CN111375690A - Hot press forming method for titanium alloy variable-curvature bidirectional stress structure sheet metal part - Google Patents
Hot press forming method for titanium alloy variable-curvature bidirectional stress structure sheet metal part Download PDFInfo
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- CN111375690A CN111375690A CN201811611409.1A CN201811611409A CN111375690A CN 111375690 A CN111375690 A CN 111375690A CN 201811611409 A CN201811611409 A CN 201811611409A CN 111375690 A CN111375690 A CN 111375690A
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- connecting section
- titanium alloy
- sheet metal
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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
- B21D37/00—Tools as parts of machines covered by this subclass
- B21D37/16—Heating or cooling
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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
- B21D22/02—Stamping using rigid devices or tools
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- Mechanical Engineering (AREA)
- Shaping Metal By Deep-Drawing, Or The Like (AREA)
- Forging (AREA)
Abstract
The invention provides a hot press forming method of a titanium alloy variable-curvature bidirectional stress structure sheet metal part, belongs to the technical field of hot press forming, and particularly relates to a hot press forming method of a titanium alloy variable-curvature bidirectional stress structure sheet metal part. The problems that the sheet material is torn and wrinkled and the thinning rate is controlled when the existing titanium alloy sheet metal part is formed are solved. It adopts step-by-step hot-press forming method, and before the final molded surface is hot-pressed, the transition molded surface is added. The hot-press forming method is mainly used for hot-press forming of the titanium alloy variable-curvature bidirectional stress structure sheet metal part.
Description
Technical Field
The invention belongs to the technical field of hot press forming, and particularly relates to a hot press forming method of a titanium alloy variable-curvature bidirectional stress structure sheet metal part.
Background
With the development of aerospace manufacturing industry, the structural material for the aircraft body is mainly characterized in that a large amount of light, high-strength and high-modulus materials with high specific strength and high specific modulus are adopted, so that the structural efficiency of the aircraft is improved, and the structural weight coefficient of the aircraft is reduced. In particular, the use amounts of the composite material and the titanium alloy are increased, and the use amounts of the traditional structural steel and the aluminum alloy are correspondingly reduced.
The titanium alloy is widely applied to the field of aerospace by the characteristics of high temperature resistance, small density, high specific strength and the like, wherein the proportion of parts of the titanium alloy sheet metal component is very large. At present, there are various methods for forming sheet metal parts, such as: the hot-press forming process has the advantages of high forming efficiency, short forming period, low material shearing rate and the like, and the hot-press forming process has outstanding advantages in batch production.
The titanium alloy sheet metal part is formed to face the problems of sheet tearing, wrinkling, thinning rate control and the like, and the forming effect of the final part depends on a hot-press forming process method. Part of sheet metal parts cannot meet the requirements due to one-step forming of the shape characteristics of the sheet metal parts, and the final shape can be obtained only by forming twice or more. For some parts which cannot be molded at one time, the key to the success of the process method is how to reasonably select the transition profile, reduce the molding times as much as possible and reduce the investment cost of the mold.
Disclosure of Invention
The invention provides a hot press forming method of a titanium alloy variable-curvature bidirectional stress structure sheet metal part, aiming at solving the problems in the prior art.
In order to achieve the purpose, the invention adopts the following technical scheme: the hot press forming method of the titanium alloy variable-curvature bidirectional stress structure sheet metal part comprises a first connecting section and a second connecting section, and is characterized in that: and adding a transition profile before hot-pressing the final profile by adopting a step-by-step hot press forming method, wherein the size of the transition profile of the first connecting section is the same as that of the final profile of the first connecting section, the height of the transition profile of the second connecting section is lower than that of the final profile of the second connecting section, the width of the transition profile of the second connecting section is the same as that of the final profile of the second connecting section, a transition area is arranged at the joint of the first connecting section and the second connecting section, and the transition profile is hot-pressed again to form the final profile of the titanium alloy variable-curvature bidirectional stress structure sheet metal part.
Furthermore, the transition area arranged at the joint of the first connecting section and the second connecting section is a fillet transition area.
Furthermore, the first connecting section is a straight cylinder section, and the second connecting section is a flaring section.
Compared with the prior art, the invention has the beneficial effects that: the invention can effectively avoid the defect that the titanium alloy variable-curvature bidirectional stress structure sheet metal part generates wrinkles after being formed. By adopting a step-by-step forming method, a transition profile is added before the final shape is formed by hot pressing, the profile can effectively avoid the wrinkle defect in one-step forming, the shearing thin rate of the finally formed part is extremely low, and the design requirement of the product is met. The plate can flow to the process end, the wrinkle defect of parts is avoided, the hot press forming times are reduced to the maximum extent, and the die input cost is reduced. In addition, the angle of the molded surface is adjusted, so that the front and rear heights of the molded surface are the same, and the phenomena that the mold moves due to the action of lateral force and the molded surface is not closed tightly are avoided.
Drawings
FIG. 1 is a schematic view of an elevational structure of a titanium alloy variable-curvature bidirectional stress structure sheet metal part
FIG. 2 is a schematic view of a top view structure of a titanium alloy sheet metal part with a variable curvature bidirectional stress structure according to the present invention
FIG. 3 is a schematic view of an elevational structure of a transition profile of a titanium alloy variable-curvature bidirectional stress structure sheet metal part
FIG. 4 is a schematic view of a top view structure of a transition profile of a titanium alloy variable-curvature bidirectional stress structure sheet metal part
FIG. 5 is a schematic view of the final profile of the sheet metal part with a variable-curvature bidirectional stress structure made of titanium alloy according to the present invention
FIG. 6 is a schematic view of the top view structure of the final molded surface of the titanium alloy sheet metal part with variable curvature bi-directional stress structure
1-transition region
Detailed Description
The technical solution in the embodiments of the present invention will be clearly and completely explained below with reference to the drawings in the embodiments of the present invention.
Referring to fig. 1 to 6, the embodiment is described, which is a method for hot press forming of a titanium alloy variable-curvature bidirectional stress structure sheet metal part, the titanium alloy variable-curvature bidirectional stress structure sheet metal part includes a first connecting section and a second connecting section, a transition profile is added before a final profile is hot pressed by a step-by-step hot press forming method, the size of the transition profile of the first connecting section is the same as the size of the final profile of the first connecting section, the height of the transition profile of the second connecting section is lower than the height of the final profile of the second connecting section, the width of the transition profile of the second connecting section is the same as the width of the final profile of the second connecting section, a transition area is arranged at the joint of the first connecting section and the second connecting section, and the transition profile is hot press formed again to form the final profile of the titanium alloy variable-.
As shown in fig. 1-2, the flaming device applied to the tail of the missile is adopted in the embodiment for explanation, the structure is a typical representative of a titanium alloy variable-curvature bidirectional stress structure sheet metal part, and comprises a flaring section and a straight cylinder section, the flaring section and the straight cylinder section cannot be formed separately and then welded, the part is required to be formed integrally, and the transition fillet at the connecting part of the flaring section and the straight cylinder section cannot be too large and needs a remarkable folding line. The part material is titanium alloy plate, and the forming process method is hot press forming. The structure of the part leads the part to be easy to generate wrinkles in the plate material accumulation in the transition area of the straight cylinder section and the flaring section in the hot press forming process. In actual production, through multiple times of simulation analysis and actual verification, qualified molded surfaces cannot be hot-pressed for one time, so that hot-press forming is required for two times or more, transition molded surfaces are added, and the selection of the transition molded surfaces is the key of success or failure. The method can successfully obtain qualified parts, reduces the hot-press forming times to the maximum extent and reduces the investment cost of the die.
As shown in fig. 3-6, the transition profile is characterized in that the straight cylinder section has the same actual size as the part, the height of the flared section in the front view direction is lower than the height of the part, the width in the front view direction is the same as the actual width of the part, and the fillet is added in the transition area. In addition, the angle of the molded surface is adjusted, so that the front and rear heights of the molded surface are the same, and the phenomena that the mold moves due to the action of lateral force and the molded surface is not closed tightly are avoided.
The hot press forming method of the titanium alloy variable-curvature bidirectional stress structure sheet metal part provided by the invention is described in detail, a specific example is applied in the text to explain the principle and the implementation mode of the invention, and the description of the embodiment is only used for helping to understand the method and the core idea of the invention; meanwhile, for a person skilled in the art, according to the idea of the present invention, there may be variations in the specific embodiments and the application scope, and in summary, the content of the present specification should not be construed as a limitation to the present invention.
Claims (3)
1. The hot press forming method of the titanium alloy variable-curvature bidirectional stress structure sheet metal part comprises a first connecting section and a second connecting section, and is characterized in that: and adding a transition profile before hot-pressing the final profile by adopting a step-by-step hot press forming method, wherein the size of the transition profile of the first connecting section is the same as that of the final profile of the first connecting section, the height of the transition profile of the second connecting section is lower than that of the final profile of the second connecting section, the width of the transition profile of the second connecting section is the same as that of the final profile of the second connecting section, a transition area is arranged at the joint of the first connecting section and the second connecting section, and the transition profile is hot-pressed again to form the final profile of the titanium alloy variable-curvature bidirectional stress structure sheet metal part.
