CN113232325B - Method for controlling thickness of composite material workpiece - Google Patents
Method for controlling thickness of composite material workpiece Download PDFInfo
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- CN113232325B CN113232325B CN202110346860.0A CN202110346860A CN113232325B CN 113232325 B CN113232325 B CN 113232325B CN 202110346860 A CN202110346860 A CN 202110346860A CN 113232325 B CN113232325 B CN 113232325B
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- composite material
- thickness
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- viscosity
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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
- B29C70/342—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 isostatic pressure
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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
- 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
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- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Composite Materials (AREA)
- Mechanical Engineering (AREA)
- Moulding By Coating Moulds (AREA)
- Casting Or Compression Moulding Of Plastics Or The Like (AREA)
Abstract
The invention discloses a method for controlling the thickness of a composite material part, and belongs to the technical field of forming processes. The method comprises the following steps: testing a composite material prepreg resin system by adopting a rheometer to obtain the temperature and time for controlling the thickness, and selecting the pressure P during the thickness control according to the curing pressure of the curing process of the composite material part; laying a blank of a composite material workpiece on a forming tool, placing a glue absorbing material on the surface of the blank after laying, and performing assembly glue absorption and thickness control according to the obtained temperature, time and pressure parameters; and (3) placing auxiliary materials on the surface of the composite material part subjected to thickness control, packaging a vacuum bag, and curing and forming according to a curing process. According to the invention, the temperature and time parameters for thickness control are selected according to the viscosity-temperature relationship of the composite material resin system, so that the thickness of the composite material part is effectively controlled, the thickness of the composite material part is controlled within +/-0.1 mm, the requirement on precise assembly of an airplane is met, and the method has universal applicability.
Description
Technical Field
The invention relates to the technical field of composite material production processes, in particular to a method for controlling the thickness of a composite material part.
Background
At present, the composite material is widely applied to airplanes, and the dosage ratio of the composite material is an important index for measuring the advancement of the airplanes. The thickness of the traditional composite material part is controlled to be +/-4%, the step difference is easy to generate in the assembling process, the repairing workload is increased, and the production efficiency is reduced. Therefore, as the requirement for precise assembly of the aircraft is increased, the requirement for controlling the thickness of the composite material part is gradually increased.
Through searching relevant documents at home and abroad, the inventor of the invention discloses a method for controlling the uniform glue absorption thickness, which is provided by the people of simple and convenient application and the like (invention patent: a method for uniformly absorbing glue by combining thick layers of carbon fiber composite materials and a laminated structure), and the technical scheme is as follows: and adding a glue absorbing material between the main prepreg materials, and performing multiple pre-pumping to finally solidify into a laminated plate with the designed thickness.
The above method has the following problems: 1) the manufacturing cost is improved and the production efficiency is reduced by multiple pre-pumping; 2) the glue absorbing material is finally solidified in the laminated plate, so that the original material design system is damaged; 3) this method is only suitable for laminates with a thickness greater than 5 mm.
Disclosure of Invention
The invention aims to solve the problems in the prior art and provides a method for controlling the thickness of a composite material part, so as to meet the requirement of the current airplane on accurate assembly, reduce the repair workload and improve the production efficiency.
In order to achieve the above object, the technical solution of the present invention is as follows:
a method for controlling the thickness of a composite material part is characterized by comprising the following steps:
step S101: testing a composite material prepreg resin system by adopting a rheometer to obtain the temperature and time for controlling the thickness, and selecting the pressure P during the thickness control according to the curing pressure of the curing process of the composite material part;
step S102: laying blanks of the composite material workpieces on a forming tool, placing glue absorbing materials on the surfaces of the blanks after laying is finished, and performing assembling glue absorbing and thickness control according to the temperature, time and pressure parameters obtained in the step S101;
step S103: and (3) placing auxiliary materials on the surface of the composite material part subjected to thickness control, packaging a vacuum bag, and curing and forming according to a curing process.
Further, in step S101, a rheometer is used to perform a viscosity-temperature test on the composite prepreg resin system to obtain a temperature-viscosity curve, a temperature T corresponding to the lowest viscosity point is selected as a thickness control temperature, then a constant temperature viscosity test is performed on the composite prepreg resin system by using the rheometer to obtain a time-viscosity curve, and a time T for maintaining low viscosity is selected as a thickness control time.
Furthermore, the forming tool is a rigid die body which is consistent with the geometric shape and size of the composite material workpiece close to the surface of the auxiliary material, and the forming tool is made of INVAR steel, aluminum alloy or composite material.
