CN106738936A - A kind of thermoplastic composite forming method - Google Patents
A kind of thermoplastic composite forming method Download PDFInfo
- Publication number
- CN106738936A CN106738936A CN201611055664.3A CN201611055664A CN106738936A CN 106738936 A CN106738936 A CN 106738936A CN 201611055664 A CN201611055664 A CN 201611055664A CN 106738936 A CN106738936 A CN 106738936A
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- China
- Prior art keywords
- embedded part
- metal embedded
- cross
- paxilla
- thermoplastic composite
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C65/00—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor
- B29C65/02—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor by heating, with or without pressure
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
Abstract
A kind of thermoplastic composite forming method of the present invention belongs to guided missile test technical field.Present invention design simultaneously manufactures metal embedded part, the metal embedded part for machining is placed in the preform of thermoplastic composite airframe structure part, Positioning screw in composite material shaping mould is screwed in the screwed hole of metal embedded part, is positioned with to metal embedded part；Temperature-pressure is carried out by composite material shaping mould, metal embedded part and thermoplastic composite airframe structure part are cured as entirety.Thermoplastic composite uses this kind of pre-embedding metal part structure type, can be used for some important connecting portions, it is ensured that the transmission of big load, improves the safe handling of composite.
Description
Technical field
A kind of thermoplastic composite forming method of the present invention belongs to technical field of composite material molding.
Background technology
In current new technology revolution, material, the energy and information are described as three big pillars of modern civilization.Aircraft material
Material is that aircraft meets every tactics, technical requirements, realizes basis and the premise of the purpose of operation and requirement.With material science
Progressive, various new materials are widely applied onto sophisticated missile, are that the development and production of advanced aircraft are laid a good foundation.
There is thermoplastic composite excellent shock resistance, low-density to be increasingly taken seriously, and apply model
Enclose and main load-bearing part is gradually turned to by secondary bearing member, therefore, the connection design for carrying position is particularly important, particularly the wing
Face and the connection of fuselage.General composite mainly carries position to solve connectivity problem, generally designs metal at this position
Frame is used for ensureing the machining accuracy and bonding strength of connecting portion, and this structure type construction weight is relatively heavy, installation time
It is more long, it is relatively costly.
The content of the invention
The purpose of the present invention：A kind of thermoplastic composite forming method is provided, the connection at primary load bearing position and big is solved
The transmission of load, while mitigating construction weight, reduces assembly cost.
Technical scheme：
A kind of thermoplastic composite forming method, the described method comprises the following steps；
1) design and manufacture metal embedded part 1, metal embedded part 1 by the cylinder of two varying cross-sections it is coaxially connected and
Into wherein the less cylinder of cross-sectional area is paxilla, and the larger cylinder of cross-sectional area is big cylinder, in the paxilla
A bottom surface on along the paxilla axially arranged tapped blind hole, the internal thread of the tapped blind hole and composite shaping mould
The external screw thread of the Positioning screw in tool matches, and another bottom surface of the paxilla is connected with a bottom surface of big cylinder；
2) step 1) in the metal embedded part 1 that machines be placed on the pre- of thermoplastic composite airframe structure part 2
In formed body, the Positioning screw 3 in composite material shaping mould 4 is screwed in the screwed hole of metal embedded part, with pre- to metal
Embedded part 1 is positioned；
3) temperature-pressure is carried out by composite material shaping mould 4, by metal embedded part 1 and thermoplastic composite machine
Body structure part 2 is cured as entirety.
The cross section of the paxilla of the metal embedded part 1 is polygon.
The cross section of the big cylinder of the metal embedded part 1 is polygon.
The cross section of the paxilla of the metal embedded part 1 is hexagon.
The cross section of the big cylinder of the metal embedded part 1 is hexagon.
The beneficial effect of the invention：The structure type of metal embedded part 1 that the inventive method is used, increased and thermoplastic composite
The contact area of material structure part 2, while reducing big load to the crushing strength of composite material element, can be used for fuel tank and mainly connects
Position, it is ensured that Oiltank structure is fully sealed.
