle bearing with inner-diameter oil groove | |
| WO2006043444A1 (en) | Machined cage for cylindrical roller bearing and method of manufacturing the same | |
| CN111001861B (en) | Numerical control machining method for cavity in large aluminum alloy skirt body | |
| CN106695248B (en) | The manufacturing method of cylinder cover for diesel engine | |
| CN105904154B (en) | A kind of new energy electric automobile motor inner casing body processing technology | |
| CN101200035A (en) | Processing method of end face open asymmetric width positioning slot extra thin wall bearing ring chamfer | |
| CN114589461B (en) | Numerical control machining process for ventilation window frame parts | |
| CN112496134B (en) | Spinning method of curved surface thin-wall end socket with flanging hole | |
| CN115156844B (en) | Processing method for integrally formed tank bottom of carrier rocket fuel tank | |
| CN112935715B (en) | Machining manufacturing method for airplane wheel hub | |
| CN106077775B (en) | A kind of processing method of three axis machine tooling back-off class workpiece | |
| CN110449648B (en) | Cutter and method for machining eccentric shaft clearance groove | |
| CN105058101B (en) | Variable-pitch airscrew propeller hub fixture peculiar to vessel | |
| CN202517512U (en) | Cutter for processing slant-ended rubber-plastic sealing ring | |
| CN112091292B (en) | Allowance hole reaming method | |
| CN112453837B (en) | Processing method of valve seat | |
| CN218050411U (en) | Precision boring device for part production | |
| CN204748112U (en) | A mould that is used for two holders of partly riveting of ball bearing to process | |
| CN221018708U (en) | Cutter for ball pit machining | |
| CN113385706B (en) | Method for machining regular polygon inner hole | |
| CN220805596U (en) | Boring cutter suitable for step hole | |
| CN116275887A (en) | Large splayed blind plate production process | |
| CN115122049B (en) | Melon petal chemical milling template processing and positioning method thereof | |
| CN212350495U (en) | Deep hole flat bottom gun drill |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |