CN114103160B - Forming process method for preventing honeycomb chamfer instability of composite material interlayer part - Google Patents
Forming process method for preventing honeycomb chamfer instability of composite material interlayer part Download PDFInfo
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- CN114103160B CN114103160B CN202111297160.3A CN202111297160A CN114103160B CN 114103160 B CN114103160 B CN 114103160B CN 202111297160 A CN202111297160 A CN 202111297160A CN 114103160 B CN114103160 B CN 114103160B
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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
-
- 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
- B29C70/68—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts by incorporating or moulding on preformed parts, e.g. inserts or layers, e.g. foam blocks
- B29C70/681—Component parts, details or accessories; Auxiliary operations
- B29C70/682—Preformed parts characterised by their structure, e.g. form
-
- 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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- 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
Abstract
The application provides a molding process method for preventing honeycomb chamfer instability of a composite material interlayer part, which belongs to the technical field of vacuum bag molding of an autoclave of the composite material interlayer part, and comprises the steps of laying a silica gel sheet on a molding die on which a demolding film is laid, wherein the silica gel sheet covers a honeycomb core material chamfer, and the laying range of the silica gel sheet is larger than the honeycomb core material chamfer area; paving a vacuum bag on the forming die paved with the silica gel sheet, and isolating the vacuum bag from the silica gel sheet through a nonporous demolding film; carrying out in-tank curing on the forming die paved with the vacuum bag according to curing parameters required by the process file of the honeycomb sandwich part; discharging from the furnace, starting the mold, and removing the cured raw silicon wafer; and (5) performing mechanical cutting on the product. The application can effectively prevent the failure of unstability of the honeycomb chamfer in the process of molding and curing the composite sandwich component, improves the molding appearance quality and strength of the component, saves energy, reduces consumption, reduces manufacturing period, reduces cost and increases efficiency, and is used for the component with the composite honeycomb sandwich structure.
Description
Technical Field
The application belongs to the technical field of composite material interlayer part autoclave vacuum bag forming, and particularly relates to a forming process method for preventing composite material interlayer part honeycomb chamfer instability.
Background
Composite honeycomb sandwich structures are a special type of composite material. The basic principle of aircraft structural design is to make the structure as light as possible while meeting the strength requirements, which necessarily lead to the need to withstand tensile and compressive loads, as well as the coupling of shear, torsional and bending loads, with a stable thin skin. In the traditional aircraft structural design, a longitudinal reinforcing part, a stability-enhancing stringer, a rib, a bulkhead and other structural reinforcing skins are used, so that the problem of structural weight increase is inevitably caused. The honeycomb sandwich structure is a composite material formed by combining 3 basic materials, which provides possibility of widely changing parameters for structural personnel to meet design technical indexes, one of effective structural forms for improving structural specific rigidity is the sandwich structure, and the composite sandwich structure has the characteristics of light weight, good strength and rigidity, heat resistance, sound absorption, sound insulation, shock resistance, fatigue resistance and the like.
Most of the manufacturing methods of the composite honeycomb sandwich structure parts adopt autoclave vacuum bag technology, and the composite honeycomb sandwich structure parts are heated and solidified after being pressurized. The positive pressure applied in the autoclave during the curing process can generate lateral pressure on the honeycomb chamfer, and as the honeycomb core material is machined at present, the honeycomb chamfer is slightly damaged, so that the capability of laterally bearing the pressure of the honeycomb chamfer is reduced, and the honeycomb chamfer is unstable after the honeycomb sandwich piece is molded and cured, such as a honeycomb dent.
In the related art, the method for preventing the instability of the honeycomb chamfer mainly comprises the steps of adding 2-3 layers of prepreg tooling cloth in the process of pasting a vacuum bag, wherein although the method can also prevent the instability of the honeycomb chamfer, the forming and curing period (at least 2 hours) is prolonged, and the circumference of a formed composite material part can form an indentation of about 0.5 mm.
Disclosure of Invention
In order to solve the problem of honeycomb core material chamfer instability after composite material molding in the related art, the application provides a molding process method for preventing composite material interlayer part honeycomb chamfer instability, which comprises the following steps:
a molding process method for preventing instability of honeycomb chamfer of a composite material interlayer part, the method comprising:
forming a forming die on which a release film is laid;
laying a silica gel sheet on a forming die on which a release film is laid, wherein the silica gel sheet is of an annular structure, the silica gel sheet covers the chamfer of the honeycomb core material, and the laying range of the silica gel sheet is larger than the chamfer area of the honeycomb core material;
paving a vacuum bag on the forming die paved with the silica gel sheet, and isolating the vacuum bag from the silica gel sheet through a nonporous demolding film;
carrying out in-tank curing on the forming die paved with the vacuum bag according to curing parameters required by the process file of the honeycomb sandwich part;
discharging from the furnace, starting the mold, and removing the cured raw silicon wafer;
and (5) performing mechanical cutting on the product.
Optionally, the layering range of the raw silicon sheet is 20-25 mm greater than the chamfer area of the honeycomb core material.
Optionally, laying a green sheet on a forming die on which a release film is laid, including:
two layers of silica gel sheets are paved on a forming die paved with a demolding film, and the silica gel sheets far away from the demolding film are larger than the paving range of the silica gel sheets close to the demolding film.
Optionally, the raw silica gel sheet far from the release film is 20-25 mm larger than the raw silica gel sheet close to the release film.
Optionally, forming a forming die on which a release film is laid, comprising:
laying a plurality of layers of honeycomb sandwich piece outer skins on the forming die, vacuumizing and compacting, wherein the laying range of the periphery of the honeycomb sandwich piece outer skins is larger than the range of cutting lines of the forming die;
laying a honeycomb core material on a forming die on which the outer skin of the honeycomb sandwich piece is laid, wherein the honeycomb core material is attached to the outer skin of the honeycomb sandwich piece;
laying a multi-layer honeycomb sandwich piece inner skin on the forming die on which the honeycomb core material is laid, and vacuumizing and compacting;
and paving a demolding film on the forming die paved with the inner skin of the honeycomb sandwich piece, wherein the demolding film covers the whole product range.
Optionally, laying a multi-layer honeycomb sandwich outer skin over a forming die and vacuum compacting, comprising:
after laying the 1 st layer of honeycomb sandwich piece outer skin, vacuumizing to 0.07-0.09 MPa for precompaction, and executing vacuumizing operation once every 3-4 layers of honeycomb sandwich piece outer skin, wherein the execution time of each vacuumizing operation is 30-40 minutes.
Optionally, the laying range of the peripheral ring of the outer skin of the honeycomb sandwich part is 20-30 mm larger than the cutting line of the forming die.
Optionally, laying a multi-layer honeycomb sandwich inner skin on a forming die on which a honeycomb core material is laid, and vacuumizing and compacting the multi-layer honeycomb sandwich inner skin, wherein the multi-layer honeycomb sandwich inner skin comprises the following steps of:
after laying the inner skin of the 1 st layer of honeycomb sandwich piece, vacuumizing to 0.07-0.09 MPa for precompaction, and executing vacuum-pumping operation in sequence every 3-4 layers of honeycomb sandwich piece, wherein the execution time of each time of completing the vacuum-pumping operation is 30-40 minutes.
Optionally, after laying the multi-layer honeycomb sandwich inner skin on the forming die on which the honeycomb core is laid and vacuum compacting, the method further comprises:
and paving the stripping cloth on the forming die paved with the inner skin of the honeycomb sandwich piece, wherein the stripping cloth is positioned in a non-sandwich area of the composite material.
Optionally, the release film is 20-30 mm larger than the lay-up perimeter.
The molding process method for preventing the honeycomb chamfer instability of the composite material interlayer part has at least the following beneficial effects:
1. the honeycomb chamfer instability fault in the forming and curing process of the composite sandwich part is effectively prevented, the forming appearance quality and strength of the part are improved, the energy is saved, the consumption is reduced, the manufacturing period is shortened, and the cost is reduced and the efficiency is improved.
2. Compared with the traditional method for laying the tooling cloth, the novel process method does not need to provide a constant-temperature platform for tooling cloth curing, saves curing time by 2 hours and saves energy consumption.
3. The used raw silica gel sheet can be repeatedly used for 5-8 times after being molded and cured.
4. The used raw silica gel sheet is formed and solidified, and the indentation of the circumference of the part is small and is 0.1-0.2mm.
5. The used raw silica gel sheet is an elastomer after being molded and cured, yi Qimo, and three injuries are prevented from being generated in the mold opening process.
6. The laying method of the silica gel sheet is the same as the laying method of the prepreg cloth of the product, and the operation is simple and can be realized by common operators.
Drawings
FIG. 1 is a flow chart of a forming process method for preventing honeycomb chamfer instability of a composite material interlayer part, which is provided by the embodiment of the application;
fig. 2 is a schematic structural diagram of a molding process according to an embodiment of the present application.
Detailed Description
The application will be described in further detail below with reference to the accompanying drawings of specific embodiments.
Fig. 1 is a flow chart of a forming process method for preventing the honeycomb chamfer instability of a composite material interlayer part, which comprises the following steps:
step 110, forming a forming die on which a release film is laid;
step 120, paving a silica gel sheet on a forming die paved with a demolding film, wherein the silica gel sheet is of an annular structure, the silica gel sheet covers the chamfer of the honeycomb core material, and the paving range of the silica gel sheet is larger than the chamfer area of the honeycomb core material;
step 130, paving a vacuum bag on a forming die paved with a raw silica gel sheet, and isolating the vacuum bag from the raw silica gel sheet through a nonporous demolding film;
step 140, putting the forming die laid with the vacuum bag into a tank for curing according to curing parameters required by the process file of the honeycomb sandwich part;
step 150, discharging from the furnace, starting the mold, and removing the cured raw silicon wafer;
step 160, performing mechanical cutting of the product.
The application researches and applies a novel composite material interlayer part autoclave vacuum bag forming technology, which is used for solving the problem of the chamfer instability of the honeycomb core material after the composite material is formed, compared with the traditional forming process method for preventing the chamfer instability of the honeycomb of the composite material interlayer part, the application replaces prepreg tooling cloth with a raw silica gel sheet, and the other methods are indistinguishable from the traditional vacuum bag technology, and the application can be suitable for the composite material interlayer part with the curing temperature of less than 200 ℃, and has the key point that the upper layer is 20-25 mm larger than the lower layer of circumference when the raw silica gel sheet is laid, so as to prevent the residual indentation on the part after the forming and curing. The specific operation is that after the part is paved, sequentially paving stripping cloth, a demolding film, a silica gel sheet, an air felt, a pasting vacuum bag and detecting the air tightness of the vacuum bag on the part, and after the air tightness detection meets the requirement, putting the part into a furnace for curing. The method will be described in detail below.
Fig. 2 is a schematic structural diagram of the forming process according to the present application, please refer to fig. 2, and the forming process for preventing the honeycomb chamfer instability of the composite material interlayer part provided by the present application includes the following steps:
step 1: the forming tool is prepared, the whole working surface of the forming die 1 is wiped by cloth which is not dehaired and soaked with acetone or butanone, oil is removed, residues or dust are removed until new dust and grease are not generated on the wiping cloth, and the forming tool is ensured to lay the prepreg and other auxiliary materials of the vacuum bag in clean and dust-free areas.
Step 2: laying the honeycomb sandwich part outer skin 2, removing one surface of the protective film from the prepreg cloth which is well fed, enabling the surface to be abutted against the working surface of the forming die 1, and enabling the laying range of the peripheral ring of the outer skin to be 20-30 mm larger than the cutting line of the forming die 1. After the 1 st layer is paved, vacuumizing to 0.07-0.09 MPa for precompaction, vacuumizing once every 3-4 layers are paved, and vacuumizing for 30-40 minutes each time, wherein vacuumizing and compacting are required for the upper and lower layers of the honeycomb so as to ensure the compactness of the layers.
Step 3: and (3) laying a honeycomb core material 8 according to the honeycomb laying template or the forming die 1, ensuring that the honeycomb core material is attached to the outer skin 2 of the honeycomb sandwich part, checking whether a chamfer angle of the honeycomb core material is damaged before laying the honeycomb core material 8, and if so, replacing the honeycomb core material after finishing, and continuing laying.
Step 4: laying an inner skin 3 of the honeycomb sandwich piece, vacuumizing to 0.07-0.09 MPa for precompaction after the inner skin is laid for 1 layer, vacuumizing once every 3-4 layers are laid, and maintaining the vacuumizing for 30-40 minutes every time so as to ensure the compactness of the laid layers.