Brief description of the drawings
Fig. 1 metal embedded part structural representations
Fig. 2 thermoplastic composite forming method schematic diagrames
The large and small cylinder cross-sectional views one of Fig. 3
The large and small cylinder cross-sectional views two of Fig. 4
The large and small cylinder polygon schematic diagrames one of Fig. 5
The large and small cylinder polygon schematic diagrames two of Fig. 6
1- pre-embedding metal part 2- thermoplastic composite airframe structure part 3- Positioning screw 4- moulds
Specific embodiment
With reference to Figure of description, the present invention will be described in detail.
A kind of thermoplastic composite forming method, the described method comprises the following steps；
1) design and manufacture metal embedded part 1, metal embedded part 1 by the cylinder of two varying cross-sections it is coaxially connected and
Into wherein the less cylinder of cross-sectional area is paxilla, and the larger cylinder of cross-sectional area is big cylinder, in the paxilla
A bottom surface on along the paxilla axially arranged tapped blind hole, the internal thread of the tapped blind hole and composite shaping mould
The external screw thread of the Positioning screw in tool matches, and another bottom surface of the paxilla is connected with a bottom surface of big cylinder；
2) step 1) in the metal embedded part 1 that machines be placed on the pre- of thermoplastic composite airframe structure part 2
In formed body, the Positioning screw in composite material shaping mould is screwed in the screwed hole of metal embedded part, with pre-buried to metal
Part is positioned；
3) temperature-pressure is carried out by composite material shaping mould, by metal embedded part 1 and thermoplastic composite machine
Body structure part 2 is cured as entirety.
The cross section of the paxilla of the metal embedded part 1 is polygon.
The cross section of the big cylinder of the metal embedded part 1 is polygon.
The cross section of the paxilla of the metal embedded part 1 is hexagon.
The cross section of the big cylinder of the metal embedded part 1 is hexagon.
Embodiment one
Paxilla can design circular, and big cylinder is designed to pentagon, as shown in Figure 3；Paxilla can also be designed to
Pentagon, big cylinder is designed to cylinder, as shown in Figure 4.
Embodiment two
It is as shown in Figure 5 that paxilla and big cylinder design quadrangularly simultaneously；Paxilla and big cylinder are designed to seven sides simultaneously
Shape, as shown in Figure 6.
Claims (5)
1. a kind of thermoplastic composite forming method, it is characterised in that the described method comprises the following steps；
1) design and manufacture metal embedded part (1), metal embedded part (1) by the cylinder of two varying cross-sections it is coaxially connected and
Into wherein the less cylinder of cross-sectional area is paxilla, and the larger cylinder of cross-sectional area is big cylinder, in the paxilla
A bottom surface on along the paxilla axially arranged tapped blind hole, the internal thread of the tapped blind hole and composite shaping mould
The external screw thread of the Positioning screw in tool matches, and another bottom surface of the paxilla is connected with a bottom surface of big cylinder；
2) step 1) in the metal embedded part (1) that machines be placed on the pre- of thermoplastic composite airframe structure part (2)
In formed body, the Positioning screw in composite material shaping mould is screwed in the screwed hole of metal embedded part, with pre-buried to metal
Part is positioned；
3) temperature-pressure is carried out by composite material shaping mould, by metal embedded part (1) and thermoplastic composite fuselage
Structural member (2) is cured as entirety.
2. the method that a kind of solution target simulator complex target according to claim 1 and background model flash, it is special
Levy and be, the cross section of the paxilla of the metal embedded part (1) is polygon.
3. the method that a kind of solution target simulator complex target according to claim 1 and 2 and background model flash, its
It is characterised by, the cross section of the big cylinder of the metal embedded part (1) is polygon.
4. the method that a kind of solution target simulator complex target according to claim 2 and background model flash, it is special
Levy and be, the cross section of the paxilla of the metal embedded part (1) is hexagon.