Furthermore, the placement position of the glue absorbing material selects full layering or partial layering according to the part assembly molded surface so as to ensure that the thickness of the part at the assembly position is uniform; and (3) setting the glue absorption amount per square meter as a through experimental verification, and placing the number n of the layers of the glue absorption materials according to the design thickness requirement h to obtain a thickness prediction formula:
h=f（σ-n*a*s）+ɛ
wherein sigma is the gel content of the prepreg blank; s is the prepreg blank area; (x) is a thickness as a function of gel content; ɛ is an error value.
Furthermore, the assembly glue absorption is that auxiliary materials are sequentially placed on the composite blank, the auxiliary materials comprise strippable layers, glue absorption materials, isolating films, air-permeable felts and vacuum bags, and after the vacuum pumping, the heating and the pressurization are carried out to complete the glue absorption of the composite part.
Further, the glue absorbing material is high-temperature resistant glass fiber dry fabric.
In summary, the invention has the following advantages:
1. according to the invention, a thickness control measure is added before the composite material is cured, the viscosity-temperature curve of a prepreg resin system of the composite material is tested, the temperature and time for thickness control are selected according to the designed thickness, the composite material blank is subjected to glue absorption treatment, and the purpose of controlling the final thickness of the composite material part is achieved by controlling the content of resin in curing molding;
2. the thickness control method can control the thickness of the composite material part to be +/-0.1 mm, meets the requirement of precise assembly of the airplane, and has universal applicability.
Drawings
FIG. 1 is a schematic of a typical temperature-viscosity of a resin;
FIG. 2 is a schematic of a typical time-viscosity of a resin;
FIG. 3 is a schematic of a thickness control assembly;
in the figure:
1. the manufacturing method comprises the following steps of forming a tool 2, manufacturing a composite material part 3, stripping 4, absorbing glue materials 5, isolating films 6, air-permeable felts 7 and vacuum bags.
Detailed Description
The present invention will be described in further detail with reference to examples, but the embodiments of the present invention are not limited thereto.
Example 1
Step S101: and testing the composite material prepreg resin system by adopting a rheometer to obtain the temperature and time for controlling the thickness, and selecting the pressure for controlling the thickness according to the curing pressure of the curing process of the composite material part 2.
Step S102: laying a blank of the composite material part 2 on the forming tool 1, placing a glue absorbing material 4 on the surface of the blank after laying, and assembling and absorbing glue for thickness control according to the temperature, time and pressure parameters obtained in the step S101;
step S103: and (3) placing auxiliary materials on the surface of the composite material part 2 with the controlled thickness, packaging a vacuum bag 7, and curing and forming according to a curing process.
In the step S101, a rheometer is used to perform viscosity-temperature test on a composite prepreg resin system to obtain resin viscosities (see a temperature-viscosity curve shown in fig. 1) at different temperatures, and according to the designed thickness, a temperature T1 corresponding to the lowest viscosity point is selected as the thickness control temperature; then, performing constant temperature viscosity test on the resin system by using a rheometer to obtain a time-viscosity curve shown in fig. 2, and selecting time t1 for maintaining low viscosity as thickness control time; the curing pressure for the curing process of the composite material part 2 is selected as the pressure P for thickness control.
The forming die tool in the step S102 is a rigid die body with a geometric shape and a size consistent with those of the surface of the composite material part 2 close to the auxiliary material, and the material can be INVAR steel, aluminum alloy, composite material and the like;
the glue absorbing material 4 in the step S102 is a high-temperature resistant glass fiber dry fabric, which has good air permeability and glue absorbing capacity, and can absorb the glue solution on the fiber fabric to control the uniformity of the thickness of the composite material part 2. The placing position selects a full-laying layer or a partial-laying layer according to the part assembling molded surface, and the thickness of parts at the assembling position is ensured to be uniform. Setting tests to verify that the glue absorption amount per square meter is a, placing 4 layers n of glue absorption materials according to the design thickness requirement h, and obtaining a thickness prediction formula:
h=f（σ-n*a*s）+ɛ
wherein sigma is the gel content of the prepreg blank; s is the prepreg blank area; (x) is a thickness as a function of gel content; ɛ is an error value.
In the step S102, the assembling and glue sucking are that auxiliary materials are sequentially placed on the composite material blank: the layer can be peeled, the glue absorbing material, the isolating membrane, the air-permeable felt and the vacuum bag are vacuumized, and then heated and pressurized to complete the glue absorption of the composite material part.