Step 5: the non-interlayer area of the composite material, namely the lamination area is paved with 1 layer of peeling cloth 4, and the peeling cloth 4 is of an annular structure. The peeling cloth 4 is laid according to specific requirements of the technological document, and the peeling cloth 4 is used for sucking glue. In practical application, the leather removing cloth is not required to be paved, the glue absorbing amount of the leather removing cloth is large, and the thickness of the formed part is thinner.
Step 6: and paving a demolding film 5, wherein the demolding film 5 covers the whole product range and is 20-30 mm larger than the paving circumference, and the demolding film is selected according to the process requirement, and can be a non-porous or porous demolding film.
Step 7: on the release film, 1-2 layers of silica gel sheets are laid, 2 layers of silica gel sheets are shown in fig. 2, a silica gel sheet 6 is laid firstly, then a silica gel sheet 7 is laid, and the silica gel sheet 6 and the silica gel sheet 7 cover the chamfer angle of the honeycomb core material and are 20-25 mm larger than the edge of the chamfer angle area of the honeycomb core material. The spreading range of the raw silica gel sheet 7 is 20-25 mm larger than that of the raw silica gel sheet 6. The silica gel sheet 7 and the silica gel sheet 6 are RTV1556A/B glue. In the embodiment, the laying layer number of the raw silicon films is determined according to actual requirements, for example, 2 raw silicon films can be laid when the thickness of the honeycomb core material is large or the curing pressure of the in-can is large.
Step 8: and manufacturing a vacuum bag, wherein the vacuum bag consists of an airfelt, a vacuum film and a sealing adhesive tape, and the specific manufacturing process can refer to the related technology. In the process, a nonporous release film is paved on the overlapping area of the silica gel sheet and the vacuum bag for isolation. After the vacuum bag is sealed, the vacuum degree is detected according to the requirements of process files, the detection is very important, and the curing can be carried out in the furnace only after the vacuum bag is qualified.
Step 9: and (3) carrying out tank filling and curing on the forming die paved with the vacuum bag according to curing parameters required by the process file of the honeycomb sandwich part, wherein the highest temperature is less than 200 ℃.
Step 10: and discharging, starting the mould when the temperature is reduced to below 60 ℃, storing the cured raw silica gel sheet 6 and the cured raw silica gel sheet 7 (equalizing plates), curing the raw silica gel sheet 6 and the raw silica gel sheet 7 into an elastic soft film after the curing, repeatedly using the soft film for 5 to 8 times, visually detecting the appearance of the soft film before each use, and re-laying the raw silica gel sheet if the soft film is aged or damaged and cannot be used again.
Step 11: the product is cut mechanically, and the process can be performed manually or in a numerical control mode.
After the honeycomb flap type part of a certain machine is paved according to the scheme of the application, through the verification of a 6-frame machine, the one-time molding qualification rate is improved from 30% to 90%, the composite design acceptance requirement is met, the repair is not needed, the part delivery period is reduced, the part production efficiency is improved, and the aims of reducing the cost and enhancing the efficiency are achieved.
The scheme has been verified in the honeycomb sandwich structure of various molding machines, under the condition that the design structure of the part and the technological parameters are not changed, the honeycomb chamfer recess can be effectively reduced through verification, the one-step molding qualification rate of the part is improved, the repair is reduced, the waste is reduced, and the quality and efficiency are improved.
According to the forming process method for preventing the honeycomb chamfer instability of the composite material interlayer part, the annular silica gel sheet is paved on the forming die paved with the demolding film, the silica gel sheet covers the honeycomb core chamfer, the paving range of the silica gel sheet is larger than the honeycomb core chamfer area, the defect of the honeycomb chamfer instability in the forming and curing process of the composite material interlayer part can be effectively prevented, the forming appearance quality and strength of the part are improved, the energy is saved, the consumption is reduced, the manufacturing period is shortened, and the cost is reduced and the efficiency is increased.
The foregoing has outlined rather broadly the more detailed description of the application in order that the detailed description thereof that follows may be better understood, and in order that the present application may be better understood. It should be noted that it will be apparent to those skilled in the art that several variations and modifications can be made without departing from the spirit of the application, which are all within the scope of the application.
