CN116021798B - Zero-glue-absorption forming method of composite material for air inlet channel - Google Patents
Zero-glue-absorption forming method of composite material for air inlet channel Download PDFInfo
- Publication number
- CN116021798B CN116021798B CN202310042733.0A CN202310042733A CN116021798B CN 116021798 B CN116021798 B CN 116021798B CN 202310042733 A CN202310042733 A CN 202310042733A CN 116021798 B CN116021798 B CN 116021798B
- Authority
- CN
- China
- Prior art keywords
- pressure
- temperature
- sensitive adhesive
- air inlet
- composite material
- 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.)
- Active
Links
- 238000000034 method Methods 0.000 title claims abstract description 39
- 239000002131 composite material Substances 0.000 title claims abstract description 33
- 238000010521 absorption reaction Methods 0.000 title claims description 6
- 239000004820 Pressure-sensitive adhesive Substances 0.000 claims abstract description 64
- 238000000465 moulding Methods 0.000 claims abstract description 30
- 229920005989 resin Polymers 0.000 claims abstract description 21
- 239000011347 resin Substances 0.000 claims abstract description 21
- 239000004744 fabric Substances 0.000 claims abstract description 19
- 238000010438 heat treatment Methods 0.000 claims description 20
- 238000001816 cooling Methods 0.000 claims description 15
- 239000000463 material Substances 0.000 claims description 13
- XQUPVDVFXZDTLT-UHFFFAOYSA-N 1-[4-[[4-(2,5-dioxopyrrol-1-yl)phenyl]methyl]phenyl]pyrrole-2,5-dione Chemical compound O=C1C=CC(=O)N1C(C=C1)=CC=C1CC1=CC=C(N2C(C=CC2=O)=O)C=C1 XQUPVDVFXZDTLT-UHFFFAOYSA-N 0.000 claims description 6
- 238000007599 discharging Methods 0.000 claims description 6
- 239000011521 glass Substances 0.000 claims description 6
- 239000003292 glue Substances 0.000 claims description 6
- 229920003192 poly(bis maleimide) Polymers 0.000 claims description 6
- 238000000926 separation method Methods 0.000 claims description 6
- 238000009461 vacuum packaging Methods 0.000 claims description 6
- 229920000728 polyester Polymers 0.000 claims description 5
- 239000011152 fibreglass Substances 0.000 claims description 3
- KXGFMDJXCMQABM-UHFFFAOYSA-N 2-methoxy-6-methylphenol Chemical compound [CH]OC1=CC=CC([CH])=C1O KXGFMDJXCMQABM-UHFFFAOYSA-N 0.000 claims description 2
- CMLFRMDBDNHMRA-UHFFFAOYSA-N 2h-1,2-benzoxazine Chemical compound C1=CC=C2C=CNOC2=C1 CMLFRMDBDNHMRA-UHFFFAOYSA-N 0.000 claims description 2
- XLJMAIOERFSOGZ-UHFFFAOYSA-M cyanate Chemical compound [O-]C#N XLJMAIOERFSOGZ-UHFFFAOYSA-M 0.000 claims description 2
- 239000003822 epoxy resin Substances 0.000 claims description 2
- 229920001568 phenolic resin Polymers 0.000 claims description 2
- 239000005011 phenolic resin Substances 0.000 claims description 2
- 229920000647 polyepoxide Polymers 0.000 claims description 2
- 150000002466 imines Chemical class 0.000 claims 1
- 238000001556 precipitation Methods 0.000 abstract description 3
- 239000000853 adhesive Substances 0.000 description 10
- 230000001070 adhesive effect Effects 0.000 description 10
- 230000000052 comparative effect Effects 0.000 description 9
- 239000010410 layer Substances 0.000 description 6
- 239000004642 Polyimide Substances 0.000 description 5
- 229920001721 polyimide Polymers 0.000 description 5
- 239000004677 Nylon Substances 0.000 description 4
- 230000002401 inhibitory effect Effects 0.000 description 4
- 229920001778 nylon Polymers 0.000 description 4
- 229920001296 polysiloxane Polymers 0.000 description 4
- 238000002360 preparation method Methods 0.000 description 4
- 238000007711 solidification Methods 0.000 description 4
- 230000008023 solidification Effects 0.000 description 4
- 239000000835 fiber Substances 0.000 description 3
- 238000005516 engineering process Methods 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000003365 glass fiber Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 239000002994 raw material Substances 0.000 description 1
- 239000002356 single layer Substances 0.000 description 1
- 230000003746 surface roughness Effects 0.000 description 1
Classifications
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
Landscapes
- Casting Or Compression Moulding Of Plastics Or The Like (AREA)
Abstract
The invention relates to a zero-suction molding method of a composite material for an air inlet channel, and belongs to the technical field of helicopter air inlet channel composite material molding. The invention provides a zero-suction molding method of a composite material for an air inlet, which aims to solve the problem of resin loss of the existing molding method of the composite material for the air inlet. The zero-suction molding method adopts the pressure-sensitive adhesive tape to replace the peeled cloth, avoids the precipitation loss of resin in the curing process, has stable molding process, small thickness fluctuation of products and strong quality stability, is particularly suitable for molding light and thin products with smaller size, and is not limited by the types of prepregs.
