CN113334798B - Method for forming porous composite material part - Google Patents
Method for forming porous composite material part Download PDFInfo
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- CN113334798B CN113334798B CN202110473327.0A CN202110473327A CN113334798B CN 113334798 B CN113334798 B CN 113334798B CN 202110473327 A CN202110473327 A CN 202110473327A CN 113334798 B CN113334798 B CN 113334798B
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- Prior art keywords
- composite material
- forming
- positioning pin
- porous composite
- soft film
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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
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/28—Shaping operations therefor
- B29C70/30—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core
- B29C70/34—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression, i.e. combined with compressing after the lay-up operation
- B29C70/345—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression, i.e. combined with compressing after the lay-up operation using matched moulds
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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
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/28—Shaping operations therefor
- B29C70/54—Component parts, details or accessories; Auxiliary operations, e.g. feeding or storage of prepregs or SMC after impregnation or during ageing
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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
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/28—Shaping operations therefor
- B29C70/54—Component parts, details or accessories; Auxiliary operations, e.g. feeding or storage of prepregs or SMC after impregnation or during ageing
- B29C70/545—Perforating, cutting or machining during or after moulding
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29L—INDEXING SCHEME ASSOCIATED WITH SUBCLASS B29C, RELATING TO PARTICULAR ARTICLES
- B29L2031/00—Other particular articles
- B29L2031/30—Vehicles, e.g. ships or aircraft, or body parts thereof
- B29L2031/3076—Aircrafts
Abstract
The invention discloses a tooling for a porous composite material part and a forming method thereof, relating to the technical field of composite material forming in the aviation industry.A forming tooling with a positioning pin hole and a process setting hole is designed and manufactured according to the geometric characteristics of a digifax of the porous composite material part, and the aperture of the process setting hole on a tooling die is set according to the aperture parameter on the digifax of the porous composite material part; pre-laying a soft film on a forming die, inserting a steel nail into a process setting hole on the forming die by penetrating the soft film through a laser positioning mode, and taking down the soft film with the steel nail to obtain an assembly A; and (3) laying a composite material prepreg on a forming die according to the digital-analog requirement, determining the position of the soft film through a positioning pin on the component A, and inserting a steel nail into a process setting hole on a forming tool after penetrating the composite material prepreg. After curing, the soft film and the steel nails on the part are taken down, and the edge and the holes of the part are modified to finish the porous composite material part.
Description
Technical Field
The invention relates to the technical field of composite material forming in the aviation industry, in particular to a method for forming a porous composite material part.
Background
The composite material is widely applied to aviation structural parts due to excellent properties of light weight, high strength, high modulus and the like. The proportion of the composite material in the aircraft structure becomes an important index for evaluating the advancement of the aircraft. Compared with metal materials, the composite material has strong designability. Composite parts with more complex structural design and higher functional requirements are gradually becoming the object of design favor. As shown in fig. 5, a composite material part with multiple small holes as in the prior art has a plurality of small holes thereon, and the diameter of the holes is very small, generally from Φ 1mm to Φ 5 mm; meanwhile, the requirement on the position precision of the hole is high. The original processing mode is that after the composite material part is manufactured, a sample plate is manually used for tracing points (with larger deviation), an assembling tool is used for pneumatic drilling and punching according to the positions of the points, and then a notch hole expanding tool is used for expanding the holes. The disadvantages of the original processing mode are: (1) the method has the advantages that large deviation exists in the point tracing by adopting a sample plate, and parts are easily scrapped due to out-of-tolerance; (2) the holes of the parts are densely arranged and measured in a number manner, so that artificial fatigue is easy to generate during drilling, and out-of-tolerance holes are easy to generate.
Disclosure of Invention
In order to solve the technical problems, the invention provides a method for molding a porous composite material part, which not only can manufacture qualified products according to the digital and analog requirements of the porous composite material part, but also can reduce the failure rate of the products and effectively reduce the manufacturing cost of the porous composite material part.
The purpose of the invention is realized by the following technical scheme:
the utility model provides a porous combined material is frock for finished piece which characterized in that: including forming die, forming die four corners department is provided with the locating pin hole, the forming die middle part is provided with the part and puts the district, the part is put the district and is provided with a plurality of technology and sets up the hole.
Preferably, the distance between the positioning pin hole and the boundary line of the part laying area is 80mm-100 mm.