Claims (8)
1. A molding process method for preventing honeycomb chamfer instability of a composite material interlayer part, which is characterized by comprising the following steps:
forming a forming die on which a release film is laid;
laying a silica gel sheet on a forming die on which a release film is laid, wherein the silica gel sheet is of an annular structure, the silica gel sheet covers the chamfer of the honeycomb core material, and the laying range of the silica gel sheet is larger than the chamfer area of the honeycomb core material; laying a silica gel sheet on a forming die on which a release film is laid, comprising: two layers of silica gel sheets are paved on a forming die paved with a demolding film, and the silica gel sheets far away from the demolding film are larger than the paving range of the silica gel sheets close to the demolding film; the spreading range of the raw silica gel sheet far away from the demolding film is 20-25 mm larger than that of the raw silica gel sheet near the demolding film;
paving a vacuum bag on the forming die paved with the silica gel sheet, and isolating the vacuum bag from the silica gel sheet through a nonporous demolding film;
putting the forming die laid with the vacuum bag into a tank for curing;
discharging from the furnace, starting the mold, and removing the cured raw silicon wafer;
and (5) performing mechanical cutting on the product.
2. The method of claim 1, wherein the step of determining the position of the substrate comprises,
the layering range of the raw silicon sheet is 20-25 mm larger than the chamfering area of the honeycomb core material.
3. The method of claim 1, wherein forming a forming die on which a release film is laid comprises:
laying a plurality of layers of honeycomb sandwich piece outer skins on the forming die, vacuumizing and compacting, wherein the laying range of the periphery of the honeycomb sandwich piece outer skins is larger than the range of cutting lines of the forming die;
laying a honeycomb core material on a forming die on which the outer skin of the honeycomb sandwich piece is laid, wherein the honeycomb core material is attached to the outer skin of the honeycomb sandwich piece;
laying a multi-layer honeycomb sandwich piece inner skin on the forming die on which the honeycomb core material is laid, and vacuumizing and compacting;
and paving a demolding film on the forming die paved with the inner skin of the honeycomb sandwich piece, wherein the demolding film covers the whole product range.
4. A method according to claim 3, wherein laying up a multi-layer honeycomb sandwich outer skin over a forming die and vacuum compacting comprises:
after laying the 1 st layer of honeycomb sandwich piece outer skin, vacuumizing to 0.07-0.09 MPa for precompaction, and executing vacuumizing operation once every 3-4 layers of honeycomb sandwich piece outer skin, wherein the execution time of each vacuumizing operation is 30-40 minutes.
5. A method according to claim 3, wherein the range of the peripheral ring of the outer skin of the honeycomb sandwich part is 20-30 mm larger than the range of the cutting line of the forming die.
6. A method according to claim 3, wherein laying a multilayer honeycomb sandwich inner skin on a former on which a honeycomb core is laid, and vacuum compacting, comprises:
after laying the inner skin of the 1 st layer of honeycomb sandwich piece, vacuumizing to 0.07-0.09 MPa for precompaction, and executing vacuumizing operation once every 3-4 layers of honeycomb sandwich piece, wherein the execution time of each vacuumizing operation is 30-40 minutes.
7. A method according to claim 3, wherein after laying the multilayer honeycomb sandwich inner skin on a forming die on which the honeycomb core is laid and vacuum compacting, the method further comprises:
and paving the stripping cloth on the forming die paved with the inner skin of the honeycomb sandwich piece, wherein the stripping cloth is positioned in a non-sandwich area of the composite material.
8. The method of claim 3, wherein the step of,
the demolding film is 20-30 mm larger than the laying circumference.
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| CN114851593B (en) * | 2022-04-21 | 2023-05-05 | 成都飞机工业（集团）有限责任公司 | Compensation method for honeycomb core lateral base angle of sandwich composite product |
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| DE102006062715A1 (en) * | 2006-08-23 | 2008-03-20 | Josef Wann Gmbh | Composite tiles for decorating kitchen-, laboratory- and restaurant furniture, comprise single component arranged in a cutout of the tiles, and a media receiving core board from core material with upper side, lower side and edge sides |
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