Description
Technical Field
The invention belongs to the technical field of helicopter air inlet channel composite material molding, and particularly relates to a composite material zero-suction molding method for an air inlet channel.
Background
The air inlet is one of important components of the aerospace power system, and the air inlet is used for decelerating and pressurizing air flowing into the air inlet, converting part of kinetic energy into pressure energy and providing the pressure energy to the engine so as to ensure the normal operation of the engine. The quality of the air inlet channel directly influences the normal work and the maximum efficiency of the engine, and meanwhile, the flight performance of the aircraft is also influenced to a great extent.
The vacuum bag/autoclave molding technology is one of the most widely applied molding technologies in the aviation and aerospace fields, and can adapt to the requirements of various materials on processing technological conditions in a wide range. Most of the manufacturing methods of composite materials for helicopter air intake channels use vacuum bag/autoclave molding techniques. When the existing composite material for the air inlet channel is molded, the surface of the prepreg is paved with the skinning cloth after the prepreg is paved, and the surface roughness, thickness and weight of the product are controlled through the skinning cloth and the adhesive absorption. However, the skinning cloth can absorb a large amount of resin, so that the quality problems of poor glue, thick bottom, ultra-thin, ultra-light weight and the like of the composite material are caused by excessive resin loss, and the overall dimensional accuracy and the internal quality of the composite material part for the air inlet channel are affected.
Disclosure of Invention
The invention provides a zero-suction molding method of a composite material for an air inlet channel, which aims to solve the problem of resin loss of the existing molding method of the composite material for the air inlet channel.
The technical scheme of the invention is as follows:
a composite material zero-suction molding method for an air inlet channel comprises the following steps:
step one, layering: laying the prepreg into a mold, reserving the length and protecting the prepreg;
step two, sticking a pressure-sensitive adhesive tape: sticking a pressure-sensitive adhesive tape on the surface of the prepreg in the product area, wherein the pressure-sensitive adhesive tape extends beyond the edge of the prepreg and is stuck to the die;
step three, paving a separation film: laying a release film on the pressure sensitive adhesive tape to cover all product areas;
laying a ventilated felt: laying airfelt on the surface of the isolating film and enabling the airfelt to exceed the isolating film;
step five, vacuum packaging: placing the prepreg blank obtained by paving in the steps into a vacuum bag, and vacuumizing;
step six, curing: placing the vacuum bag filled with the prepreg blank in an autoclave, and heating and curing under certain pressure and temperature;
step seven, demolding: and (5) cooling the autoclave to room temperature, discharging from the autoclave, and demoulding to obtain the composite material for the air inlet channel.
Further, in the first step, the prepreg is bismaleimide resin-based glass cloth prepreg QY260/EW100A.
Further, the resin system in the prepreg is replaced by one of a medium-temperature or high-temperature cured epoxy resin, a phenolic resin, a cyanate resin or a benzoxazine resin.