The package curing in step S103 is an improvement of the prior art and is not a point of the present invention, and therefore is not described again.
While the present invention has been described in detail with reference to the illustrated embodiments, it should not be construed as limited to the scope of the present patent. Various modifications and alterations within the scope of the description that is described herein will occur to persons skilled in the art without the aid of inventive faculty, and are intended to be covered by the appended claims.
The above description is only a preferred embodiment of the present invention, and is not intended to limit the present invention in any way, and all simple modifications and equivalent variations of the above embodiments according to the technical spirit of the present invention are included in the scope of the present invention.
Claims (5)
1. A method for controlling the thickness of a composite material part is characterized by comprising the following steps:
step S101: testing a composite material prepreg resin system by adopting a rheometer to obtain the temperature and time for controlling the thickness, and selecting the pressure P during the thickness control according to the curing pressure of the curing process of the composite material part;
step S102: laying blanks of the composite material workpieces on a forming tool, placing glue absorbing materials on the surfaces of the blanks after laying is finished, and performing assembling glue absorbing and thickness control according to the temperature, time and pressure parameters obtained in the step S101;
step S103: placing an auxiliary material on the surface of the composite material part subjected to thickness control, packaging a vacuum bag, and curing and forming according to a curing process;
in the step S101, a rheometer is adopted to perform viscosity-temperature test on a composite material prepreg resin system to obtain a temperature-viscosity curve, the temperature T corresponding to the lowest viscosity point is selected as the thickness control temperature, then the rheometer is adopted to perform constant temperature viscosity test on the composite material prepreg resin system to obtain a time-viscosity curve, and the time T for maintaining low viscosity is selected as the thickness control time.
2. The method as claimed in claim 1, wherein the forming tool is a rigid mold body having a geometric shape and a size consistent with those of the surface of the composite material member close to the auxiliary material, and the forming tool is made of INVAR steel, aluminum alloy or composite material.
3. The method for controlling the thickness of the composite material part as claimed in claim 1, wherein the placement position of the glue absorbing material selects full layering or partial layering according to the part assembly profile so as to ensure that the part thickness at the assembly position is uniform; and (3) setting the glue absorption amount per square meter as a through experimental verification, and placing the number n of the layers of the glue absorption materials according to the design thickness requirement h to obtain a thickness prediction formula:
h=f（σ-n*a*s）+ɛ
wherein sigma is the gel content of the prepreg blank; s is the prepreg blank area; (x) is a thickness as a function of gel content; ɛ is an error value.
4. The method as claimed in claim 1, wherein the step of glue absorption for assembly is that auxiliary materials are sequentially placed on the composite material blank, the auxiliary materials comprise a strippable layer, a glue absorption material, a separation film, a breathable felt and a vacuum bag, and the composite material blank is heated and pressurized after being vacuumized to complete the glue absorption of the composite material blank.
5. A method for controlling the thickness of a composite article as claimed in claim 1 or claim 3 wherein the glue-absorbing material is a high temperature resistant dry fabric of glass fibre.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN202110346860.0A CN113232325B (en) | 2021-03-31 | 2021-03-31 | Method for controlling thickness of composite material workpiece |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202110346860.0A CN113232325B (en) | 2021-03-31 | 2021-03-31 | Method for controlling thickness of composite material workpiece |
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| Publication Number | Publication Date |
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| CN113232325A CN113232325A (en) | 2021-08-10 |
| CN113232325B true CN113232325B (en) | 2022-04-08 |
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Family Cites Families (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2875278B2 (en) * | 1989-04-14 | 1999-03-31 | 本田技研工業株式会社 | Molding method of fiber reinforced resin |
| US5759325A (en) * | 1996-03-29 | 1998-06-02 | Sikorsky Aircraft Corporation | Method for controlling thickness during lay-up and fabrication of press-cured composite articles |
| US6406660B1 (en) * | 2000-02-07 | 2002-06-18 | The United States Of America As Represented By The Secretary Of The Army | Method for producing polymer matrix composites having low volume percentage of reinforcement fiber and controlled thickness |
| CN104908337A (en) * | 2015-04-28 | 2015-09-16 | 中国商用飞机有限责任公司 | Production method for control of composite material vacuum auxiliary moulding thickness |
| AU2016222310B2 (en) * | 2016-08-29 | 2022-09-29 | The Boeing Company | Method of locally influencing resin permeability of a dry preform |
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