2. The hot press forming method of the titanium alloy variable-curvature bidirectional stress structure sheet metal part according to claim 1, characterized in that: the transition area arranged at the joint of the first connecting section and the second connecting section is a fillet transition area.
3. The hot press forming method of the titanium alloy variable-curvature bidirectional stress structure sheet metal part according to claim 1, characterized in that: the first connecting section is a straight cylinder section, and the second connecting section is an opening expanding section.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811611409.1A CN111375690B (en) | 2018-12-27 | 2018-12-27 | Hot press forming method for titanium alloy variable-curvature bidirectional stress structure sheet metal part |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811611409.1A CN111375690B (en) | 2018-12-27 | 2018-12-27 | Hot press forming method for titanium alloy variable-curvature bidirectional stress structure sheet metal part |
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| Publication Number | Publication Date |
|---|---|
| CN111375690A true CN111375690A (en) | 2020-07-07 |
| CN111375690B CN111375690B (en) | 2022-04-12 |
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| CN201811611409.1A Active CN111375690B (en) | 2018-12-27 | 2018-12-27 | Hot press forming method for titanium alloy variable-curvature bidirectional stress structure sheet metal part |
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Citations (9)
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|---|---|---|---|---|
| US2956334A (en) * | 1958-06-30 | 1960-10-18 | American Welding Mfg Co | Method of making rocket nozzles |
| GB937695A (en) * | 1961-12-22 | 1963-09-25 | Ludwig Bolkow | Process for the manufacture of liquid cooled combustion chambers for rockets |
| US3597821A (en) * | 1968-08-09 | 1971-08-10 | Rohr Corp | Method of making an integrated match machining rocket nozzle |
| US4942653A (en) * | 1989-08-25 | 1990-07-24 | Rockwell International Corporation | Production method for a channeled wall thrust nozzle |
| US5701670A (en) * | 1994-06-23 | 1997-12-30 | Boeing North American, Inc. | Method of making rocket engine combustion chamber utilizing "slide in" port liner |
| WO2002018772A1 (en) * | 2000-09-02 | 2002-03-07 | Astrium Gmbh | Segmented rocket drive and method for producing the same |
| CN102717461A (en) * | 2012-06-27 | 2012-10-10 | 晋西工业集团有限责任公司 | Overall compression molding mold for rocket ammunition jet pipe with support lugs |
| CN103920752A (en) * | 2014-04-03 | 2014-07-16 | 北京星航机电装备有限公司 | Sectioning thermal expansion shape correcting method for special-shaped variable-cross-section titanium alloy tube parts |
| CN105268801A (en) * | 2014-07-18 | 2016-01-27 | 周子童 | Hot-pressing method |
-
2018
- 2018-12-27 CN CN201811611409.1A patent/CN111375690B/en active Active
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2956334A (en) * | 1958-06-30 | 1960-10-18 | American Welding Mfg Co | Method of making rocket nozzles |
| GB937695A (en) * | 1961-12-22 | 1963-09-25 | Ludwig Bolkow | Process for the manufacture of liquid cooled combustion chambers for rockets |
| US3597821A (en) * | 1968-08-09 | 1971-08-10 | Rohr Corp | Method of making an integrated match machining rocket nozzle |
| US4942653A (en) * | 1989-08-25 | 1990-07-24 | Rockwell International Corporation | Production method for a channeled wall thrust nozzle |
| US5701670A (en) * | 1994-06-23 | 1997-12-30 | Boeing North American, Inc. | Method of making rocket engine combustion chamber utilizing "slide in" port liner |
| WO2002018772A1 (en) * | 2000-09-02 | 2002-03-07 | Astrium Gmbh | Segmented rocket drive and method for producing the same |
| CN102717461A (en) * | 2012-06-27 | 2012-10-10 | 晋西工业集团有限责任公司 | Overall compression molding mold for rocket ammunition jet pipe with support lugs |
| CN103920752A (en) * | 2014-04-03 | 2014-07-16 | 北京星航机电装备有限公司 | Sectioning thermal expansion shape correcting method for special-shaped variable-cross-section titanium alloy tube parts |
| CN105268801A (en) * | 2014-07-18 | 2016-01-27 | 周子童 | Hot-pressing method |
Non-Patent Citations (1)
| Title |
|---|
| 戚正风等: "固体火箭发动机喷管喉衬材料的分段设计 ", 《炭素》 * |
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| CN111375690B (en) | 2022-04-12 |
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