Preferably, the diameter phi of the process setting hole is 1mm-5 mm.
Preferably, the depth h of the process setting hole is 10mm-15 mm.
A method for forming a porous composite material part is characterized by comprising the following steps:
the method comprises the following steps that firstly, a soft film is placed on a forming die, a steel nail penetrates through the soft film and is embedded into a technological setting hole by means of laser projection positioning, then a gasket is placed on the soft film, and a positioning pin penetrates through the gasket and the soft film and is embedded into a positioning pin hole; curing, forming and demolding to obtain a soft film, and combining the soft film with steel nails and positioning pins to form a component A;
laying the composite material prepreg in the part laying area, and placing the positioning cushion block outside the part laying area; combining the component A and the composite material prepreg sheet together through a positioning pin on the component A and a positioning pin hole on a forming die, enabling a steel nail to penetrate through the composite material prepreg sheet and be embedded into a technological setting hole, and enabling the positioning pin to penetrate through a positioning cushion block and be embedded into the positioning pin hole; curing, molding and demolding to obtain a component B;
and step three, taking down the soft membrane and the steel nails on the component B, and modifying the edges and the holes of the component to obtain the porous composite material product.
Preferably, the first step and the second step further comprise brushing a release agent on the forming die and the steel nail in advance.
Preferably, the second step further comprises laying a layer of isolating membrane on the composite material prepreg and the positioning cushion block.
The working principle is as follows: designing and manufacturing a forming tool with a positioning pin hole and a process setting hole according to the geometrical characteristics of the digifax of the porous composite material workpiece, wherein the aperture of the process setting hole on a tool die is set according to the aperture parameters of the digifax of the porous composite material workpiece; pre-laying a soft film on a forming die, inserting a steel nail into a process setting hole on the forming die by penetrating the soft film through a laser positioning mode, and taking down the soft film with the steel nail to obtain an assembly A; and (3) laying a composite material prepreg on a forming die according to the digital-analog requirement, determining the position of the soft film through a positioning pin on the component A, and inserting a steel nail into a process setting hole on a forming tool after penetrating the composite material prepreg. After curing, the soft film and the steel nails on the part are taken down, and the edge and the holes of the part are modified to finish the porous composite material part.
The invention has the beneficial effects that: the novel forming method is provided for the porous composite material part, the process forming difficulty of the composite material part with a plurality of fine pores is effectively solved, the manufacturing method is simple, and the operation is convenient and reliable.
Drawings
The invention will be described in further detail with reference to the following description taken in conjunction with the accompanying drawings and detailed description, in which:
FIG. 1 is a front view of a molding tool for a workpiece with a porous composite material according to the present invention;
FIG. 2 is a cross-sectional view of a molding tool with a porous composite material part according to the present invention;
FIG. 3 is a schematic cross-sectional view of a flexible membrane with a porous composite article according to the present invention;
FIG. 4 is a schematic cross-sectional view of an assembly of the present invention with a porous composite article;
FIG. 5 is a schematic view of an article of the present invention with a porous composite;
the labels in the figure are: 1. forming a mold; 2. positioning a pin hole; 3. a part placement area; 4. a process setting hole; 5. a soft film; 6. steel nails; 7. positioning a pin; 8. a gasket; 9. positioning a cushion block; 10. a composite prepreg sheet; 11. and (5) isolating the membrane.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be obtained by a person skilled in the art without making any creative effort based on the embodiments in the present invention, belong to the protection scope of the present invention.
In the description of the present invention, it is to be understood that the terms "upper", "lower", "front", "rear", "left", "right", "top", "bottom", "inner", "outer", and the like, are used in the orientations and positional relationships indicated in the drawings, which are based on the orientations and positional relationships indicated in the drawings, and are used for convenience of description and simplicity of description, but do not indicate or imply that the devices or elements referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus, are not to be construed as limiting the present invention.
Example 1
As a most basic embodiment of the present invention, this embodiment discloses a tooling for a porous composite material part, as shown in fig. 1 and fig. 2, the tooling includes a forming mold 1, positioning pin holes 2 are provided at four corners of the forming mold 1, a part laying area 3 is provided in the middle of the forming mold 1, and the part laying area 3 is provided with a plurality of process setting holes 4.