Further, the pressure-sensitive adhesive tape used in the second step is a polyimide high temperature resistant pressure-sensitive adhesive tape AIRKAP, the thickness of the base material of the pressure-sensitive adhesive tape is 0.025mm, and the total thickness of the pressure-sensitive adhesive tape is 0.06mm.
Further, in the fourth step, the airfelt is glass fiber or polyester fiber.
Further, in the curing process of the step six, the positive pressure of the autoclave is not lower than 0.6MPa, and the vacuum degree in the product is not lower than-0.085 MPa.
Further, in the step six, the temperature is raised to 125+/-10 ℃ at a heating rate of 0.5-3 ℃/min and is kept for 60-75 min, the temperature is raised to 175+/-5 ℃ and is kept for 240-255 min, the temperature is raised to 200+/-5 ℃ and is kept for 60-75 min, the temperature is raised to 230+/-5 ℃ and is kept for 240-255 min, then the temperature is lowered at a cooling rate lower than 1.5 ℃/min, and the pressure is relieved when the temperature is lowered to below 80 ℃ to finish the curing.
The invention has the beneficial effects that:
the zero-suction molding method of the composite material for the air inlet channel adopts the pressure-sensitive adhesive tape to replace the peeled cloth, avoids the precipitation loss of resin in the curing process, and solves the problems of poor glue, thick bottom, ultra-thin product, ultra-light weight and the like caused by resin loss. The molding process of the molding method is stable, the fluctuation of the thickness of the product is small, the quality stability is strong, and the molding method is particularly suitable for molding light and thin products with smaller size and is not limited by the type of prepreg. In the forming method, the pressure sensitive adhesive tape is adhered to the surface of the prepreg when laid, and remains smooth when vacuumized, so that reworking caused by folds of auxiliary materials after vacuumized is avoided, and the production efficiency is improved; after molding, the pressure-sensitive adhesive tape has smaller adhesive force with the product, is easy to peel off, and shortens the molding period.
Drawings
FIG. 1 is a photograph of a composite product for an air intake duct of a helicopter prepared in accordance with the present invention.
Detailed Description
The following embodiments are used for further illustrating the technical scheme of the present invention, but not limited thereto, and all modifications and equivalents of the technical scheme of the present invention are included in the scope of the present invention without departing from the spirit and scope of the technical scheme of the present invention. The process equipment or apparatus not specifically noted in the following examples are all conventional equipment or apparatus in the art, and the raw materials and the like used in the examples of the present invention are commercially available unless otherwise specified; unless specifically indicated, the technical means used in the embodiments of the present invention are conventional means well known to those skilled in the art.
Example 1
The embodiment provides a composite material zero-suction molding method for an air inlet channel of a helicopter.
The prepreg material used in this example was bismaleimide resin-based glass cloth prepreg QY260/EW100A, purchased from Zhongboat composite Co., ltd. The pressure-sensitive adhesive tape used in this example was a polyimide high temperature resistant pressure-sensitive adhesive tape AIRKAP, the thickness of the base material of the pressure-sensitive adhesive tape was 0.025mm, the total thickness was 0.06mm, the adhesive was a silicone-containing adhesive, the elongation at break of the pressure-sensitive adhesive tape was 70%, and the maximum use temperature was 380 ℃. The airfelt used in this example is fiberglass.
The specific forming method of the embodiment comprises the following steps:
step one, layering: after the preparation of the mould is finished, sequentially laying 9 layers of prepreg into the mould, reserving the length for protecting the prepreg;
step two, sticking a pressure-sensitive adhesive tape: sticking pressure-sensitive adhesive tapes on the surfaces of the prepregs in the product area, wherein the pressure-sensitive adhesive tapes exceed the edges of the prepregs and are stuck to the mold, and the pressure-sensitive adhesive tapes are stuck in a lap joint manner and cannot leak out of the prepregs;
step three, paving a separation film: laying a release film on the pressure sensitive adhesive tape to cover all product areas;
laying a ventilated felt: laying airfelt on the surface of the isolating film and enabling the airfelt to exceed the isolating film;
step five, vacuum packaging: placing the prepreg blank obtained by paving in the steps into a vacuum bag, vacuumizing, and inhibiting a vacuum film from bridging in a product area;
step six, curing: placing the vacuum bag filled with the prepreg blank obtained in the step five in an autoclave, wherein the positive pressure of the autoclave is not lower than 0.6MPa, the vacuum degree in the product is not lower than-0.085 MPa, heating to 125 ℃ at a heating rate of 1 ℃/min and preserving heat for 60 min, continuously heating to 175 ℃ and preserving heat for 240 min, continuously heating to 200 ℃ and preserving heat for 60 min, continuously heating to 230 ℃ and preserving heat for 240 min, then cooling at a cooling rate of lower than 1.5 ℃/min, and releasing pressure when the temperature is reduced to below 80 ℃ to finish solidification;
step seven, demolding: and (5) cooling the autoclave to room temperature, discharging from the autoclave, and demoulding to obtain the composite material for the air inlet channel.