5. the method that a kind of solution target simulator complex target according to claim 3 and background model flash, it is special
Levy and be, the cross section of the big cylinder of the metal embedded part (1) is hexagon.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611055664.3A CN106738936A (en) | 2016-11-25 | 2016-11-25 | A kind of thermoplastic composite forming method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611055664.3A CN106738936A (en) | 2016-11-25 | 2016-11-25 | A kind of thermoplastic composite forming method |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106738936A true CN106738936A (en) | 2017-05-31 |
Family
ID=58910737
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201611055664.3A Pending CN106738936A (en) | 2016-11-25 | 2016-11-25 | A kind of thermoplastic composite forming method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106738936A (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109236823A (en) * | 2018-10-10 | 2019-01-18 | 迪皮埃复材构件（太仓）有限公司 | A kind of strong magnetic metal embedded part for composite inner |
| CN109514890A (en) * | 2018-10-10 | 2019-03-26 | 迪皮埃复材构件（太仓）有限公司 | A kind of production method of composite material mould vacuum port |
| EP3569828A1 (en) * | 2018-05-09 | 2019-11-20 | Safran Aero Boosters S.A. | Overmoulding metal insert for locally reinforcing a moulded part of an aircraft engine |
| CN111497277A (en) * | 2020-04-20 | 2020-08-07 | 上海伽材新材料科技有限公司 | Accurate positioning structure and method for composite metal embedded part |
| CN112013004A (en) * | 2020-08-14 | 2020-12-01 | 湖北航天技术研究院总体设计所 | Connecting structure of composite material joint |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN102166824A (en) * | 2010-12-29 | 2011-08-31 | 江西昌河航空工业有限公司 | Method for positioning composite material metal insert |
| EP2474712A2 (en) * | 2011-01-07 | 2012-07-11 | United Technologies Corporation | Attachment of threaded holes to composite fan case |
| CN103003059A (en) * | 2010-07-02 | 2013-03-27 | 兰博基尼汽车公开有限公司 | Process, mould, devices and kit for manufacturing products made of composite materials, as well as products manufactured with this process and/or with these means |
| CN204003905U (en) * | 2014-04-09 | 2014-12-10 | 中国兵器工业集团第五三研究所 | A kind of threaded insert |
| CN204800906U (en) * | 2015-07-21 | 2015-11-25 | 宁波沥高复合材料有限公司 | Location built -in fitting that aerospace combined material mould was used |
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2016
- 2016-11-25 CN CN201611055664.3A patent/CN106738936A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN103003059A (en) * | 2010-07-02 | 2013-03-27 | 兰博基尼汽车公开有限公司 | Process, mould, devices and kit for manufacturing products made of composite materials, as well as products manufactured with this process and/or with these means |
| CN102166824A (en) * | 2010-12-29 | 2011-08-31 | 江西昌河航空工业有限公司 | Method for positioning composite material metal insert |
| EP2474712A2 (en) * | 2011-01-07 | 2012-07-11 | United Technologies Corporation | Attachment of threaded holes to composite fan case |
| CN204003905U (en) * | 2014-04-09 | 2014-12-10 | 中国兵器工业集团第五三研究所 | A kind of threaded insert |
| CN204800906U (en) * | 2015-07-21 | 2015-11-25 | 宁波沥高复合材料有限公司 | Location built -in fitting that aerospace combined material mould was used |
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP3569828A1 (en) * | 2018-05-09 | 2019-11-20 | Safran Aero Boosters S.A. | Overmoulding metal insert for locally reinforcing a moulded part of an aircraft engine |
| BE1026267B1 (en) * | 2018-05-09 | 2019-12-10 | Safran Aero Boosters Sa | Metal overmolding insert for locally reinforcing a molded part of an aircraft engine |
| CN109236823A (en) * | 2018-10-10 | 2019-01-18 | 迪皮埃复材构件（太仓）有限公司 | A kind of strong magnetic metal embedded part for composite inner |
| CN109514890A (en) * | 2018-10-10 | 2019-03-26 | 迪皮埃复材构件（太仓）有限公司 | A kind of production method of composite material mould vacuum port |
| CN109236823B (en) * | 2018-10-10 | 2020-09-11 | 迪皮埃复材构件（太仓）有限公司 | Strong magnetic metal embedded part used inside composite material |
| CN109514890B (en) * | 2018-10-10 | 2021-05-14 | 迪皮埃复材构件（太仓）有限公司 | Method for manufacturing vacuum port of composite material mold |
| CN111497277A (en) * | 2020-04-20 | 2020-08-07 | 上海伽材新材料科技有限公司 | Accurate positioning structure and method for composite metal embedded part |
| CN112013004A (en) * | 2020-08-14 | 2020-12-01 | 湖北航天技术研究院总体设计所 | Connecting structure of composite material joint |
| CN112013004B (en) * | 2020-08-14 | 2022-02-01 | 湖北航天技术研究院总体设计所 | Connecting structure of composite material joint |
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