As shown in fig. 3 and 4, a method for forming a porous composite material part comprises the following steps:
firstly, placing a soft film 5 on a forming die 1, wherein the soft film 5 is made of rubber, penetrating a steel nail 6 through the soft film 5 and embedding the steel nail into a process setting hole 4 by means of laser projection positioning, then placing a gasket 8 on the soft film 5, and embedding a positioning pin 7 into a positioning pin hole 2 through the gasket 8 and the soft film 5; curing, molding and demolding to obtain a soft film 5, a steel nail 6 and a positioning pin 7 which are combined into a component A;
secondly, laying the composite material prepreg 10 on the part laying area 3, and placing the positioning cushion block 9 outside the part laying area 3; the assembly A and the composite material prepreg 10 are combined together through the positioning pin 7 on the assembly A and the positioning pin hole 2 on the forming die 1, so that the steel nail 6 penetrates through the composite material prepreg 10 to be embedded into the technological setting hole 4, and the positioning pin 7 penetrates through the positioning cushion block 9 to be embedded into the positioning pin hole 2; curing, molding and demolding to obtain a component B;
and step three, taking down the soft membrane 5 and the steel nail 6 on the component B, and modifying the edges and holes of the part to obtain the porous composite material part.
Example 2
As a most preferable embodiment of the present invention, the present embodiment discloses a tooling for a porous composite material part, as shown in fig. 1 and fig. 2, the tooling comprises a forming mold 1, positioning pin holes 2 are arranged at four corners of the forming mold 1, a part placement area 3 is arranged at the middle part of the forming mold 1, the part placement area 3 is provided with a plurality of process setting holes 4, a distance between the positioning pin holes 2 and a boundary line of the part placement area 3 is 80mm to 100mm, a diameter Φ of the process setting hole 4 is 1mm to 5mm, and a depth h of the process setting hole 4 is 10mm to 15 mm.
As shown in fig. 3 and 4, a method for forming a porous composite material part comprises the following steps:
firstly, brushing a release agent on a forming die 1 and a steel nail 6 in advance, placing a flexible film 5 on the forming die 1, penetrating the steel nail 6 through the flexible film 5 and embedding the steel nail 6 into a process setting hole 4 by means of laser projection positioning by using rubber as the flexible film 5, then placing a gasket 8 on the flexible film 5, and embedding a positioning pin 7 into a positioning pin hole 2 through the gasket 8 and the flexible film 5; curing, molding and demolding to obtain a soft film 5, a steel nail 6 and a positioning pin 7 which are combined into a component A;
step two, brushing a release agent on the forming die 1 and the steel nail 6 in advance, laying the composite material prepreg 10 in the part laying area 3, and placing the positioning cushion block 9 outside the part laying area 3; laying a layer of isolation film 11 on the composite material prepreg 10 and the positioning cushion block 9 to prevent the composite material prepreg from being bonded on the soft film (5) after the curing process; the assembly A and the composite material prepreg 10 are combined together through the positioning pin 7 on the assembly A and the positioning pin hole 2 on the forming die 1, so that the steel nail 6 penetrates through the composite material prepreg 10 to be embedded into the technological setting hole 4, and the positioning pin 7 penetrates through the positioning cushion block 9 to be embedded into the positioning pin hole 2; curing, molding and demolding to obtain a component B;
and step three, taking down the soft membrane 5 and the steel nail 6 on the component B, and modifying the edges and holes of the part to obtain the porous composite material part.
In summary, after reading the present disclosure, those skilled in the art can make various other corresponding changes without creative efforts according to the technical solutions and technical concepts of the present disclosure, which all belong to the protection scope of the present disclosure.
Claims (6)
1. A method for forming a porous composite material part is characterized by comprising the following steps: the tool for the porous composite material workpiece comprises a forming die (1), wherein positioning pin holes (2) are formed in four corners of the forming die (1), a part laying area (3) is arranged in the middle of the forming die (1), and a plurality of process arrangement holes (4) are formed in the part laying area (3);
the molding method comprises the following steps:
the method comprises the following steps that firstly, a soft film (5) is placed on a forming die (1), a steel nail (6) penetrates through the soft film (5) and is embedded into a process setting hole (4) in a laser projection positioning mode, then a gasket (8) is placed on the soft film (5), and a positioning pin (7) penetrates through the gasket (8) and the soft film (5) and is embedded into a positioning pin hole (2); curing, molding and demolding to obtain a soft film (5), a steel nail (6) and a positioning pin (7) which are combined into a component A;
secondly, laying the composite material prepreg (10) in the part laying area (3), and placing the positioning cushion block (9) outside the part laying area (3); the assembly A and the composite material prepreg (10) are combined together through a positioning pin (7) on the assembly A and a positioning pin hole (2) on a forming die (1), a steel nail (6) penetrates through the composite material prepreg (10) and is embedded into a process setting hole (4), and the positioning pin (7) penetrates through a positioning cushion block (9) and is embedded into the positioning pin hole (2); curing, molding and demolding to obtain a component B;
and step three, taking down the soft membrane (5) and the steel nails (6) on the component B, and modifying the edges and holes of the parts to obtain the porous composite material part.