Example 2
The embodiment provides a composite material zero-suction molding method for an air inlet channel of a helicopter.
The prepreg material used in this example was bismaleimide resin-based glass cloth prepreg QY260/EW100A, purchased from Zhongboat composite Co., ltd. The pressure-sensitive adhesive tape used in this example was a polyimide high temperature resistant pressure-sensitive adhesive tape AIRKAP, the thickness of the base material of the pressure-sensitive adhesive tape was 0.025mm, the total thickness was 0.06mm, the adhesive was a silicone-containing adhesive, the elongation at break of the pressure-sensitive adhesive tape was 70%, and the maximum use temperature was 380 ℃. The airfelt used in this example is fiberglass.
The specific forming method of the embodiment comprises the following steps:
step one, layering: after the preparation of the mould is finished, sequentially laying 9 layers of prepreg into the mould, reserving the length for protecting the prepreg;
step two, sticking a pressure-sensitive adhesive tape: sticking pressure-sensitive adhesive tapes on the surfaces of the prepregs in the product area, wherein the pressure-sensitive adhesive tapes exceed the edges of the prepregs and are stuck to the mold, and the pressure-sensitive adhesive tapes are stuck in a lap joint manner and cannot leak out of the prepregs;
step three, paving a separation film: laying a release film on the pressure sensitive adhesive tape to cover all product areas;
laying a ventilated felt: laying airfelt on the surface of the isolating film and enabling the airfelt to exceed the isolating film;
step five, vacuum packaging: placing the prepreg blank obtained by paving in the steps into a vacuum bag, vacuumizing, and inhibiting a vacuum film from bridging in a product area;
step six, curing: placing the vacuum bag filled with the prepreg blank obtained in the step five in an autoclave, wherein the positive pressure of the autoclave is not lower than 0.6MPa, the vacuum degree in the product is not lower than-0.085 MPa, the temperature is raised to 115 ℃ at the heating rate of 0.5 ℃/min and kept for 65 min, the temperature is continuously raised to 170 ℃ and kept for 245 min, the temperature is continuously raised to 195 ℃ and kept for 65 min, the temperature is continuously raised to 225 ℃ and kept for 245 min, then the temperature is reduced at the cooling rate of lower than 1.5 ℃/min, and the pressure is relieved when the temperature is reduced to below 80 ℃ to finish solidification;
step seven, demolding: and (5) cooling the autoclave to room temperature, discharging from the autoclave, and demoulding to obtain the composite material for the air inlet channel.
Example 3
The embodiment provides a composite material zero-suction molding method for an air inlet channel of a helicopter.
The prepreg material used in this example was bismaleimide resin-based glass cloth prepreg QY260/EW100A, purchased from Zhongboat composite Co., ltd. The pressure-sensitive adhesive tape used in this example was a polyimide high temperature resistant pressure-sensitive adhesive tape AIRKAP, the thickness of the base material of the pressure-sensitive adhesive tape was 0.025mm, the total thickness was 0.06mm, the adhesive was a silicone-containing adhesive, the elongation at break of the pressure-sensitive adhesive tape was 70%, and the maximum use temperature was 380 ℃. The airfelt used in this example is polyester fiber.
The specific forming method of the embodiment comprises the following steps:
step one, layering: after the preparation of the mould is finished, sequentially laying 9 layers of prepreg into the mould, reserving the length for protecting the prepreg;
step two, sticking a pressure-sensitive adhesive tape: sticking pressure-sensitive adhesive tapes on the surfaces of the prepregs in the product area, wherein the pressure-sensitive adhesive tapes exceed the edges of the prepregs and are stuck to the mold, and the pressure-sensitive adhesive tapes are stuck in a lap joint manner and cannot leak out of the prepregs;
step three, paving a separation film: laying a release film on the pressure sensitive adhesive tape to cover all product areas;
laying a ventilated felt: laying airfelt on the surface of the isolating film and enabling the airfelt to exceed the isolating film;
step five, vacuum packaging: placing the prepreg blank obtained by paving in the steps into a vacuum bag, vacuumizing, and inhibiting a vacuum film from bridging in a product area;
step six, curing: placing the vacuum bag filled with the prepreg blank obtained in the step five in an autoclave, wherein the positive pressure of the autoclave is not lower than 0.6MPa, the vacuum degree in the product is not lower than-0.085 MPa, heating to 130 ℃ at a heating rate of 2 ℃/min and preserving heat for 70 min, continuously heating to 180 ℃ and preserving heat for 250 min, continuously heating to 205 ℃ and preserving heat for 70 min, continuously heating to 235 ℃ and preserving heat for 250 min, then cooling at a cooling rate of lower than 1.5 ℃/min, and releasing pressure when the temperature is reduced to below 80 ℃ to finish solidification;
step seven, demolding: and (5) cooling the autoclave to room temperature, discharging from the autoclave, and demoulding to obtain the composite material for the air inlet channel.
Example 4
The embodiment provides a composite material zero-suction molding method for an air inlet channel of a helicopter.
The prepreg material used in this example was bismaleimide resin-based glass cloth prepreg QY260/EW100A, purchased from Zhongboat composite Co., ltd. The pressure-sensitive adhesive tape used in this example was a polyimide high temperature resistant pressure-sensitive adhesive tape AIRKAP, the thickness of the base material of the pressure-sensitive adhesive tape was 0.025mm, the total thickness was 0.06mm, the adhesive was a silicone-containing adhesive, the elongation at break of the pressure-sensitive adhesive tape was 70%, and the maximum use temperature was 380 ℃. The airfelt used in this example is polyester fiber.
The specific forming method of the embodiment comprises the following steps:
step one, layering: after the preparation of the mould is finished, sequentially laying 9 layers of prepreg into the mould, reserving the length for protecting the prepreg;
step two, sticking a pressure-sensitive adhesive tape: sticking pressure-sensitive adhesive tapes on the surfaces of the prepregs in the product area, wherein the pressure-sensitive adhesive tapes exceed the edges of the prepregs and are stuck to the mold, and the pressure-sensitive adhesive tapes are stuck in a lap joint manner and cannot leak out of the prepregs;
step three, paving a separation film: laying a release film on the pressure sensitive adhesive tape to cover all product areas;
laying a ventilated felt: laying airfelt on the surface of the isolating film and enabling the airfelt to exceed the isolating film;
step five, vacuum packaging: placing the prepreg blank obtained by paving in the steps into a vacuum bag, vacuumizing, and inhibiting a vacuum film from bridging in a product area;
step six, curing: placing the vacuum bag filled with the prepreg blank obtained in the step five in an autoclave, wherein the positive pressure of the autoclave is not lower than 0.6MPa, the vacuum degree in the product is not lower than-0.085 MPa, heating to 135 ℃ at a heating rate of 3 ℃/min and preserving heat for 75 min, continuously heating to 175 ℃ and preserving heat for 255 min, continuously heating to 200 ℃ and preserving heat for 75 min, continuously heating to 230 ℃ and preserving heat for 255 min, then cooling at a cooling rate of lower than 1.5 ℃/min, and releasing pressure when the temperature is reduced to below 80 ℃ to finish solidification;
step seven, demolding: and (5) cooling the autoclave to room temperature, discharging from the autoclave, and demoulding to obtain the composite material for the air inlet channel.
Comparative example 1
The comparative example differs from example 1 only in that the pressure-sensitive adhesive tape of example 1 was replaced with a peal cloth, which was a high strength nylon peal cloth having a thickness of 0.13mm and a weight of 85 g/square meter.