2. A method of forming a porous composite article as claimed in claim 1, wherein: the distance between the positioning pin hole (2) and the boundary line of the part laying area (3) is 80-100 mm.
3. A method of forming a porous composite article as claimed in claim 1, wherein: the diameter phi of the process setting hole (4) is 1mm-5 mm.
4. A method of forming a porous composite article as claimed in claim 1, wherein: the depth h of the technical setting hole (4) is 10mm-15 mm.
5. A method of forming a porous composite article as claimed in claim 1, wherein: the first step and the second step also comprise brushing a release agent on the forming die (1) and the steel nail (6) in advance.
6. A method of forming a porous composite article as claimed in claim 5 wherein: and the second step also comprises the step of laying a layer of isolating membrane (11) on the composite material prepreg (10) and the positioning cushion block (9).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110473327.0A CN113334798B (en) | 2021-04-29 | 2021-04-29 | Method for forming porous composite material part |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110473327.0A CN113334798B (en) | 2021-04-29 | 2021-04-29 | Method for forming porous composite material part |
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| Publication Number | Publication Date |
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| CN113334798A CN113334798A (en) | 2021-09-03 |
| CN113334798B true CN113334798B (en) | 2022-07-15 |
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| US3704194A (en) * | 1970-07-02 | 1972-11-28 | Gen Electric | Perforated reinforced plastic member and method for making |
| GB9016636D0 (en) * | 1990-07-28 | 1990-09-12 | Westland Aerostructures Ltd | Method for making perforated composite laminates and moulds for use therein |
| JPH084643B2 (en) * | 1993-07-16 | 1996-01-24 | 株式会社ブリヂストン | Golf club head manufacturing method |
| US6117376A (en) * | 1996-12-09 | 2000-09-12 | Merkel; Michael | Method of making foam-filled composite products |
| AUPS289402A0 (en) * | 2002-06-11 | 2002-07-04 | Mitchell, Jennifer Joyce | Composite board and process for making the board |
| US8128775B2 (en) * | 2008-12-30 | 2012-03-06 | Mra Systems, Inc. | Process and apparatus for producing composite structures |
| CN102407606A (en) * | 2010-09-20 | 2012-04-11 | 江苏环球龙圣环境科技发展有限公司 | Thin shell cabin cover die for wind-driven generator and manufacturing method thereof |
| CN102275342B (en) * | 2011-06-08 | 2013-09-18 | 沈阳飞机工业（集团）有限公司 | Honeycomb sandwich piece pre-encapsulation molding tool and process method thereof |
| CN203611402U (en) * | 2013-10-12 | 2014-05-28 | 航天海鹰(镇江)特种材料有限公司 | Auxiliary molding and demolding tool for molding composite material part through soft tool |
| CN109353035A (en) * | 2018-09-25 | 2019-02-19 | 成都飞机工业（集团）有限责任公司 | A kind of composite structure adhering method without technology nail positioning |
| CN114502360A (en) * | 2019-06-07 | 2022-05-13 | 泰普爱复合材料股份有限公司 | Mold precision pin for component positioning during manufacture of wind turbine blades |
| CN111716599B (en) * | 2020-06-22 | 2021-05-07 | 大连理工大学 | Detachable composite material flexible skin manufacturing device and using method |
| CN213056087U (en) * | 2020-06-29 | 2021-04-27 | 浙江恒石纤维基业有限公司 | Composite material forming die |
| CN112318896A (en) * | 2020-11-05 | 2021-02-05 | 成都联科航空技术有限公司 | Die and forming method for curved-surface metal honeycomb composite material |
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