Comparative example 2
The comparative example differs from example 2 only in that the pressure-sensitive adhesive tape of example 1 was replaced with a peal cloth, which was a high strength nylon peal cloth having a thickness of 0.13mm and a weight of 85 g/square meter.
Comparative example 3
The comparative example differs from example 3 only in that the pressure-sensitive adhesive tape of example 1 was replaced with a peal cloth, which was a high strength nylon peal cloth having a thickness of 0.13mm and a weight of 85 g/square meter.
Comparative example 4
The comparative example differs from example 4 only in that the pressure-sensitive adhesive tape of example 1 was replaced with a peal cloth, which was a high strength nylon peal cloth having a thickness of 0.13mm and a weight of 85 g/square meter.
The theoretical thickness of a monolayer after curing of QY260/EW100A was 0.09mm, and 9 layers of prepregs were laid down in each of examples 1 to 4 and comparative examples 1 to 4, as shown in Table 1, as the thickness of the 9 layers of prepregs and the thickness data of the products after demolding.
TABLE 1
As can be seen from the data in Table 1, the thickness of the product prepared by using the pressure-sensitive adhesive tape can be ensured to be stable, the pressure-sensitive adhesive tape is impermeable to glue and has higher temperature resistance, the precipitation of resin can be effectively blocked in the product curing process, the zero-glue-absorption molding is realized, and the resin loss of 67g per square meter of the product can be reduced. Meanwhile, the pressure sensitive adhesive tape is easy to strip from a product in the demolding process, is particularly suitable for molding a light and thin product with smaller size, and is not limited by the type of prepreg.
Claims (6)
1. A composite material zero-suction molding method for an air inlet channel is characterized by comprising the following steps:
step one, layering: laying the prepreg into a mold, reserving the length and protecting the prepreg;
step two, sticking a pressure-sensitive adhesive tape: sticking pressure-sensitive adhesive tapes on the surfaces of the prepregs in the product area, wherein the pressure-sensitive adhesive tapes exceed the edges of the prepregs and are stuck to the mold, and the pressure-sensitive adhesive tapes are stuck in a lap joint manner and cannot leak out of the prepregs; the pressure-sensitive adhesive tape is a polyester imine high temperature resistant pressure-sensitive adhesive tape AIRKAP, the thickness of the base material of the pressure-sensitive adhesive tape is 0.025mm, and the total thickness is 0.06mm;
step three, paving a separation film: laying a release film on the pressure sensitive adhesive tape to cover all product areas;
laying a ventilated felt: laying airfelt on the surface of the isolating film and enabling the airfelt to exceed the isolating film;
step five, vacuum packaging: placing the prepreg blank obtained by paving in the steps into a vacuum bag, vacuumizing, and keeping the pressure-sensitive adhesive tape flat during vacuumizing;
step six, curing: placing the vacuum bag filled with the prepreg blank in an autoclave, and heating and curing under certain pressure and temperature;
step seven, demolding: and (5) cooling the autoclave to room temperature, discharging from the autoclave, and demoulding to obtain the composite material for the air inlet channel.
2. The method for forming zero glue of composite material for air inlet duct according to claim 1, wherein the prepreg in the first step is bismaleimide resin-based glass cloth prepreg QY260/EW100A.
3. The method for zero-glue-absorption molding of composite material for air inlet channels according to claim 2, wherein the resin system in the prepreg is replaced by one of medium-temperature or high-temperature cured epoxy resin, phenolic resin, cyanate resin or benzoxazine resin.
4. A method of zero glue forming of air intake duct composites according to claim 3, wherein the airfelt in step four is fiberglass or polyester.
5. The method for forming the composite material zero-suction glue for the air inlet channel according to claim 4, wherein the positive pressure of the autoclave is not lower than 0.6MPa in the curing process in the step six, and the vacuum degree in the product is not lower than-0.085 MPa.
6. The method for forming the composite material zero-glue-absorption material for the air inlet channel according to claim 5, wherein in the sixth curing process, the temperature is raised to 125+/-10 ℃ at a heating rate of 0.5-3 ℃/min and is kept at the temperature for 60-75 min, the temperature is raised to 175+/-5 ℃ and is kept at the temperature for 240-255 min, the temperature is raised to 200+/-5 ℃ and is kept at the temperature for 60-75 min, the temperature is raised to 230+/-5 ℃ and is kept at the temperature for 240-255 min, then the temperature is lowered at a cooling rate of less than 1.5 ℃/min, and the pressure is relieved when the temperature is lowered to below 80 ℃ to finish the curing.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310042733.0A CN116021798B (en) | 2023-01-28 | 2023-01-28 | Zero-glue-absorption forming method of composite material for air inlet channel |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310042733.0A CN116021798B (en) | 2023-01-28 | 2023-01-28 | Zero-glue-absorption forming method of composite material for air inlet channel |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN116021798A CN116021798A (en) | 2023-04-28 |
| CN116021798B true CN116021798B (en) | 2023-10-20 |
Family
ID=86075631
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202310042733.0A Active CN116021798B (en) | 2023-01-28 | 2023-01-28 | Zero-glue-absorption forming method of composite material for air inlet channel |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN116021798B (en) |
Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105014956A (en) * | 2015-07-30 | 2015-11-04 | 江西洪都航空工业集团有限责任公司 | Closed-corner internal pressurization process suitable for composite material hard adhesive joint structure |
| CN105082568A (en) * | 2015-08-10 | 2015-11-25 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | Liquid molding process of special-shaped composite structural part |
| CN105579222A (en) * | 2013-08-01 | 2016-05-11 | 德莎欧洲公司 | Method for molding body in mold |
| CN106985416A (en) * | 2017-06-01 | 2017-07-28 | 江苏恒神股份有限公司 | The process of autoclave molding carbon fiber product |
| CN107283866A (en) * | 2017-05-25 | 2017-10-24 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | The purposes of porous ceramics and the method for carrying out non-autoclave prepreg shaping |
| CN108749028A (en) * | 2018-05-29 | 2018-11-06 | 沈阳飞机工业（集团）有限公司 | A kind of manufacturing method of normal temperature cure high temperature resistant auxiliary mould material system suitable for autoclave forming process |
| CN108928017A (en) * | 2018-06-21 | 2018-12-04 | 江西昌河航空工业有限公司 | A kind of curing method in composite material special type face |
| CN108943762A (en) * | 2018-07-12 | 2018-12-07 | 安徽佳力奇碳纤维科技股份公司 | A kind of suction of composite molding zero glue thermocouple setting method |
| CN109130240A (en) * | 2018-08-02 | 2019-01-04 | 西安电子工程研究所 | A kind of integrated molding die and forming method for covering copper electromagnetic shielding carbon fiber product |
| CN113942254A (en) * | 2021-09-24 | 2022-01-18 | 成都飞机工业（集团）有限责任公司 | Accurate control method for molding surface of honeycomb sandwich composite material part encapsulation area |
Family Cites Families (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP2404729B1 (en) * | 2005-10-21 | 2020-06-17 | Entrotech, Inc. | Composite articles comprising protective sheets and related methods |
| WO2012154544A2 (en) * | 2011-05-06 | 2012-11-15 | Purdue Research Foundation | Method and system of vacuum assisted resin transfer molding for repair of composite materials and structure |
| DE102015208320A1 (en) * | 2015-05-05 | 2016-11-10 | Tesa Se | Adhesive tape with temporary fixing adhesive |
| JP6788268B2 (en) * | 2016-02-22 | 2020-11-25 | 株式会社ダイワ工業 | Manufacturing method of wiring board or wiring board material |
| WO2018056276A1 (en) * | 2016-09-20 | 2018-03-29 | ユニチカ株式会社 | Release film and method for manufacturing same |
| GB2571786B (en) * | 2018-03-09 | 2021-06-02 | Gurit Uk Ltd | Manufacture of fire-retardant sandwich panels |
-
2023
- 2023-01-28 CN CN202310042733.0A patent/CN116021798B/en active Active
Patent Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105579222A (en) * | 2013-08-01 | 2016-05-11 | 德莎欧洲公司 | Method for molding body in mold |
| CN105014956A (en) * | 2015-07-30 | 2015-11-04 | 江西洪都航空工业集团有限责任公司 | Closed-corner internal pressurization process suitable for composite material hard adhesive joint structure |
| CN105082568A (en) * | 2015-08-10 | 2015-11-25 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | Liquid molding process of special-shaped composite structural part |
| CN107283866A (en) * | 2017-05-25 | 2017-10-24 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | The purposes of porous ceramics and the method for carrying out non-autoclave prepreg shaping |
| CN106985416A (en) * | 2017-06-01 | 2017-07-28 | 江苏恒神股份有限公司 | The process of autoclave molding carbon fiber product |
| CN108749028A (en) * | 2018-05-29 | 2018-11-06 | 沈阳飞机工业（集团）有限公司 | A kind of manufacturing method of normal temperature cure high temperature resistant auxiliary mould material system suitable for autoclave forming process |
| CN108928017A (en) * | 2018-06-21 | 2018-12-04 | 江西昌河航空工业有限公司 | A kind of curing method in composite material special type face |
| CN108943762A (en) * | 2018-07-12 | 2018-12-07 | 安徽佳力奇碳纤维科技股份公司 | A kind of suction of composite molding zero glue thermocouple setting method |
| CN109130240A (en) * | 2018-08-02 | 2019-01-04 | 西安电子工程研究所 | A kind of integrated molding die and forming method for covering copper electromagnetic shielding carbon fiber product |
| CN113942254A (en) * | 2021-09-24 | 2022-01-18 | 成都飞机工业（集团）有限责任公司 | Accurate control method for molding surface of honeycomb sandwich composite material part encapsulation area |
Non-Patent Citations (1)
| Title |
|---|
| 真空吸附技术在风力发电玻璃钢件上的应用;付秀君;李立民;;玻璃钢/复合材料(第05期);全文 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN116021798A (en) | 2023-04-28 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN110481059B (en) | A composite foam sandwich structure and its forming method | |
| CN105034403B (en) | Method for manufacturing composite shell | |
| CN109808196B (en) | Fiber laminated composite material containing high-orientation-degree carbon nano tubes between layers and preparation method thereof | |
| CN112590247A (en) | Method for integrally forming C-sandwich flat radome | |
| US8784089B2 (en) | Foamed tools | |
| CN110815875A (en) | Forming method of composite material honeycomb sandwich structure part | |
| CN113681937B (en) | Composite material cap-shaped stringer wallboard structure and preparation method | |
| CN107032658B (en) | Carbon fiber composite material and preparation method thereof | |
| CN108673909A (en) | A kind of carbon fiber product molding/decoration integrated technique | |
| CN116021798B (en) | Zero-glue-absorption forming method of composite material for air inlet channel | |
| CN114179462A (en) | Self-adhesive composite material honeycomb plate and preparation method thereof | |
| JPWO2019188195A1 (en) | Manufacturing method of fiber reinforced plastic | |
| CN117774375A (en) | Composite material ring frame and forming method and device thereof | |
| CN110595283B (en) | Production process of bulletproof flashboard | |
| CN114559680B (en) | Forming die and forming method for ship propeller composite material blade autoclave | |
| CN207128360U (en) | A kind of core filled composite material | |
| CN109177230A (en) | A method of improving composite product mass production efficiency | |
| CN115742474B (en) | A wave absorbing layer with low curing deformation and a preparation method thereof | |
| CN112851385A (en) | Continuous alumina fiber reinforced ceramic matrix composite with adjustable dielectric property and preparation method thereof | |
| CN111716601A (en) | A preparation method of a large-scale main bearing composite material structure and a molding die used therefor | |
| CN115195155A (en) | High-temperature-resistant high-pressure-resistant vacuum bag film sealing structure and method | |
| CN102303410A (en) | Method for molding core and cavity of corner sealing element | |
| CN114670466A (en) | Laminate with high post-impact compressive strength and method of making same | |
| CN116691031A (en) | Composite material structural member modularized variable-temperature zone vacuum curing device and forming method | |
| CN114311748B (en) | A composite material connector for aviation and its preparation method and installation method |
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 |